WorldWideScience

Sample records for aircraft by type of lift

  1. Design of heavy lift cargo aircraft

    Data.gov (United States)

    National Aeronautics and Space Administration — This is the bird of the skies of the future. The heavy lift cargo aircraft which is currently being developed by me has twice the payload capacity of an Antonov...

  2. CFD Study of an Annular-Ducted Fan Lift System for VTOL Aircraft

    OpenAIRE

    Yun Jiang; Bo Zhang; Tao Huang

    2015-01-01

    The present study aimed at assessing a novel annular-ducted fan lift system for VTOL aircraft through computational fluid dynamics (CFD) simulations. The power and lift efficiency of the lift fan system in hover mode, the lift and drag in transition mode, the drag and flight speed of the aircraft in cruise mode and the pneumatic coupling of the tip turbine and jet exhaust were studied. The results show that the annular-ducted fan lift system can have higher lift efficiency compared to the ro...

  3. CFD Study of an Annular-Ducted Fan Lift System for VTOL Aircraft

    Directory of Open Access Journals (Sweden)

    Yun Jiang

    2015-09-01

    Full Text Available The present study aimed at assessing a novel annular-ducted fan lift system for VTOL aircraft through computational fluid dynamics (CFD simulations. The power and lift efficiency of the lift fan system in hover mode, the lift and drag in transition mode, the drag and flight speed of the aircraft in cruise mode and the pneumatic coupling of the tip turbine and jet exhaust were studied. The results show that the annular-ducted fan lift system can have higher lift efficiency compared to the rotor of the Apache helicopter; the smooth transition from vertical takeoff to cruise flight needs some extra forward thrust to overcome a low peak of drag; the aircraft with the lift fan system enclosed during cruise flight theoretically may fly faster than helicopters and tiltrotors based on aerodynamic drag prediction, due to the elimination of rotor drag and compressibility effects on the rotor blade tips; and pneumatic coupling of the tip turbine and jet exhaust of a 300 m/s velocity can provide enough moment to spin the lift fan. The CFD results provide insight for future experimental study of the annular-ducted lift fan VTOL aircraft.

  4. A perspective on 15 years of proof-of-concept aircraft development and flight research at Ames-Moffett by the Rotorcraft and Powered-Lift Flight Projects Division, 1970-1985

    Science.gov (United States)

    Few, David D.

    1987-01-01

    A proof-of-concept (POC) aircraft is defined and the concept of interest described for each of the six aircraft developed by the Ames-Moffet Rotorcraft and Powered-Lift Flight Projects Division from 1970 through 1985; namely, the OV-10, the C-8A Augmentor Wing, the Quiet Short-Haul Research Aircraft (QSRA), the XV-15 Tilt Rotor Research Aircraft (TRRA), the Rotor Systems Research Aircraft (RSRA)-compound, and the yet-to-fly RSRA/X-Wing Aircraft. The program/project chronology and most noteworthy features of the concepts are reviewed. The paper discusses the significance of each concept and the project demonstrating it; it briefly looks at what concepts are on the horizon as potential POC research aircraft and emphasizes that no significant advanced concept in aviation technology has ever been accepted by civilian or military users without first completing a demonstration through flight testing.

  5. Application of powered lift and mechanical flap concepts for civil short-haul transport aircraft design

    Science.gov (United States)

    Conlon, J. A.; Bowles, J. V.

    1977-01-01

    The objective of this paper is to determine various design and performance parameters, including wing loading and thrust loading requirements, for powered-lift and mechanical flap conceptual aircraft constrained by field length and community noise impact. Mission block fuel and direct operating costs (DOC) were found for optimum designs. As a baseline, the design and performance parameters were determined for the aircraft using engines without noise suppression. The constraint of the 90 EPNL noise contour being less than 2.6 sq km (1.0 sq mi) in area was then imposed. The results indicate that for both aircraft concepts the design gross weight, DOC, and required mission block fuel decreased with field length. At field lengths less than 1100 m (3600 ft) the powered lift aircraft had lower DOC and block fuel than the mechanical flap aircraft but produced higher unsuppressed noise levels. The noise goal could easily be achieved with nacelle wall treatment only and thus resulted in little or no performance or weight penalty for all studied aircraft.

  6. The STOL performance of a two-engine, USB powered-lift aircraft with cross-shafted fans

    Science.gov (United States)

    Stevens, V. C.; Wilson, S. B., III; Zola, C. A.

    1985-01-01

    The short takeoff and landing capabilities that characterize the performance of powered-lift aircraft are dependent on engine thrust and are, therefore, severely affected by loss of an engine. This paper shows that the effects of engine loss on the short takeoff and landing performance of powered-lift aircraft can be effectively mitigated by cross-shafting the engine fans in a twin-engine configuration. Engine-out takeoff and landing performances are compared for three powered-lift aircraft configurations: one with four engines, one with two engines, and one with two engines in which the fans are cross-shafted. The results show that the engine-out takeoff and landing performance of the cross-shafted two-engine configuration is significantly better than that of the two-engine configuration without cross-shafting.

  7. Factors affecting handling qualities of a lift-fan aircraft during steep terminal area approaches

    Science.gov (United States)

    Gerdes, R. M.; Hynes, C. S.

    1975-01-01

    The XV-5B lift-fan aircraft was used to explore the factors affecting handling qualities in the terminal area. A 10 deg ILS approach task was selected to explore these problems. Interception of the glide slope at 457.2 m, glide slope tracking, deceleration along the glide slope to a spot hover were considered. Variations in airplane deck angle, deceleration schedule, and powered-lift management were studied. The overall descent performance envelope was identified on the basis of fan stall, maximum comfortable descent rate, and controllability restrictions. The collective-lift stick provided precise glide slope tracking capability. The pilot preferred a deck-parallel attitude for which he used powered lift to control glide slope and pitch attitude to keep the angle of attack near zero. Workload was reduced when the deceleration schedule was delayed until the aircraft was well established on the glide slope, since thrust vector changes induced flight path disturbances.

  8. Overview of Fundamental High-Lift Research for Transport Aircraft at NASA

    Science.gov (United States)

    Leavitt, L. D.; Washburn, A. E.; Wahls, R. A.

    2007-01-01

    NASA has had a long history in fundamental and applied high lift research. Current programs provide a focus on the validation of technologies and tools that will enable extremely short take off and landing coupled with efficient cruise performance, simple flaps with flow control for improved effectiveness, circulation control wing concepts, some exploration into new aircraft concepts, and partnership with Air Force Research Lab in mobility. Transport high-lift development testing will shift more toward mid and high Rn facilities at least until the question: "How much Rn is required" is answered. This viewgraph presentation provides an overview of High-Lift research at NASA.

  9. Flight evaluation of configuration management system concepts during transition to the landing approach for a powered-lift STOL aircraft

    Science.gov (United States)

    Franklin, J. A.; Innis, R. C.

    1980-01-01

    Flight experiments were conducted to evaluate two control concepts for configuration management during the transition to landing approach for a powered-lift STOL aircraft. NASA Ames' augmentor wing research aircraft was used in the program. Transitions from nominal level-flight configurations at terminal area pattern speeds were conducted along straight and curved descending flightpaths. Stabilization and command augmentation for attitude and airspeed control were used in conjunction with a three-cue flight director that presented commands for pitch, roll, and throttle controls. A prototype microwave system provided landing guidance. Results of these flight experiments indicate that these configuration management concepts permit the successful performance of transitions and approaches along curved paths by powered-lift STOL aircraft. Flight director guidance was essential to accomplish the task.

  10. 32 CFR 256.6 - Runway classification by aircraft type.

    Science.gov (United States)

    2010-07-01

    ... 32 National Defense 2 2010-07-01 2010-07-01 false Runway classification by aircraft type. 256.6 Section 256.6 National Defense Department of Defense (Continued) OFFICE OF THE SECRETARY OF DEFENSE (CONTINUED) MISCELLANEOUS AIR INSTALLATIONS COMPATIBLE USE ZONES § 256.6 Runway classification by...

  11. A Mission-Adaptive Variable Camber Flap Control System to Optimize High Lift and Cruise Lift-to-Drag Ratios of Future N+3 Transport Aircraft

    Science.gov (United States)

    Urnes, James, Sr.; Nguyen, Nhan; Ippolito, Corey; Totah, Joseph; Trinh, Khanh; Ting, Eric

    2013-01-01

    Boeing and NASA are conducting a joint study program to design a wing flap system that will provide mission-adaptive lift and drag performance for future transport aircraft having light-weight, flexible wings. This Variable Camber Continuous Trailing Edge Flap (VCCTEF) system offers a lighter-weight lift control system having two performance objectives: (1) an efficient high lift capability for take-off and landing, and (2) reduction in cruise drag through control of the twist shape of the flexible wing. This control system during cruise will command varying flap settings along the span of the wing in order to establish an optimum wing twist for the current gross weight and cruise flight condition, and continue to change the wing twist as the aircraft changes gross weight and cruise conditions for each mission segment. Design weight of the flap control system is being minimized through use of light-weight shape memory alloy (SMA) actuation augmented with electric actuators. The VCCTEF program is developing better lift and drag performance of flexible wing transports with the further benefits of lighter-weight actuation and less drag using the variable camber shape of the flap.

  12. Application of powered-lift concepts for improved cruise efficiency of long-range aircraft

    Science.gov (United States)

    Coe, P. L., Jr.; Fournier, P. G.

    1976-01-01

    Results of studies conducted to explore the use of powered lift concepts for improved low speed performance of long range subsonic and supersonic cruise vehicles are summarized. It is indicated that powered lift can provide significant improvements in low speed performance, as well as substantial increases in cruise efficiency and range for both subsonic and supersonic cruise configurations.

  13. Aerodynamic Aspects of the Longitudinal Motion of a High-Lift Aircraft Configuration with Circulation Control

    OpenAIRE

    Keller, Dennis; Rudnik, Ralf

    2013-01-01

    The aim of sub-project C1 of the Collaborative Research Center/Sonderforschungsbereich 880 (SFB 880) is to investigate numerically the flight mechanical characteristics of an aircraft with circulation controlled high-lift devices from an aerodynamic point of view. This paper summarizes the most important aspects of the work done so far. It begins with a basic analysis of the impact of varying blowing coefficients on the aircraft performance based on the wing-body configuration. Furthermore, an o...

  14. Aerodynamics of the Wing/Fuselage Junction at an Transport Aircraft in High-lift Configuration.

    OpenAIRE

    Melber-Wilkending, Stefan

    2008-01-01

    This paper presents the numerical simulation (DLR TAU-code) and the analysis of viscous high-lift flow around a complex wing/body configuration (DLR ALVAST) in landing configuration. The investigations aim for a better understanding of the aerodynamics at the wing root and the lift breakdown for such a configuration.

  15. Diagnosis of Wing Icing Through Lift and Drag Coefficient Change Detection for Small Unmanned Aircraft

    DEFF Research Database (Denmark)

    Sørensen, Kim Lynge; Blanke, Mogens; Johansen, Tor Arne

    2015-01-01

    This paper address the issue of structural change, caused by ice accretion, on UAVs by utilising a Neyman Pearson (NP) based statistical change detection approach, for the identification of structural changes of fixed wing UAV airfoils. A structural analysis is performed on the nonlinear aircraft...

  16. A contrarotative aircraft lifting concept for a future Titan mission

    Science.gov (United States)

    Duquesnay, P.; Coustenis, A.; Lebreton, J.-P.; Tavel, J.

    2008-09-01

    Titan has a thick and cold atmosphere (surface pressure 1.5 bar and surface temperature 94 K) and the surface gravity is about 1/7 of Earth's. Surface wind velocities are low. These unique characteristics make Titan's atmosphere an ideal place for an helicopter type of aircraft with vertical lift capability. Here we present a conceptual idea of a Titan helicopter designed as a student project. Two cases have been considered: a 100-kg helicopter and a 2-kg one. The concept is based on a contra-rotating double rotor. The device would be powered by a combination of rechargeable batteries and a low-power radioisotope source. The double rotor and the body of the helicopter would be protected by a mesh structure. It would carry a science payload at its base that would allow surface sampling and analysis each time it would land. During landing, it would also recharge its batteries to allow flying to the next stop. The concept has been inspired by studying modelaircraft- making devices. Various concepts developed for industrial and military applications have also been a source of inspiration. The following web sites were consulted: • www.onera.fr/conferences/drones • www.aurora.aero • www.sikorsky.com/sik/index.asp • www.microdrones.com The poster will present a preliminary design of the device. Its capability to contribute to the exploration of Titan's surface will be illustrated.

  17. A novel hovering type of fixed wing aircraft with stealth capability

    Directory of Open Access Journals (Sweden)

    Valeriu DRĂGAN

    2010-12-01

    Full Text Available The tactical need for fixed wing aircraft with hovering capably has long been recognized bythe military for two reasons: increased safety when landing on aircraft carriers and higher velocitiesthat the ones obtainable with rotary wing aircraft.Thus far, the only concept governing the field of vertical flight was to use thrust either from a liftfan-F35, puffer ducts –Harrier or smaller jet engines-D0 31 or Yak-141, i.e. direct lift thrust.In this paper we will look at the prospect of using a combination of the Coanda effect with theVenturi effect to generate lift by so- called “supercirculation”. This novel approach can yield manyadvantages to conventional vertical lifting by providing a more stable platform and requiring lowerpower settings – and thus lower fuel consumption.The aircraft has a fixed, negatively sweped wing that uses circulation control to achieve lift atzero air speed. The fluid used for supercirculation will come from the fan thrust reversers – which, ifcorrectly managed, can give a sufficient flow for lifting the craft and also a negative thrust componentto compensate for the positive thrust of the primary flow (not diverted.

  18. Unsteady features of jets in lift and cruise modes for VTOL aircraft

    Science.gov (United States)

    Kibens, V.; Saripalli, K. R.; Wlezien, R. W.; Kegelman, J. T.

    1988-01-01

    Experiments were performed to simulate jet plume effects associated with VTOL aircraft in takeoff and cruise modes. A water facility was used to investigate the influence of inclination angle and separation distance on the three-dimensional fountain flowfield generated by two impinging jets operating at a jet Reynolds number of 250,000. Substantial differences in the flow features were observed for different spacings between the jets. Plume effects in cruise mode were simulated by a supersonic unheated jet parallel to a wall. Variation of the distance between the wall and the edge of the plume is shown to have a major controlling effect on the supersonic screech instability.

  19. Project of service lift

    OpenAIRE

    Nguyen, Huy Long

    2009-01-01

    This diploma thesis deal with project of service lift. The service lift is drive by special mechanism using thrust chain. The chain is led from chain accumulator over sprocket gear to vertical guiding groove. Lift car is connected to the end of chain. There are designed and described the most important constructional unit of service lift in this thesis. But the most attention is pay to drive, including break system and chain accumulator. The drive is consist of electric motor, clutch, break, ...

  20. Annoyance and acceptability judgements of noise produced by three types of aircraft by residents living near JFK Airport

    Science.gov (United States)

    Borsky, P. N.

    1974-01-01

    A random sample of selected communities near JFK Airport were interviewed. Subsamples, with differing feelings of fear of aircraft crashes and different locations of residence were invited to participate in a laboratory experiment. The subjects were exposed to tape recordings of simulated flyovers of aircraft in approach and departure operations at nominal distances from the airport. The subjects judged the extent of noise annoyance and acceptability of the aircraft noises. Results indicate that level of noise is most significant in affecting annoyance judgements. Subjects with feelings of high fear report significantly more annoyance and less acceptability of aircraft noise than subjects with feelings of low fear.

  1. Investigations of hydraulic operating conditions of air lift pump with three types of air-water mixers

    Directory of Open Access Journals (Sweden)

    Kalenik Marek

    2015-03-01

    Full Text Available Investigations of hydraulic operating conditions of air lift pump with three types of air-water mixers. The paper presents the analysis of results of the investigations concerning the influence of various constructive solutions of the air-water mixers on hydraulic operating conditions of the air lift pump. The scope of the investigations encompassed the determination of characteristics of delivery head and delivery rate for three types of air-water mixers applied in the constructed air lift pump. Using the obtained results, the efficiency of the three types of air-water mixers applied in this air lift pump was determined. The analysis was carried out and there was checked whether the improved analytical Stenning-Martin model can be used to design air lift pumps with the air-water mixers of these types. The highest capacity in the water transport was reached by the air lift pump with the 1st type air-water mixer, the lowest one – with the 3rd type air-water mixer. The water flow in the air lift pump increases along with the rise in the air flow. The lower are the hydraulic losses generated during flow of the air flux by the air-water mixer, the higher is the air lift pump capacity. Along with the rise in the water delivery head, the capacity of the air lift pump decreases. The highest efficiency is reached by the air lift pump with the 1st type air-water mixer, the lowest – with the 3st type air-water mixer. The efficiency of the air lift pump for the three investigated types of air-water mixers decreases along with the rise in air flow rate and water delivery head. The values of submergence ratio (h/L of the delivery pipe, calculated with the use of the improved analytical Stenning-Martin model, coincide quite well with the values of h/L determined from the measurements.

  2. Design of lift positional table

    OpenAIRE

    Bartel, Jindřich

    2015-01-01

    This bachelor´s thesis describes the design of a lift positional table for overcome the height difference between the two roller tracks. Weight of the load is 550 kg and height difference of roller tracks is 2000 mm. The aim is to suggest the type of power lifting, power lifting functional calculation, functional calculation of the driver tray pallets and determining the main dimensions of the lifting table. The Appendix contains technical drawings of the lifting table and the table frame.

  3. Investigations of hydraulic operating conditions of air lift pump with three types of air-water mixers

    OpenAIRE

    Kalenik Marek

    2015-01-01

    Investigations of hydraulic operating conditions of air lift pump with three types of air-water mixers. The paper presents the analysis of results of the investigations concerning the influence of various constructive solutions of the air-water mixers on hydraulic operating conditions of the air lift pump. The scope of the investigations encompassed the determination of characteristics of delivery head and delivery rate for three types of air-water mixers applied in the constructed air lift p...

  4. CO2 Fixation, Lipid Production, and Power Generation by a Novel Air-Lift-Type Microbial Carbon Capture Cell System.

    Science.gov (United States)

    Hu, Xia; Liu, Baojun; Zhou, Jiti; Jin, Ruofei; Qiao, Sen; Liu, Guangfei

    2015-09-01

    An air-lift-type microbial carbon capture cell (ALMCC) was constructed for the first time by using an air-lift-type photobioreactor as the cathode chamber. The performance of ALMCC in fixing high concentration of CO2, producing energy (power and biodiesel), and removing COD together with nutrients was investigated and compared with the traditional microbial carbon capture cell (MCC) and air-lift-type photobioreactor (ALP). The ALMCC system produced a maximum power density of 972.5 mW·m(-3) and removed 86.69% of COD, 70.52% of ammonium nitrogen, and 69.24% of phosphorus, which indicate that ALMCC performed better than MCC in terms of power generation and wastewater treatment efficiency. Besides, ALMCC demonstrated 9.98- and 1.88-fold increases over ALP and MCC in the CO2 fixation rate, respectively. Similarly, the ALMCC significantly presented a higher lipid productivity compared to those control reactors. More importantly, the preliminary analysis of energy balance suggested that the net energy of the ALMCC system was significantly superior to other systems and could theoretically produce enough energy to cover its consumption. In this work, the established ALMCC system simultaneously achieved the high level of CO2 fixation, energy recycle, and municipal wastewater treatment effectively and efficiently. PMID:26270956

  5. 螺旋桨飞机升力失速特性研究%Investigation on lift stall characteristics of propeller aircraft

    Institute of Scientific and Technical Information of China (English)

    刘毅; 赵晓霞; 欧阳绍修

    2015-01-01

    飞机的最大升力系数 CLmax 直接影响翼载的选取,进而影响飞机的重量和经济性。螺旋桨飞机在带动力条件下 CLmax 随滑流强度增加而提高,但按照常规理论采用无动力 CLmax 数据选取的翼载偏小偏保守,没有充分发掘飞机的性能潜力。结合适航规定以及某四发螺旋桨飞机飞行实际情况,提出了一种基于发动机慢车状态确定 CLmax的概念,并将飞机带动力 CLmax 分解为无动力 CLmax 、螺旋桨拉力、螺旋桨法向力、滑流增升效应等4部分贡献,通过无动力和多天平带动力风洞实验完成了上述分量的模拟、测量和修正。计算表明某四发螺旋桨飞机在发动机慢车失速试飞条件下的滑流强度约为0.1,螺旋桨系统的动力增升作用使不同襟翼构型的 CLmax 增加8%~9%。该方法获得的 CLmax 与飞机试飞结果较为吻合,充分挖掘了飞机的低速性能潜力,并为同类螺旋桨飞机设计提供了一定的参考。%The maximum lift coefficient CLmax is directly connected to the selection of wing loading,which further affects aircraft’s mass and economy.CLmax of propeller aircraft is improved with increased slipstream intensity at powered condition,however the conventional theory trends to some conservative and smaller power-off value,hence does not utilize the full potential per-formance of aircraft.Combining the airworthiness regulations and the actual flight condition of an aircraft with four turbo-prop engines,a new concept is proposed to find the optimal CLmax based on engine standby condition.The power-on CLmax is separated into four parts:power-off CLmax , propeller thrust component,propeller normal force and lift due to slipstream,which are simula-ted,measured and corrected by power-off and multi-balance power-on wind tunnel tests.The calculation shows that the propeller aircraft with four engines has slipstream intensity in the order of 0.1 at stall flight

  6. Mathematical model for lift/cruise fan V/STOL aircraft simulator programming data

    Science.gov (United States)

    Bland, M. P.; Fajfar, B.; Konsewicz, R. K.

    1976-01-01

    Simulation data are reported for the purpose of programming the flight simulator for advanced aircraft for tests of the lift/cruise fan V/STOL Research Technology Aircraft. These simulation tests are to provide insight into problem areas which are encountered in operational use of the aircraft. A mathematical model is defined in sufficient detail to represent all the necessary pertinent aircraft and system characteristics. The model includes the capability to simulate two basic versions of an aircraft propulsion system: (1) the gas coupled configuration which uses insulated air ducts to transmit power between gas generators and fans in the form of high energy engine exhaust and (2) the mechanically coupled power system which uses shafts, clutches, and gearboxes for power transmittal. Both configurations are modeled such that the simulation can include vertical as well as rolling takeoff and landing, hover, powered lift flight, aerodynamic flight, and the transition between powered lift and aerodynamic flight.

  7. by Lifting Line Method

    Directory of Open Access Journals (Sweden)

    Horia Dumitrescu

    1998-01-01

    Full Text Available The vortex model of propellers is modified and applied to the high-speed horizontal axis turbines. The turbine blades are replaced by lifting lines and trailing vortices which shed along the blade span. The model is not a free wake model, but it is still a nonlinear one which should be solved iteratively. In addition to the regular case where the trailing vortices are constrained to distribute along a helical surface, another version, where each trailing vortex sheding from the blade grows as a free helical vortex line, is also included. Performance parameters are calculated by application of the Biot-Savart law along with the Kutta-Joukowski theorem. Predictions are, shown to compare favorably with existing numerical data from more involved free wake methods, but require less computational effort. Thereby, the present method may be a very useful tool for calculating the aerodynamic loads on horizontal-axis wind turbine blades.

  8. Micropatterning of nanoparticle films by bilayer lift-off

    International Nuclear Information System (INIS)

    Nanostructured films are deposited by a new technique that matches supersonic cluster beam deposition with flame spray pyrolysis production of nanoparticles (FlameBeam). These films are structured with micrometric lateral resolution, applying a lift-off method by pre-structuring a photoresist-PMMA bilayer with a suitable ‘mushroom-like’ cross-section, depositing a nanostructured silver film on top and lifting off the bilayer in an aqueous solution. Optical inspection revealed that line-shaped microstructures, having a minimal width of up to 3 µm, can be successfully obtained. The nanostructured films have survived the aqueous treatment, as demonstrated by electron microscopy imaging and electrical characterization through 4-point measurement method (Van-der-Pauw). The latter has been possible through sputtered gold pads that were realized on the substrate prior to the deposition of the photoresist and of the nanostructured film. These results disclose novel possibilities in the fine patterning of FlameBeam-deposited films and their integration into microelectromechanical systems devices in general. (paper)

  9. An experimental study of a jet issuing from a lifting wing. [vertical-horizontal flight transitions in VTOL aircraft

    Science.gov (United States)

    Mcmahon, H. M.; Antani, D. L.

    1979-01-01

    An experimental program was conducted to determine the behavior of a round turbulent jet issuing from a lifting two-dimensional wing in crossflow. The jet was located at 65% wing chord on an NACA 0021 airfoil fitted with a 30% chord NACA 4415 flap. The flowfield associated with the jet was surveyed extensively with directional pressure probes to determine local velocity vectors and pressures for three different values of lift coefficient at jet effective velocity ratios (square root of the ratio of the jet dynamic pressure to the freestream dynamic pressure) of 4, 6, and 8. Data describing the jet centerline and the path of the contrarotating vortices accompanying the deflected jet are presented and compared with similar data for a round jet issuing from a large flat plate. The spacing and strength of the vortices are calculated using a simple vortex model previously proposed for the flat plate case. The results show that the penetration of the jet and the vortices increases significantly with increasing lift for the range of test parameters covered in the study. The calculated vortex spacing and strength also show an increase with lift.

  10. Performance studies on the application of four-engine and two-engine USB propulsive lift to the E-2C aircraft

    Science.gov (United States)

    Riddle, D. W.; Stevens, V. C.

    1986-01-01

    A study has been completed of the performance benefits to be derived from applying advanced upper-surface blowing (USB) propulsive-lift technology to the E-2C aircraft. The results of comparing four-engine with two-engine USB configurations are discussed, and engine sizing and aerodynamic/structural considerations pertaining to the E-2C/USB modification are examined. The effects of the modification on performance are described in detail with regard to takeoff distance and landing distance estimation in free-deck operations, operations using catapult and arresting gear, ceiling and radar surveillance missions, and range and endurance capability.

  11. 14 CFR 60.21 - Interim qualification of FSTDs for new aircraft types or models.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Interim qualification of FSTDs for new aircraft types or models. 60.21 Section 60.21 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION... aircraft, even though the aircraft manufacturer's aircraft data package is preliminary, if the...

  12. Lifting particle coordinate changes of magnetic moment type to Vlasov-Maxwell Hamiltonian dynamics

    International Nuclear Information System (INIS)

    Techniques for coordinate changes that depend on both dependent and independent variables are developed and applied to the Maxwell-Vlasov Hamiltonian theory. Particle coordinate changes with a new velocity variable dependent on the magnetic field, with spatial coordinates unchanged, are lifted to the field theoretic level, by transforming the noncanonical Poisson bracket and Hamiltonian structure of the Vlasov-Maxwell dynamics. Several examples are given including magnetic coordinates, where the velocity is decomposed into components parallel and perpendicular to the local magnetic field, and the case of spherical velocity coordinates. An example of the lifting procedure is performed to obtain a simplified version of gyrokinetics, where the magnetic moment is used as a coordinate and the dynamics is reduced by elimination of the electric field energy in the Hamiltonian.

  13. A novel hovering type of fixed wing aircraft with stealth capability

    OpenAIRE

    Valeriu DRĂGAN

    2010-01-01

    The tactical need for fixed wing aircraft with hovering capably has long been recognized bythe military for two reasons: increased safety when landing on aircraft carriers and higher velocitiesthat the ones obtainable with rotary wing aircraft.Thus far, the only concept governing the field of vertical flight was to use thrust either from a liftfan-F35, puffer ducts –Harrier or smaller jet engines-D0 31 or Yak-141, i.e. direct lift thrust.In this paper we will look at the prospect of using a c...

  14. 升力风扇垂直起降飞机过渡态总体参数分析%Analysis of Conceptual Parameters of Lift-Fan VTOL Aircraft in Transition

    Institute of Scientific and Technical Information of China (English)

    昌敏; 周洲; 郑志成

    2013-01-01

    Lift-fan VTOL aircraft is a special type of fixed wing aircraft , whose three modes are: helicopter-like hover, fixed-wing, and special transition.Among these three modes, aerodynamic lift system and direct lift system share only one engine system.The working conditions of the two lift systems differ apparently .Consequently, the relationships among conceptual parameters of lift -fan VTOL aircraft are different from those of conventional aircraft . On the basis of classical momentum theory , we established a preliminary model for analyzing characteristics of lift , drag and power.Then we assessed the impacts of the conceptual parameters exerted on characteristics of total drag and power consumed.We gave feasible methods for so selecting and weighing the conceptual parameters as to meet the requirements of reducing "surplus power"and saving more fuel during transition for cruising efficiency .The three conclusions in section 4 of the full paper, in our opinion, can provide effective guidance for the preliminary design of lift-fan VTOL aircraft.%  升力风扇垂直起降飞机属于一种特殊的固定翼飞行器,兼有直升机式的悬停状态、固定翼状态,以及特殊的过渡状态。在这三种状态下,两套升力部件(直接升力部件和气动升力部件)只共用一套动力源,使得动力源工作状态差异很大,导致各总体参数之间的匹配关系与常规固定翼飞机甚为不同。为此,基于螺旋桨动量理论推导了升力风扇垂直起降飞机全机升阻、功率特性的估算模型;并针对整个过渡过程,分析了各总体参数对过渡态功率、阻力特性的影响,进而得到各总体参数的合理匹配方法以满足减小"富余功率"和节省过渡阶段的燃油消耗量的设计要求,提高巡航经济性。所研究的成果能为升力风扇垂直起降飞机概念设计提供有效地指导原则。

  15. Testing lifting capacity : Validity of determining effort level by means of observation

    NARCIS (Netherlands)

    Reneman, M.F; Fokkens, A.S.; Dijkstra, P.U.; Geertzen, J.H.B.; Groothoff, J.W.

    2005-01-01

    Study Design. Video observation study. Objectives. To establish the validity of determining effort level by visual observation of a lifting test. Summary of Background Data. Determining effort level during a lifting test is critical for interpretation of test performance, yet the validity of these d

  16. Conceptual design, evaluation and research identification for Remote Augmented Propulsive Lift Systems (RALS) with ejectors for VTOL aircraft

    Science.gov (United States)

    Willis, W. S.; Konarski, M.; Sutherland, M. V.

    1982-01-01

    Ejector concepts for use with a remote augmented lift system (RALS) exhaust nozzle were studied. A number of concepts were considered and three were selected as having the greatest promise of providing the desired aircraft and exhaust gas cooling and lift enhancement. A scale model test program is recommended to explore the effects of the more important parameters on ejector performance.

  17. Aircraft type influence on contrail properties

    Directory of Open Access Journals (Sweden)

    P. Jeßberger

    2013-05-01

    Full Text Available The investigation of the impact of aircraft parameters on contrail properties helps to better understand the climate impact from aviation. Yet, in observations, it is a challenge to separate aircraft and meteorological influences on contrail formation. During the CONCERT campaign in November 2008, contrails from 3 Airbus passenger aircraft of type A319-111, A340-311 and A380-841 were probed at cruise under similar meteorological conditions with in-situ instruments on board the DLR research aircraft Falcon. Within the 2 min old contrails detected near ice saturation, we find similar effective diameters Deff (5.2–5.9 μm, but differences in particle number densities nice (162–235 cm−3 and in vertical contrail extensions (120–290 m, resulting in large differences in contrail optical depths τ (0.25–0.94. Hence larger aircraft produce optically thicker contrails. Based on the observations, we apply the EULAG-LCM model with explicit ice microphysics and in addition the Contrail and Cirrus Prediction model CoCiP to calculate the aircraft type impact on young contrails under identical meteorological conditions. The observed increase in τ for heavier aircraft is confirmed by the models, yet for generally smaller τ. An aircraft dependence of climate relevant contrail properties persists during contrail lifetime, adding importance to aircraft dependent model initialization. We finally derive an analytical relationship between contrail, aircraft and meteorological parameters. Near ice saturation, contrail width × τ scales linearly with fuel flow rate as confirmed by observations. For higher saturation ratios approximations from theory suggest a non-linear increase in the form (RHI–12/3. Summarized our combined results could help to more accurately assess the climate impact from aviation using an aircraft dependent contrail parameterization.

  18. Aircraft borne combined measurements of the Fukushima radionuclide Xe-133 and fossil fuel combustion generated pollutants in the TIL - Implications for Cyclone induced lift and TIL physical-chemical processes

    Science.gov (United States)

    Arnold, Frank; Schlager, Hans; Simgen, Hardy; Aufmhoff, Heinfried; Baumann, Robert; Lindemann, Sigfried; Rauch, Ludwig; Kaether, Frank; Pirjolla, Liisa; Schumann, Ulrich

    2013-04-01

    The radionuclide Xe-133, released by the March 2011 nuclear disaster at Fukushima/Daiichi (hereafter FD), represents an ideal tracer for atmospheric transport. We report the, to our best knowledge, only aircraft borne measurements of FD Xe-133 in the Tropopause Inversion Layer (TIL), indicating rapid lift of Xe-133 rich planetary boundary layer air to the TIL. On the same research aircraft (FALCON), we have also conducted on-line measurements of fossil fuel combustion generated pollutant gases (SO2, NOx, HNO3,NOy), which were found to have increased concentrations in the TIL. In addition, we have conducted supporting model simulations of transport, chemical processes, and aerosol processes. Our investigations reveal a potentially important influence of East-Asian cyclone induced pollutants transport to the TIL, particularly influencing aerosol formation in the TIL.

  19. Aircraft borne combined measurements of the Fukushima radionuclide Xe-133 and fossil fuel combustion generated pollutants in the TIL - implications for cyclone induced rapid lift and TIL physico-chemical processes

    International Nuclear Information System (INIS)

    The radionuclide Xe-133, released by the March 2011 nuclear disaster at Fukushima/Daiichi (hereafter FD), represents an ideal tracer for atmospheric transport. We report the, to our best knowledge, only aircraft borne measurements of FD Xe-133 in the Tropopause Inversion Layer (TIL), indicating rapid lift of polluted planetary boundary layer air to the TIL. On the same research aircraft (FALCON), we have also conducted on-line measurements of fossil fuel combustion generated pollutant gases (SO2 and other species), which had increased concentrations in the TIL. In addition, we have conducted supporting model simulations of transport, chemical processes, and aerosol processes. Our investigations reveal a potentially important impact of East-Asian cyclone induced pollutants transport to the TIL. This impact includes particularly aerosol formation.

  20. Effect of conditions of air-lift type reactor work on cadmium adsorption

    Energy Technology Data Exchange (ETDEWEB)

    Filipkowska, Urszula; Szymczyk, Paula Szymczyk; Kuczajowska-Zadrozna, Malgorzata; Joezwiak, Tomasz [University of Warmia and Mazury in Olsztyn, Warszawska (Poland)

    2015-10-15

    We investigated cadmium sorption by activated sludge immobilized in 1.5% sodium alginate with 0.5% polyvinyl alcohol. Experiments were conducted in an air-lift type reactor at the constant concentration of biosorbent reaching 5 d.m./dm{sup 3}, at three flow rates: 0.1, 0.25 and 0.5 V/h, and at three concentrations of the inflowing cadmium solution: 10, 25 and 50mg/dm{sup 3}. Analyses determined adsorption capacity of activated sludge immobilized in alginate as well as reactor's work time depending on flow rate and initial concentration of the solution. Results achieved were described with the use of Thomas model. The highest adsorption capacity of the sorbent (determined from the Thomas model), i.e., 200.2mg/g d.m. was obtained at inflowing solution concentration of 50mg/dm{sup 3} and flow rate of 0.1V/h, whereas the lowest one reached 53.69mg/g d.m. at the respective values of 10mg/dm{sup 3} and 0.1 V/h. Analyses were also carried out to determine the degree of biosorbent adsorption capacity utilization at the assumed effectiveness of cadmium removal - at the breakthrough point (C=0.05*C{sub 0}) and at adsorption capacity depletion point (C−0.9*C0). The study demonstrated that the effectiveness of adsorption capacity utilization was influenced by both the concentration and flow rate of the inflowing solution. The highest degree of sorbent capacity utilization was noted at inflowing solution concentration of 50mg/dm{sup 3} and flow rate of 0.1 V/h, whereas the lowest one at the respective values of 10mg/dm{sup 3} and 0.1 V/h. The course of the process under dynamic conditions was evaluated using coefficients of tangent inclination - a, at point C/C{sub 0}=1/2. A distinct tendency was demonstrated in changes of tangent slope a as affected by the initial concentration of cadmium and flow rate of the solution. The highest values of a coefficient were achieved at the flow rate of 0.1 V/h and initial cadmium concentration of 50mg/dm{sup 3}.

  1. Computation of load functions for different types of aircraft

    International Nuclear Information System (INIS)

    In the presentation the influence of different parameters on the Ft-function were shown. The increase of the impact velocity shows for all aircraft a higher maximal load value and a reduced impact time. Due to the structural setup of the aircraft's the intensity is of these effects different. Comparing the Ft-function of A320, A340 and A380 for an impact velocity of 100 and 175 m/s no constant relation between them can be determined. • The variation of the flight direction with respect to the vertical axis shows a great influence on the Ft-function. A approximation by the cosine is especially for bigger rotations not correct. The influence of the rotation about the horizontal axis can be neglected. Finally the SPH-method was applied for the modelling of the fuel. The comparison to the discrete modelling approach was carried out for the Phantom F4. Thereby no big influence on the Ft-function is observed. For the evaluation of this modelling approach on the local damage the loaded area must be determined in further investigations

  2. Analysis of data from water lift powered by solar energy pump

    Energy Technology Data Exchange (ETDEWEB)

    Oyama, Paulo Takashi [Universidade Estadual do Oeste do Parana (UNIOESTE), Cascavel, PR (Brazil); Ricieri, Reinaldo Prandini [Universidade Estadual do Oeste do Parana (UNIOESTE), Cascavel, PR (Brazil). Dept. de Engenharia Agricola], E-mail: ricieri@unioeste.br; Halmeman, Maria Cristina Rodrigues [Universidade Estadual Paulista (UNESP), Botucatu, SP (Brazil); Gnoatto, Estor; Kavanagh; Brenneisen, Paulo Job [Universidade Tecnologica Federal do Parana (UTFPR), Medianeira, PR (Brazil)], Emails: gnoatto@utfpr.edu.br, kavanagh@utfpr.edu.br, brenneisen@utfpr.edu.br

    2008-07-01

    Due to the high costs to install electricity in remote locations, away from the regular urban electrical installations, photovoltaic solar energy has ample application in public illumination, water pumping, health services offices, etc. With the purpose to contribute to a better use of this kind of energy, this project aimed in analyzing the outflow and efficiency of a motor pump powered by photovoltaic panels, the irradiation necessary to activate it for water lift, collecting data at every 6- meter height, ranging from 6,2 to 18,2 meters. This study is part of a development project of the Universidade Tecnologica Federal do Parana (UTFPR), by making use of photovoltaic panels, motor pump, pyranometers, thermocouple type K, pressure transducer and outflow transducer. The data show a maximum average outflow of 584,299 Lh{sup -1} and maximum efficiency of 23,338% for a lift of 18,2 m. There is also the need of irradiation for the activation of the motor pump proportional to the height of the lift, in a polynomial dependence of the third order. (author)

  3. Control of a swept wing tailless aircraft through wing morphing

    Science.gov (United States)

    Guiler, Richard W.

    Inspired by flight in nature, work done by Lippisch, the Hortens, and Northrop offered insight to achieving the efficiency of bird flight with swept-wing tailless aircraft. Tailless designs must incorporate aerodynamic compromises for control, which have inhibited potential advantages. A morphing mechanism, capable of changing the twist of wing and that can also provide pitch, roll and yaw control for a tailless swept wing aircraft is the first step to a series of morphing techniques, which will lead to more fluid, bird-like flight. This research focuses on investigating the design of a morphing wing to improve the flight characteristics of swept wing Horten type tailless aircraft. Free flight demonstrators, wind tunnel flow visualization, wind-tunnel force and moment data along with CFD studies have been used to evaluate the stability, control and efficiency of a morphing swept wing tailless aircraft. A wing morphing mechanism for the control of a swept wing tailless aircraft has been developed. This new control technique was experimentally and numerically compared to an existing elevon equipped tailless aircraft and has shown the potential for significant improvement in efficiency. The feasibility of this mechanism was also validated through flight testing of a flight weight version. In the process of comparing the Horten type elevon equipped aircraft and the morphing model, formal wind tunnel verification of wingtip induced thrust, found in Horten (Bell Shaped Lift distribution) type swept wing tailless aircraft was documented. A more complete physical understanding of the highly complex flow generated in the control region of the morphing tailless aircraft has been developed. CFD models indicate the possibility of the presence of a Leading Edge Vortex (LEV) on the control section morphing wing when the tip is twisted between +3.5 degrees and +7 degrees. The presence of this LEV causes a reduction of drag while lift is increased. Similar LEVs have been

  4. 14 CFR 21.27 - Issue of type certificate: surplus aircraft of the Armed Forces.

    Science.gov (United States)

    2010-01-01

    ... paragraph (f) and adding in its place the words “14 CFR”, effective Apr. 14, 2010. ... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Issue of type certificate: surplus aircraft..., DEPARTMENT OF TRANSPORTATION AIRCRAFT CERTIFICATION PROCEDURES FOR PRODUCTS AND PARTS Type Certificates §...

  5. Normalized lift: an energy interpretation of the lift coefficient simplifies comparisons of the lifting ability of rotating and flapping surfaces.

    Directory of Open Access Journals (Sweden)

    Phillip Burgers

    Full Text Available For a century, researchers have used the standard lift coefficient C(L to evaluate the lift, L, generated by fixed wings over an area S against dynamic pressure, ½ρv(2, where v is the effective velocity of the wing. Because the lift coefficient was developed initially for fixed wings in steady flow, its application to other lifting systems requires either simplifying assumptions or complex adjustments as is the case for flapping wings and rotating cylinders.This paper interprets the standard lift coefficient of a fixed wing slightly differently, as the work exerted by the wing on the surrounding flow field (L/ρ·S, compared against the total kinetic energy required for generating said lift, ½v(2. This reinterpreted coefficient, the normalized lift, is derived from the work-energy theorem and compares the lifting capabilities of dissimilar lift systems on a similar energy footing. The normalized lift is the same as the standard lift coefficient for fixed wings, but differs for wings with more complex motions; it also accounts for such complex motions explicitly and without complex modifications or adjustments. We compare the normalized lift with the previously-reported values of lift coefficient for a rotating cylinder in Magnus effect, a bat during hovering and forward flight, and a hovering dipteran.The maximum standard lift coefficient for a fixed wing without flaps in steady flow is around 1.5, yet for a rotating cylinder it may exceed 9.0, a value that implies that a rotating cylinder generates nearly 6 times the maximum lift of a wing. The maximum normalized lift for a rotating cylinder is 1.5. We suggest that the normalized lift can be used to evaluate propellers, rotors, flapping wings of animals and micro air vehicles, and underwater thrust-generating fins in the same way the lift coefficient is currently used to evaluate fixed wings.

  6. Surface properties of GaN fabricated by laser lift-off and ICP etching

    International Nuclear Information System (INIS)

    In this report, we describe the surface properties of a controlled thickness GaN microcavity which incorporates Zr2O3/SiO2 DBR stacks for both the bottom and the top mirrors. The GaN microcavities were fabricated using laser lift-off and inductively coupled plasma etching. We also compared etch rates, surface composition, and surface roughness between grown GaN and GaN fabricated by laser lift-off and ICP etching

  7. Investigation of Maximum Blade Loading Capability of Lift-Offset Rotors

    Science.gov (United States)

    Yeo, Hyeonsoo; Johnson, Wayne

    2013-01-01

    Maximum blade loading capability of a coaxial, lift-offset rotor is investigated using a rotorcraft configuration designed in the context of short-haul, medium-size civil and military missions. The aircraft was sized for a 6600-lb payload and a range of 300 nm. The rotor planform and twist were optimized for hover and cruise performance. For the present rotor performance calculations, the collective pitch angle is progressively increased up to and through stall with the shaft angle set to zero. The effects of lift offset on rotor lift, power, controls, and blade airloads and structural loads are examined. The maximum lift capability of the coaxial rotor increases as lift offset increases and extends well beyond the McHugh lift boundary as the lift potential of the advancing blades are fully realized. A parametric study is conducted to examine the differences between the present coaxial rotor and the McHugh rotor in terms of maximum lift capabilities and to identify important design parameters that define the maximum lift capability of the rotor. The effects of lift offset on rotor blade airloads and structural loads are also investigated. Flap bending moment increases substantially as lift offset increases to carry the hub roll moment even at low collective values. The magnitude of flap bending moment is dictated by the lift-offset value (hub roll moment) but is less sensitive to collective and speed.

  8. Normalized Lift: An Energy Interpretation of the Lift Coefficient Simplifies Comparisons of the Lifting Ability of Rotating and Flapping Surfaces

    OpenAIRE

    Burgers, Phillip; Alexander, David E.

    2012-01-01

    For a century, researchers have used the standard lift coefficient CL to evaluate the lift, L, generated by fixed wings over an area S against dynamic pressure, ½ρv 2, where v is the effective velocity of the wing. Because the lift coefficient was developed initially for fixed wings in steady flow, its application to other lifting systems requires either simplifying assumptions or complex adjustments as is the case for flapping wings and rotating cylinders. This paper interprets the standard ...

  9. Planning of aircraft departure trajectories by using fuzzy logic and lexocographic optimization

    OpenAIRE

    Prats Menéndez, Xavier; Quevedo Casín, Joseba Jokin; Puig Cayuela, Vicenç; Nejjari Akhi-Elarab, Fatiha

    2007-01-01

    In this paper a strategy for planning aircraft departure trajectories for a given airport is presented. Noise annoyance produced by overflying aircraft is modelled by using fuzzy logic in function of the received noise level during the trajectory, the type and specific sensibility of the areas being overflyed and the time of the day when the aircraft departure takes place. Hence, an annoyance figure is obtained at different locations in the vicinity of the airport in function of a given traje...

  10. Dynamic scheduling of aircraft high-lift devices and landing gear deployment for optimized continuous descent operations with required times of arrival

    OpenAIRE

    Duran Perez, David

    2015-01-01

    This report presents a novel implementation of Time and Energy Managed Operations (TEMO) in which the dynamic scheduling of high-lift devices (flaps/slats) and landing gear deployment is used in order to reduce fuel consumption and speed brakes usage while achieving accurate Required Time of Arrivals (RTAs) at the landing runway threshold. Two solutions are proposed: one resolving time and energy deviations with strategic re-planning of the high-lift devices and/or gear deployment; and anothe...

  11. Analytical prediction of the unsteady lift on a rotor caused by downstream struts

    Science.gov (United States)

    Taylor, A. C., III; Ng, W. F.

    1987-01-01

    A two-dimensional, inviscid, incompressible procedure is presented for predicting the unsteady lift on turbomachinery blades caused by the upstream potential disturbance of downstream flow obstructions. Using the Douglas-Neumann singularity superposition potential flow computer program to model the downstream flow obstructions, classical equations of thin airfoil theory are then employed, to compute the unsteady lift on the upstream rotor blades. The method is applied to a particular geometry which consists of a rotor, a downstream stator, and downstream struts which support the engine casing. Very good agreement between the Douglas-Neumann program and experimental measurements was obtained for the downstream stator-strut flow field. The calculations for the unsteady lift due to the struts were in good agreement with the experiments in showing that the unsteady lift due to the struts decays exponentially with increased axial separation of the rotor and the struts. An application of the method showed that for a given axial spacing between the rotor and the strut, strut-induced unsteady lift is a very weak function of the axial or circumferential position of the stator.

  12. IDENTIFICATION OF TYPES AND MODELS OF AIRCRAFT USING ASC-ANALYSIS OF THEIR SILHOUETTES (CONTOURS (GENERALIZATION, ABSTRACTION, CLASSIFICATION AND IDENTIFICATION

    Directory of Open Access Journals (Sweden)

    Lutsenko Y. V.

    2015-12-01

    Full Text Available The article discusses the application of automated system-cognitive analysis (ASC-analysis, its mathematical model which is system theory of information and its software tool, which is intellectual system called "Eidos" for solving problems related to identification of types and models of aircraft by their silhouettes on the ground, to be more precise, their external contours: 1 digitization of scanned images of aircraft and creation of their mathematical models; 2 formation of mathematical models of specific aircraft with the use of the information theory; 3 modeling of the generalized images of various aircraft types and models and their graphic visualization; 4 comparing an image of a particular plane with generalized images of various aircraft types and models, and quantifying the degree of similarities and differences between them, i.e., the identification of the type and model of airplane by its silhouette (contour on the ground; 5 quantification of the similarities and differences of the generalized images of the planes with each other, i.e., clusterconstructive analysis of generalized images of various aircraft types and models. The article gives a new approach to digitizing images of aircraft, based on the use of the polar coordinate system, the center of gravity of the image and its external contour. Before digitizing images, we may use their transformation, standardizing the position of the images, their sizes (resolution, distance and the angle of rotation (angle in three dimensions. Therefore, the results of digitization and ASC-analysis of the images can be invariant (independent relative to their position, dimensions and turns. The shape of the contour of a particular aircraft is considered as a noise information on the type and model of aircraft, including information about the true shape of the aircraft type and its model (clean signal and noise, which distort the real shape, due to noise influences, both of the means of

  13. Generalised Eisenhart lift of the Toda chain

    CERN Document Server

    Cariglia, Marco

    2013-01-01

    The Toda chain of nearest neighbour interacting particles on a line can be described both in terms of geodesic motion on a manifold with one extra dimension, the Eisenhart lift, or in terms of geodesic motion in a symmetric space with several extra dimensions. We examine the relationship between these two realisations and discover that the symmetric space is a generalised, multi-particle Eisenhart lift of the original problem, that reduces to the standard Eisenhart lift. Such generalised Eisenhart lift acts as an inverse Kaluza-Klein reduction, promoting coupling constants to momenta in higher dimension. In particular, isometries of the generalised lift metric correspond to energy preserving transformations that mix coordinates and coupling constants. A by-product of the analysis is that the lift of the Toda Lax pair can be used to construct higher rank Killing tensors for both the standard and generalised lift metrics.

  14. Generalised Eisenhart lift of the Toda chain

    International Nuclear Information System (INIS)

    The Toda chain of nearest neighbour interacting particles on a line can be described both in terms of geodesic motion on a manifold with one extra dimension, the Eisenhart lift, or in terms of geodesic motion in a symmetric space with several extra dimensions. We examine the relationship between these two realisations and discover that the symmetric space is a generalised, multi-particle Eisenhart lift of the original problem that reduces to the standard Eisenhart lift. Such generalised Eisenhart lift acts as an inverse Kaluza-Klein reduction, promoting coupling constants to momenta in higher dimension. In particular, isometries of the generalised lift metric correspond to energy preserving transformations that mix coordinates and coupling constants. A by-product of the analysis is that the lift of the Toda Lax pair can be used to construct higher rank Killing tensors for both the standard and generalised lift metrics

  15. M2-F1 lifting body aircraft on a flatbed truck

    Science.gov (United States)

    1997-01-01

    After the grounding of the M2-F1 in 1966, it was kept in outside storage on the Dryden complex. After several years, its fabric and plywood structure was damaged by the sun and weather. Restoration of the vehicle began in February 1994 under the leadership of NASA retiree Dick Fischer, with other retirees who had originally worked on the M2-F1's construction and flight research three decades before also participating. The photo shows the now-restored M2-F1 returning to the site of its flight research, now called the Dryden Flight Research Center, on 22 August 1997. The wingless, lifting body aircraft design was initially conceived as a means of landing an aircraft horizontally after atmospheric reentry. The absence of wings would make the extreme heat of re-entry less damaging to the vehicle. In 1962, NASA Flight Research Center (later Dryden Flight Research Center, Edwards, CA) management approved a program to build a lightweight, unpowered lifting body as a prototype to flight test the wingless concept. It would look like a 'flying bathtub,' and was designated the M2-F1, the 'M' referring to 'manned' and 'F' referring to 'flight' version. It featured a plywood shell placed over a tubular steel frame crafted at Dryden. Construction was completed in 1963. The first flight tests of the M2-F1 were over Rogers Dry Lake at the end of a tow rope attached to a hopped-up Pontiac convertible driven at speeds up to about 120 mph. This vehicle needed to be able to tow the M2-F1 on the Rogers Dry Lakebed adjacent to NASA's Flight Research Center (FRC) at a minimum speed of 100 miles per hour. To do that, it had to handle the 400-pound pull of the M2-F1. Walter 'Whitey' Whiteside, who was a retired Air Force maintenance officer working in the FRC's Flight Operations Division, was a dirt-bike rider and hot-rodder. Together with Boyden 'Bud' Bearce in the Procurement and Supply Branch of the FRC, Whitey acquired a Pontiac Catalina convertible with the largest engine available

  16. Musculoskeletal pain among critical-care nurses by availability and use of patient lifting equipment: An analysis of cross-sectional survey data

    OpenAIRE

    Lee, SJ; Faucett, J; Gillen, M; Krause, N.

    2013-01-01

    Background: Patient handling is a major risk factor for musculoskeletal injuries among nurses. Lifting equipment is a main component of safe patient handling programs that aim to prevent musculoskeletal injury. However, the actual levels of lift availability and usage are far from optimal. Objective: To examine the effect of patient lifting equipment on musculoskeletal pain by level of lift availability and lift use among critical-care nurses. Design and participants: A cross-sectional postal...

  17. Friction characteristics of three 30 by 11.5-14.5, type 8, aircraft tires with various tread groove patterns and rubber compounds

    Science.gov (United States)

    Yager, T. J.; Mccarty, J. L.

    1977-01-01

    A test program was conducted to evaluate friction performance and wear characteristics on wet runways of three 30 x 11.5-14.5, type, aircraft tires having two different tread patterns and natural rubber contents. All test tires had the standard three circumferential groove tread, but two had molded transverse grooves which extended from shoulder to shoulder. The tread rubber content of the two tires with transverse grooves differed in that one had a 100 percent natural rubber tread and the other had a rubber tread composition that was 30 percent synthetic and 70 percent natural. The third test tire had the conventional 100 percent natural rubber tread. Results indicate that the differences in tire tread design and rubber composition do not significantly affect braking and cornering friction capability on wet or dry surfaces. Braking performance of the tires decreases with increased speed, with increased yaw angle and, at higher speeds, with increased wetness of the surface.

  18. Research on enhancement of natural circulation capability in lead–bismuth alloy cooled reactor by using gas-lift pump

    International Nuclear Information System (INIS)

    Highlights: • The gas-lift pump has been adopted to enhance the natural circulation capability. • LENAC code is developed in my study. • The calculation results by LENAC code show good agreement with experiment results. • Gas mass flow rate, bubble diameter, rising pipe length are important parameters. -- Abstract: The gas-lift pump has been adopted to enhance the natural circulation capability in the type of lead–bismuth alloy cooled reactors such as Accelerator Driven System (ADS) and Liquid–metal Fast Reactor (LMFR). The natural circulation ability and the system safety are obviously influenced by the two phase flow characteristics of liquid metal–inert gas. In this study, LENAC (LEad bismuth alloy NAtural Circulation capability) code has been developed to evaluate the natural circulation capability of lead–bismuth cooled ADS with gas-lift pump. The drift flow theory, void fraction prediction model and friction pressure drop prediction model have been incorporated into LENAC code. The calculation results by LENAC code show good agreement with experiment results of CIRCulation Experiment (CIRCE) facility. The effects of the gas mass flow rate, void fraction, gas quality, bubble diameter and the rising pipe height or the potential difference between heat exchanger and reactor core on natural circulation capability of gas-lift pump have been analyzed. The results showed that in bubbly flow pattern, for a fixed value of gas mass flow rate, the natural circulation capability increased with the decrease of the bubble diameter. In the bubbly flow, slug flow, churn flow and annular flow pattern, with the gas mass flow rate increasing, the natural circulation capability initially increased and then declined. And the flow parameters influenced the thermal hydraulic characteristics of the reactor core significantly. The present work is helpful for revealing the law of enhancing the natural circulation capability by gas-lift pump, and providing theoretical

  19. Cosmic radiation and airline pilots: Exposure pattern as a function of aircraft type

    International Nuclear Information System (INIS)

    The project presented here has been carried out as part of an epidemiological project on Norwegian aircraft personnel, entitled 'Exposure to low level ionising radiation and incidence of cancer in airline pilots and crew'. The purpose of the main project is to determine if there may be a relationship between exposure to cosmic radiation at aircraft cruising altitudes and the incidence of cancer. The methodology used as basis for estimating the radiation exposures is presented. The information used as basis for the dose estimations comes from a variety of sources: the files at the Personnel Licensing Section and the Aviation Medical Section of Norwegian Aviation Administration, the route tables of Scandinavian Airlines System (SAS), large amounts of expert information contributed by members of the Pilot's Associations in Norway and a couple of non-Norwegian pilots and from other members of the staff of SAS and other airlines. The estimation for each pilot was based on individual information of annual block hours and an estimated dose rate for each type of aircraft. The latter was estimated as a weighted average of CARI-estimated doses on a selection of routes flown by the airplanes in the different time periods. The project includes all pilots that have been licensed in Norway since 1946. These pilots have been flying a large variety of different types of aircraft and routes. The cosmic radiation intensity is a function of altitude in the atmosphere and, less markedly, of geographical latitude and of the intensity of the radiation from the sun (quantified as the heliocentric potential). Different types of aircraft fly at different altitudes and are used for different purposes (passenger traffic, cargo, air photography, preparation of maps etc) and used on different routes. The end results of the project described in this article are radiation exposures per block hour for each type of aircraft, and for each individual year (the differences between years reflect the

  20. Accuracy of measurement of thickness of a 6061 aluminum sample at 1-mm lift off

    International Nuclear Information System (INIS)

    The accuracy of measurement of a 0.51-mm thick, 6061 aluminum sample under lift-off variations of 0.25 mm at 1.08 is shown to be 5 percent by means of a complex-reluctance plane analysis. The analysis is shown to depend critically on the statistical accuracy of such measurements. Large lift-off measurements of aluminum thickness with large lift-off variations can be important for measurement of samples with radii of curvature such as aluminum cans, for measurements of sheets in rolling mills, and for reducing measurement problems in automatic scanning of aircraft skins where corrosion or spalling may have occurred

  1. Development of a Marine Propeller With Nonplanar Lifting Surfaces

    DEFF Research Database (Denmark)

    Andersen, Poul; Friesch, Jürgen; Kappel, Jens J.;

    2005-01-01

    The principle of non-planar lifting surfaces is applied to the design of modern aircraft wings to obtain better lift to drag ratios. Whereas a pronounced fin or winglet at the wingtip has been developed for aircraft, the application of the nonplanar principle to marine propellers, dealt with in...... this paper, has led to the KAPPEL propeller with blades curved toward the suction side integrating the fin or winglet into the propeller blade. The combined theoretical, experimental, and practical approach to develop and design marine propellers with nonplanar lifting surfaces has resulted in...

  2. Influence of Lift Offset on Rotorcraft Performance

    Science.gov (United States)

    Johnson, Wayne

    2009-01-01

    The influence of lift offset on the performance of several rotorcraft configurations is explored. A lift-offset rotor, or advancing blade concept, is a hingeless rotor that can attain good efficiency at high speed by operating with more lift on the advancing side than on the retreating side of the rotor disk. The calculated performance capability of modern-technology coaxial rotors utilizing a lift offset is examined, including rotor performance optimized for hover and high-speed cruise. The ideal induced power loss of coaxial rotors in hover and twin rotors in forward flight is presented. The aerodynamic modeling requirements for performance calculations are evaluated, including wake and drag models for the high-speed flight condition. The influence of configuration on the performance of rotorcraft with lift-offset rotors is explored, considering tandem and side-by-side rotorcraft as well as wing-rotor lift share.

  3. Modern trends of aircraft fly-by-wire systems

    Directory of Open Access Journals (Sweden)

    С. С. Юцкевич

    2013-07-01

    Full Text Available Specifics of civil aviation modern transport aircraft fly-by-wire control systems are described. A comparison of the systems-level hardware and software, expressed through modes of guidance, provision of aircraft Airbus A-320, Boeing B-777, Tupolev Tu-214, Sukhoi Superjet SSJ-100 are carried out. The possibility of transition from mechanical control wiring to control through fly-by-wire system in the backup channel is shown.

  4. Experimental and numerical research of lift force produced by Coandă effect

    Science.gov (United States)

    Constantinescu, S. G.; Niculescu, M. L.

    2013-10-01

    The paper presents research results of aerodynamics of Coandă airfoil, that is a key element of drones with jet propulsion. The Coandă propulsion allows drones to monitor quickly the large areas in emergencies: forest fires, earthquakes, meteor attacks and so on. The aim of this work consists in establishment of geometric and aerodynamic parameters at which, the lift force produced by Coandă airfoil is maximal.

  5. Hybrid upper surface blown flap propulsive-lift concept for the Quiet Short-Haul Research Aircraft

    Science.gov (United States)

    Cochrane, J. A.; Carros, R. J.

    1975-01-01

    The hybrid upper surface blowing concept consists of wing-mounted turbofan engines with a major portion of the fan exhaust directed over the wing upper surface to provide high levels of propulsive lift, but with a portion of the fan airflow directed over selected portions of the airframe to provide boundary layer control. NASA-sponsored preliminary design studies identified the hybrid upper surface blowing concept as the best propulsive lift concept to be applied to the Quiet Short-Haul Research Aircraft (QSRA) that is planned as a flight facility to conduct flight research at low noise levels, high approach lift coefficients, and steep approaches. Data from NASA in-house and NASA-sponsored small and large-scale wind tunnel tests of various configurations using this concept are presented.

  6. Lift Enhancement by Dynamically Changing Wingspan in Forward Flapping Flight

    CERN Document Server

    Wang, Shizhao; He, Guowei; Liu, Tianshu

    2013-01-01

    Stretching and retracting wingspan has been widely observed in the flight of birds and bats, and its effects on the aerodynamic performance particularly lift generation are intriguing. The rectangular flat-plate flapping wing with a sinusoidally stretching and retracting wingspan is proposed as a simple model of biologically-inspired dynamic morphing wings. Direct numerical simulations of the low-Reynolds-number flows around the flapping morphing wing in a parametric space are conducted by using immersed boundary method. It is found that the instantaneous and time-averaged lift coefficients of the wing can be significantly enhanced by dynamically changing wingspan in a flapping cycle. The lift enhancement is caused not only by changing the lifting surface area, but also manipulating the flow structures that are responsible to the generation of the vortex lift. The physical mechanisms behind the lift enhancement are explored by examining the three-dimensional flow structures around the flapping wing.

  7. Lifting of the Vlasov-Maxwell Bracket by Lie-transform Method

    CERN Document Server

    Brizard, A J; Burby, J W; de Guillebon, L; Vittot, M

    2016-01-01

    The Vlasov-Maxwell equations possess a Hamiltonian structure expressed in terms of a Hamiltonian functional and a functional bracket. In the present paper, the transformation ("lift") of the Vlasov-Maxwell bracket induced by the dynamical reduction of single-particle dynamics is investigated when the reduction is carried out by Lie-transform perturbation methods. The ultimate goal of this work is to derive explicit Hamiltonian formulations for the guiding-center and gyrokinetic Vlasov-Maxwell equations that have important applications in our understanding of turbulent magnetized plasmas.

  8. PRODUCTION SYSTEM MODELING OF THE GAS LIFTED WELL BY MEANS OF THE PROGRAM PROSPER

    Directory of Open Access Journals (Sweden)

    Sonja Koščak Kolin

    2009-12-01

    Full Text Available A production system analysis was made for the well Šandrovac-136 equipped with a continuous gas lift. The analysis was based on the test data which served as the foundation for creating a production well model in computer program ‘PROSPER’ (Version 10.3, License 2681. The importance of the measured data in well modeling is accuracy and reliability in predicting future developments of the production system. The model design can be divided in six steps among which the most important are: calculation of the IPR curve, calculation of the gas lift system and matching of VLP and IPR curves based on the well testing. The aim of the VLP/IPR matching is to choose an appropriate method for calculating the pressure drop gradient by applying the nonlinear regression method, which results in the system working point adjusted to the measured data. This model was applied in sensitivity analysis of the well, in which three key variables are selected to predict their effect on future system changes, primarily on changes of the production and bottom dynamic pressure (the paper is published in Croatian.

  9. Aircraft

    Science.gov (United States)

    Hibbs, Bart D.; Lissaman, Peter B. S.; Morgan, Walter R.; Radkey, Robert L.

    1998-01-01

    This disclosure provides a solar rechargeable aircraft that is inexpensive to produce, is steerable, and can remain airborne almost indefinitely. The preferred aircraft is a span-loaded flying wing, having no fuselage or rudder. Travelling at relatively slow speeds, and having a two-hundred foot wingspan that mounts photovoltaic cells on most all of the wing's top surface, the aircraft uses only differential thrust of its eight propellers to turn. Each of five sections of the wing has one or more engines and photovoltaic arrays, and produces its own lift independent of the other sections, to avoid loading them. Five two-sided photovoltaic arrays, in all, are mounted on the wing, and receive photovoltaic energy both incident on top of the wing, and which is incident also from below, through a bottom, transparent surface. The aircraft is capable of a top speed of about ninety miles per hour, which enables the aircraft to attain and can continuously maintain altitudes of up to sixty-five thousand feet. Regenerative fuel cells in the wing store excess electricity for use at night, such that the aircraft can sustain its elevation indefinitely. A main spar of the wing doubles as a pressure vessel that houses hydrogen and oxygen gasses for use in the regenerative fuel cell. The aircraft has a wide variety of applications, which include weather monitoring and atmospheric testing, communications, surveillance, and other applications as well.

  10. Dynamic response of Hovercraft lift fans

    Science.gov (United States)

    Moran, D. D.

    1981-08-01

    Hovercraft lift fans are subjected to varying back pressure due to wave action and craft motions when these vehicles are operating in a seaway. The oscillatory back pressure causes the fans to perform dynamically, exhibiting a hysteresis type of response and a corresponding degradation in mean performance. Since Hovercraft motions are influenced by variations in lift fan pressure and discharge, it is important to understand completely the nature of the dynamic performance of lift fans in order to completely solve the Hovercraft seakeeping problem. The present study was performed to determine and classify the instabilities encountered in a centrifugal fan operating against time-varying back pressure. A model-scale experiment was developed in which the fan discharge was directed into a flow-measuring device, terminating in a rotating valve which produced an oscillatory back pressure superimposed upon a mean aerodynamic resistance. Pressure and local velocity were measured as functions of time at several locations in the fan volute. The measurements permitted the identification of rotating (or propagating) stall in the impeller. One cell and two cell configurations were classified and the transient condition connecting these two configurations was observed. The mechanisms which lead to rotating stall in a centrifugal compressor are presented and discussed with specific reference to Hovercraft applications.

  11. X-ray inspection of composite materials for aircraft structures using detectors of Medipix type

    International Nuclear Information System (INIS)

    This work presents an overview of promising X-ray imaging techniques employed for non-destructive defectoscopy inspections of composite materials intended for the Aircraft industry. The major emphasis is placed on non-tomographic imaging techniques which do not require demanding spatial and time measurement conditions. Imaging methods for defects visualisation, delamination detection and porosity measurement of various composite materials such as carbon fibre reinforced polymers and honeycomb sendwiches are proposed. We make use of the new large area WidePix X-ray imaging camera assembled from up to 100 edgeless Medipix type detectors which is highly suitable for this type of measurements

  12. Shimura Lifts of Weakly Holomorphic Modular Forms

    OpenAIRE

    Li , Yingkun; Zemel, Shaul

    2015-01-01

    We show how to realize the Shimura lift of arbitrary level and character using the vector-valued theta lifts of Borcherds. Using the regularization of Borcherds' lift we extend the Shimura lift to take weakly holomorphic modular forms of half-integral weight to meromorphic modular forms of even integral weight having poles at CM points.

  13. Lifting analysis of integrated spool cover

    OpenAIRE

    Søfteland, Tor Edvard

    2013-01-01

    Large competition in the offshore industry requires innovative solutions to satisfy the demand. A new concept of spool installations is considered where three large spools are lifted in an integrated protection structure designed to support the spools during the lift and protect them from impact loads associated with fishing activities and dropped objects after installation. By integrating the spool and protection structure, the time needed for the installation will be significantly reduced. ...

  14. Intensive probing of a clear air convective field by radar and instrumental drone aircraft.

    Science.gov (United States)

    Rowland, J. R.

    1973-01-01

    An instrumented drone aircraft was used in conjunction with ultrasensitive radar to study the development of a convective field in the clear air. Radar data are presented which show an initial constant growth rate in the height of the convective field of 3.8 m/min, followed by a short period marked by condensation and rapid growth at a rate in excess of 6.1 m/min. Drone aircraft soundings show general features of a convective field including progressive lifting of the inversion at the top of the convection and a cooling of the air at the top of the field. Calculations of vertical heat flux as a function of time and altitude during the early stages of convection show a linear decrease in heat flux with altitude to near the top of the convective field and a negative heat flux at the top. Evidence is presented which supports previous observations that convective cells overshoot their neutral buoyancy level into a region where they are cool and moist compared to their surroundings. Furthermore, only that portion of the convective cell that has overshot its neutral buoyancy level is generally visible to the radar.

  15. Conceptual design of high speed supersonic aircraft: A brief review on SR-71 (Blackbird) aircraft

    Science.gov (United States)

    Xue, Hui; Khawaja, H.; Moatamedi, M.

    2014-12-01

    The paper presents the conceptual design of high-speed supersonic aircraft. The study focuses on SR-71 (Blackbird) aircraft. The input to the conceptual design is a mission profile. Mission profile is a flight profile of the aircraft defined by the customer. This paper gives the SR-71 aircraft mission profile specified by US air force. Mission profile helps in defining the attributes the aircraft such as wing profile, vertical tail configuration, propulsion system, etc. Wing profile and vertical tail configurations have direct impact on lift, drag, stability, performance and maneuverability of the aircraft. A propulsion system directly influences the performance of the aircraft. By combining the wing profile and the propulsion system, two important parameters, known as wing loading and thrust to weight ratio can be calculated. In this work, conceptual design procedure given by D. P. Raymer (AIAA Educational Series) is applied to calculate wing loading and thrust to weight ratio. The calculated values are compared against the actual values of the SR-71 aircraft. Results indicates that the values are in agreement with the trend of developments in aviation.

  16. The modeling and prediction of multiple jet VTOL aircraft flow fields in ground effect

    Science.gov (United States)

    Kotansky, D. R.

    1982-01-01

    An engineering methodology based on an empirical data base and analytical fluid dynamic models was developed for the prediction of propulsive lift system induced aerodynamic effects for multiple lift jet VTOL aircraft operating in the hover mode in and out of ground effect. The effects of aircraft geometry, aircraft orientation (pitch, roll) as well as height above ground are considered. Lift jet vector and splay directions fit the airframe, lift jet exit flow conditions, and both axisymmetric and rectangular nozzle exit geometry are also accommodated. The induced suckdown flows are computed from the potential flowfield induced by the turbulent entrainment of both the free jets and wall jets in ground effect and from the free jets alone out of ground effect. The methodology emphasized geometric considerations, computation of stagnation lines and fountain upwash inclination, fountain upwash formation and development, and fountain impingement on the airframe.

  17. Pt/Ti Electrodes of PZT Thin Films Patterning by Novel Lift-Off Using ZnO as a Sacrificial Layer

    International Nuclear Information System (INIS)

    We achieve a successful novel lift-off of patterning Pt/Ti electrodes on SiO2/Si substrates by employing ZnO sacrificial layer deposition and patterning, successive uniform Pt/Ti deposition and final lift-off. Then we deposit PZT thin films on the electrodes. Compared with the conventional lift-off processes for the electrodes, this novel process does not need post-annealing, which must be performed after conventional lift-off process. It is demonstrated that the electrodes patterned by the novel lift-off process have stronger adhesion. The electrodes and the PZT films on the electrodes are more compact and smoother than those by the conventional lift-off process

  18. WIND TUNNEL RESEARCH ON THE INFLUENCE OF ACTIVE AIRFLOW ON THE LIFT FORCE GENERATED BY THE AIRFOIL

    Directory of Open Access Journals (Sweden)

    Paweł Magryta

    2013-09-01

    Full Text Available The paper discusses the results of wind tunnel tests of airfoils with additional active airflow applied to their upper surfaces. These studies were carried out for a range of velocities up to 28 m/s in an open wind tunnel. Several types of airfoils selected for the examination feature different geometries and are widely applied in today’s aviation industry. The changes in the lift and drag force generated by these airfoils were recorded during the study. The test bench for the tests was equipped with a compressor and a vacuum pump to enable airflow through some holes on the airfoil upper surface. A rapid prototyping method and a 3D printer based on a powder printing technique were applied to print the airfoils. All of their surfaces were subject to surface grinding to smooth their external surfaces. The wind tunnel tests with and without active airflow applied to airfoils are summarised in the paper.

  19. Electromagnetic Radiation can affect the Lift Force

    OpenAIRE

    De Aquino, Fran

    2015-01-01

    Here we show that, under certain circumstances, electromagnetic radiations can strongly reduce the lift force. An aircraft for example, can be shot down when reached by a flux of specific electromagnetic radiation. This discovery can help the aircraft pilots to avoid regions where there are electromagnetic radiations potentially dangerous. Not only the flight of the aircrafts are affected by the electromagnetic radiation, but also the flight of any flying object whose flight depends on the li...

  20. Lift-up laminoplasty for myelopathy caused by ossification of the posterior longitudinal ligament of the cervical spine

    Directory of Open Access Journals (Sweden)

    Takami T

    2004-01-01

    Full Text Available Background and Aims: We have utilized lift-up laminoplasty to treat patients with myelopathy caused by ossification of the posterior longitudinal ligament (OPLL of the cervical spine. The preliminary surgical outcome with computer-assisted morphological assessment is presented. Material and Methods: The surgical technique of lift-up laminoplasty includes standard posterior exposure of the cervical spine, en-bloc laminectomy, and expansion of the cervical canal by lift-up of the laminae with custom-designed hydroxyapatite laminar spacers and stabilization of the laminae using titanium miniplates. From 1998 to 2003, 10 consecutive patients with cervical myelopathy secondary to OPLL have been treated with this method and comprehensively evaluated. Care was taken to tailor the treatment to individual patients by using different sizes of spacers to adjust the degree of expansion depending on the amount of stenosis of the cervical spine. The degree of expansion of the cervical canal was altered by design, based on the preoperative imaging simulation. Results: Preliminary surgical outcome, evaluated at 6 months after surgery, revealed a significant improvement of neurological function. Image analysis revealed that the cervical canals were significantly expanded, with a mean reduction of 13.1% in the stenosis ratio. Lift-up laminoplasty was effective in the treatment of patients with myelopathy secondary to cervical OPLL, and the amount of expansion could be individually adjusted at the discretion of the surgeon. Conclusion: Although analysis with a larger population and a longer follow-up period needs to be undertaken, our method of lift-up laminoplasty appears to be a viable choice among standard posterior cervical approaches for cervical OPLL.

  1. Flight test investigation of certification issues pertaining to general-aviation-type aircraft with natural laminar flow

    Science.gov (United States)

    Doty, Wayne A.

    1990-01-01

    Development of Natural Laminar Flow (NLF) technology for application to general aviation-type aircraft has raised some question as to the adequacy of FAR Part 23 for certification of aircraft with significant NLF. A series of flight tests were conducted with a modified Cessna T210R to allow quantitative comparison of the aircraft's ability to meet certification requirements with significant NLF and with boundary layer transition fixed near the leading edge. There were no significant differences between the two conditions except an increasing in drag, which resulted in longer takeoff distances and reduced climb performance.

  2. Hoisting facility for lifting/descent maneuvers of storage container main sub-assembly on the fabrication line and inside the stand-by repository

    International Nuclear Information System (INIS)

    The main sub-assembly of the CANDU type spent fuel storage container is composed of a stainless steel circular plate with 25 mm thickness and 1070 mm diameter on which a central pivot is mounted allowing manipulation of both the sub-assembly and loaded container, as well as retaining and positioning the clusters to be stored. Combined mass of these components results in 230 kg, a value which requires adequate mechanical means for manipulations. The proposed facility is simpler than the one pneumatically or hydraulically driven since it implies no longer pneumatic or hydraulic installations which, as additional burden, render more difficult the lifting /descending maneuvers over longer ranges, both in the fabrication sector and stand-by repository, as well. Two lifting rings are provided in which the hook of the lifting device is introduced to block /unblock the device in/ from the central pivot of the container's main sub-assembly. The technical characteristics are: - maximal load for lifting, 500 kg; - height, 990 mm; - breadth, 360 mm; - gripping diameter of the end part, 60 mm; - external diameter of the balls in the position 'blocked', 70 mm; - own mass, 57 kg; - functioning position, vertical. A drawing is given showing the facility together with the storage container (unloaded)

  3. The design of steel string crane with lifting capacity 10 tons

    International Nuclear Information System (INIS)

    The steel string (sling) used for lift Crane of type of Overhead Travelling Crane, with capacities lifting 10 ton are designed. If compared to other string type, string of steel have some excellence. At this design, election of type of string become primary and the factor of safety become prima facie matter with pursuant to up to date standard. From made of design, is hence got by specification and age of steel string. (author)

  4. Separation of Lift-Generated Vortex Wakes Into Two Diverging Parts

    Science.gov (United States)

    Rossow, Vernon J.; Brown, Anthony P.

    2010-01-01

    As part of an ongoing study of the spreading rate of lift-generated vortex wakes, the present investigation considers possible reasons as to why segments of lift-generated wakes sometimes depart from the main part of the wake to move rapidly in either an upward or downward direction. It is assumed that deficiencies or enhancements of the lift carry over across the fuselage-shrouded wing are the driving mechanism for departures of wake-segments. The computations presented first indicate that upwardly departing wake segments that were observed and photographed could have been produced by a deficiency in lift carryover across the fuselage-shrouded part of the wing. Computations made of idealized vortex wakes indicate that upward departure of a wake segment requires a centerline reduction in the span loading of 70% or more, whether the engines are at idle or robust thrust. Similarly, it was found that downward departure of wake segments is produced when the lift over the center part of the wing is enhanced. However, it was also found that downward departures do not occur without the presence of robust engine-exhaust streams (i.e., engines must NOT be at idle). In those cases, downward departures of a wake segment occurs when the centerline value of the loading is enhanced by any amount between about 10% to 100%. Observations of condensation trails indicate that downward departure of wake segments is rare. Upward departures of wake segments appears to be more common but still rare. A study to determine the part of the aircraft that causes wake departures has not been carried out. However, even though departures of wake segments rarely occur, some aircraft do regularly shed these wake structures. If aircraft safety is to be assured to a high degree of reliability, and a solution for eliminating them is not implemented, existing guidelines for the avoidance of vortex wakes [1,3] may need to be broadened to include possible increases in wake sizes caused by vertical

  5. CHARACTERIZATION OF FULLERENE DERIVATIVES BY MALDI LIFT-TOF/TOF MASS SPECTROMETRY

    OpenAIRE

    PIOTROVSKY L.B.; MILMAN B.L.; NIKOLAEV D.N.; LUGOVKINA N.V.; LITASOVA E.V.; DUMPIS M.A.

    2014-01-01

    MALDI LIFT-TOF/TOF mass spectra of fullerene C 60 and six of its derivatives, methano[60]fullerene carboxylic acid, its ethyl ester, diethyl methano[60]fullerene dicarboxylate, and three isomeric tetraethyl bis-methano[60]fullerene tetracarboxylates (compounds I-VII, respectively) as model analytes were recorded and discussed. This technique used in mass spectrometry for the first time is proposed for the characterization, structure elucidation, and non-target screening of fullerenes.

  6. Long lifetime and high-fidelity quantum memory of photonic polarization qubit by lifting Zeeman degeneracy

    OpenAIRE

    Xu, Zhongxiao; Wu, Yuelong; Tian, Long; Chen, Lirong; Zhang, Zhiying; Yan, Zhihui; Li, Shujing; Wang, Hai; Xie, Changde; Peng, Kunchi

    2013-01-01

    Long-lived and high-fidelity memory for photonic polarization qubit (PPQ) is crucial for constructing quantum networks. Here we present an EIT-based millisecond storage system in which a moderate magnetic field is applied on a cold-atom cloud to lift Zeeman degeneracy. PPQ states are stored as two magnetic-field-insensitive spin waves. Especially, the influence of magnetic-field-sensitive spin waves on the storage performances is almost totally avoided. The measured average fidelities of pola...

  7. Time resolved three-dimensional flamebase imaging of a lifted jet flame by laser scanning

    Science.gov (United States)

    Weinkauff, J.; Greifenstein, M.; Dreizler, A.; Böhm, B.

    2015-10-01

    The measurement of flame surface evolution in both space and time is necessary for the advancement of knowledge concerning the physical processes contributing to lifted jet flame stabilisation. Previous studies either reproduce the flame front accurately in three-dimensional space or in time. In this study a measurement system capable of both is presented. Based on the Mie-scattering of oil droplets added to the jet flow, the system reconstructs the volumetric surface at the base of a lifted jet flame from a series of two-dimensional slices. The slices are created using a pulsed high-speed laser and a polygonal laser scanner unit which serves to sweep the laser beam through the measurement volume. A single high-speed camera is used for recording the subsequent measurement slices. The achieved temporal and spatial resolution as well as the accuracy and precision of the sheet placement are discussed in respect to the flames’ scales. The first results of the reconstruction of the lifted jet flame at its stabilisation point show the potential of such measurements to avoid the ambiguities in interpreting conventional 2D-data.

  8. Time resolved three-dimensional flamebase imaging of a lifted jet flame by laser scanning

    International Nuclear Information System (INIS)

    The measurement of flame surface evolution in both space and time is necessary for the advancement of knowledge concerning the physical processes contributing to lifted jet flame stabilisation. Previous studies either reproduce the flame front accurately in three-dimensional space or in time. In this study a measurement system capable of both is presented. Based on the Mie-scattering of oil droplets added to the jet flow, the system reconstructs the volumetric surface at the base of a lifted jet flame from a series of two-dimensional slices. The slices are created using a pulsed high-speed laser and a polygonal laser scanner unit which serves to sweep the laser beam through the measurement volume. A single high-speed camera is used for recording the subsequent measurement slices. The achieved temporal and spatial resolution as well as the accuracy and precision of the sheet placement are discussed in respect to the flames’ scales. The first results of the reconstruction of the lifted jet flame at its stabilisation point show the potential of such measurements to avoid the ambiguities in interpreting conventional 2D-data. (paper)

  9. Effect of wing flexibility on aircraft flight dynamics

    OpenAIRE

    Qiao, Yuqing

    2012-01-01

    The purpose of this thesis is to give a preliminary investigation into the effect of wing deformation on flight dynamics. The candidate vehicle is FW-11 which is a flying wing configuration aircraft with high altitude and long endurance characteristics. The aeroelastic effect may be significant for this type of configuration. Two cases, the effect of flexible wing on lift distribution and on roll effectiveness during the cruise condition with different inertial parameters are investigated. ...

  10. Study on dynamic lifting characteristics of control rod drive mechanism

    International Nuclear Information System (INIS)

    Based on the equations of the electric circuit and the magnetic circuit and analysis of the dynamic lifting process for the control rod drive mechanism (CRDM), coupled magnetic-electric-mechanical equations both for the static status and the dynamic status are derived. The analytical method is utilized to obtain the current and the time when the lift starts. The numerical simulation method of dynamic analysis recommended by ASME Code is utilized to simulate the dynamic lifting process of CRDM, and the dynamic features of the system with different design gaps are studied. Conclusions are drawn as: (1) the lifting-start time increases with the design gap, and the time for the lifting process is longer with larger gaps; (2) the lifting velocity increases with time; (3) the lifting acceleration increases with time, and with smaller gaps, the impact acceleration is larger. (author)

  11. Transportation of Floating Structures by Using Newly Built Heavy Lifting Semi Vessel HYSY278

    Institute of Scientific and Technical Information of China (English)

    SUN Wei-ying; ZHANG Da-gang; FAN Zhi-xia

    2013-01-01

    Transportation of floating structures for long distance has always been associated with the use of heavy semi transport vessel.The requirements of this type of vessel are always special,and its availability is limited.To prepare for the future development of the South China Sea deepwater projects,COOEC has recently built a heavy lift transport vessel-Hai Yang Shi You 278 (HYSY278).This semi-submersible vessel has displacement capacity of 50k DWT,and a breath of 42 m.Understanding the vessel's applicability and preparing its use for future deepwater projects are becoming imminent need.This paper reviews the critical issues associated with the floating structure transportation and performs detailed analysis of two designed floating structures during transportation.The newly built COOEC transportation vessel HYSY278 will be used to dry transport the floating structures from COOEC fabrication yard in Qingdao to the oil field in the South China Sea.The entire process will start with load-out/float-offthe floating structures from the construction sites,offload the platform from the vessel if needed,dry transport floating structures through a long distance,and finally offload the platform.Both hydrodynamic and structural analyses are performed to evaluate transport vessel and floating structures.Critical issues associated with the transportation and offloading of platform from the vessel will be studied in detail.Detailed study is performed to evaluate the response of the system during this phase and additional work needed to make the vessel feasible for use of this purpose.The results demonstrate that with proper modifications,HYSY278 can effectively be used for transporting structures with proper arrangement and well-prepared operation.The procedure and details are presented on the basis of study results.Special attentions associated with future use will also be discussed based on the results from analysis.

  12. Maximum acceptable weights for asymmetric lifting of Chinese females.

    Science.gov (United States)

    Wu, Swei-Pi

    2003-05-01

    This study used the psychophysical approach to evaluate the effects of asymmetric lifting on the maximum acceptable weight of lift (MAWL) and the resulting heart rate, oxygen uptake and rating of perceived exertion (RPE). A randomized complete block factorial design was employed. Twelve female college students lifted weights at three different lifting frequencies (one-time maximum, 1 and 4 lifts/min) in the sagittal plane and at three different asymmetric angles (30 degrees, 60 degrees, and 90 degrees ) from the floor to a 68-cm height pallet. This lifting experiment was conducted for a 1-h work period using a free-style lifting technique. The MAWLs for asymmetric lifting were significantly lower than those for symmetric lifting in the sagittal plane. The MAWL decreased with the increase in the angle of asymmetry. However, the heart rate, oxygen uptake and RPE remained unchanged. Though the MAWL decreased significantly with lifting frequency, both the physiological costs (heart rate and oxygen uptake) and rating of perceived exertion increased with the increase in lift frequency. The most stressed body part was the arm. Lifting frequency had no significant effect on the percentage decrease in MAWL from the sagittal plane values. On average, decreases of 5%, 9% and 14% for MAWL at 30 degrees, 60 degrees and 90 degrees asymmetric lifting, respectively, were revealed. This result was in agreement with the findings of Chinese males studied by Wu [Int. J. Ind. Ergonom. 25 (2000) 675]. The percentage decrease in MAWL with twisting angle for the Chinese participants was somewhat lower than those for Occidental participants. In addition, even though there was an increase in heart rate and RPE with the increase in the symmetrical lift angle for Occidental participants, it was different from the Chinese participants. Lastly, the 1991 NIOSH equation asymmetry multiplier is more conservative in comparison with the results of the present study. PMID:12737921

  13. Long lifetime and high-fidelity quantum memory of photonic polarization qubit by lifting Zeeman degeneracy

    CERN Document Server

    Xu, Zhongxiao; Tian, Long; Chen, Lirong; Zhang, Zhiying; Yan, Zhihui; Li, Shujing; Wang, Hai; Xie, Changde; Peng, Kunchi

    2013-01-01

    Receiving a photonic qubit, storing it with long lifetime and retrieving it with high fidelity are crucial for constructing quantum networks. Photonic polarization qubits (PPQs) are extensively used for encoding and transmitting quantum information since they are easily manipulated and analyzed. Dynamic Electromagnetically induced transparency (EIT) in atoms is an efficient process to store PPQs which has been studied. However, due to the decoherence induced by magnetic field fluctuations, the lifetime of the qubit memory is limited and the achieved longest lifetime in EIT based system is only about 470us, so far. Here we present an EIT based millisecond storage in which a moderate magnetic field is applied on a cold atom cloud to lift Zeeman degeneracy. PPQ states can be stored as two magnetic field insensitive spin waves and the influence of magnetic field sensitive spin waves on the storage is almost totally avoided. The measured average fidelity of polarization states is 0.986 at 200us and 0.784 at 4.5ms.

  14. Analysis of ROV Lift Operation

    OpenAIRE

    Bjerkholt, Runa Folvik

    2014-01-01

    As a service company performing subsea operations, DeepOcean wishes to operate in the widest range of sea conditions. The majority of all offshore operations are performed using remotely operated vehicles (ROVs), where lifting through the splash zone is considered the most critical phase during launching and recovery of the ROV system. Available standards from DNV propose a systematic and analytical approach for estimating the hydrodynamic loads occurring in the splash zone. A maximum operati...

  15. Transient analysis of energy Transfer Control (ECT) and compressor bleed concepts of remote lift fan control

    Science.gov (United States)

    Sellers, J. F.

    1973-01-01

    The transient performance of two concepts for control of vertical takeoff aircraft remote lift fans is analyzed and discussed. Both concepts employ flow transfer between pairs of lift fans located in separate parts of the aircraft in order to obtain attitude control moments for hover and low-speed flight. The results presented are from a digital computer, dynamic analysis of the YJ97/LF460 remote drive turbofan. The transient responses of the two systems are presented for step demands in lift and moment.

  16. Validation of Vortex-Lattice Method for Loads on Wings in Lift-Generated Wakes

    Science.gov (United States)

    Rossow, Vernon J.

    1995-01-01

    A study is described that evaluates the accuracy of vortex-lattice methods when they are used to compute the loads induced on aircraft as they encounter lift-generated wakes. The evaluation is accomplished by the use of measurements made in the 80 by 120 ft Wind Tunnel of the lift, rolling moment, and downwash in the wake of three configurations of a model of a subsonic transport aircraft. The downwash measurements are used as input for a vortex-lattice code in order to compute the lift and rolling moment induced on wings that have a span of 0.186, 0.510, or 1.022 times the span of the wake-generating model. Comparison of the computed results with the measured lift and rolling-moment distributions the vortex-lattice method is very reliable as long as the span of the encountering or following wing is less than about 0.2 of the generator span. As the span of the following wing increases above 0.2, the vortex-lattice method continues to correctly predict the trends and nature of the induced loads, but it overpredicts the magnitude of the loads by increasing amounts.

  17. Postural responses triggered by multidirectional leg lifts and surface tilts.

    Science.gov (United States)

    Hughey, Lucinda K; Fung, Joyce

    2005-08-01

    movement generation and the recovery of postural equilibrium during leg lifting. In conclusion, regardless of the type (voluntary versus involuntary) or direction of perturbation, the strategy employed by the central nervous system to control the body COM displacement concerns mainly trunk stabilization. PMID:15940494

  18. Doubling the annual coefficient of performance of air-conditioning units by taking advantage of small temperature lifts; Verdoppelung der Jahresarbeitszahl von Klimakaelteanlagen durch Ausnuetzung eines kleinen Temperaturhubes

    Energy Technology Data Exchange (ETDEWEB)

    Wellig, B.; Kegel, B.; Meier, M.

    2006-07-01

    The seasonal performance factor (SPF) of chilled water systems (CWS) is closely related to the temperature lift, i.e. the difference between the temperature of the heat source and the heat sink. In many applications in building services engineering, a temperature lift of 10-20 K is in principle sufficient. However, the potential for highly efficient refrigerating systems is not fully exploited as standard chillers are designed for lifts of 30-60 K. The exergy analysis of typical CWS shows that the external exergy losses are greater than the exergy losses of the chiller. The second-law (or exergetic) efficiency is usually far below 10%. It is therefore important to avoid unnecessarily high temperature lifts. Measurements on refrigeration systems in two office buildings have shown that even in state-of-the-art CWS, considerable energy savings (up to 50%) can be achieved by persistent use of small temperature lifts. However, SPF-values around 5-6 can hardly be exceeded in systems with electric driven chillers. SPFs higher than 10 or even above 20 can only be reached with optimized free cooling processes. Basic decisions, which ultimately lead to CWS with unnecessarily high temperature lifts, are taken in the early project stages. Therefore, this study presents guidelines for the design and operation of CWS with small temperature lifts. The implementation of these simple measures will lead to a considerable reduction of energy consumption and operating costs. (author)

  19. Evaluation of hydraulic lift in cotton germplasm

    Science.gov (United States)

    Hydraulic lift (HL) in plants is defined as the redistribution of water from wetter to drier soil through the plant roots in response to soil water potential gradients. Water is released from the roots into the dry soil when transpiration is low (night) and reabsorbed by the plant when higher transp...

  20. Static Thrust Analysis of the Lifting Airscrew

    Science.gov (United States)

    Knight, Montgomery; Hefner, Ralph A

    1937-01-01

    This report presents the results of a combined theoretical and experimental investigation conducted at the Georgia School of Technology on the static thrust of the lifting air screw of the type used in modern autogiros and helicopters. The theoretical part of this study is based on Glauert's analysis but certain modifications are made that further clarify and simplify the problem. Of these changes the elimination of the solidity as an independent parameter is the most important. The experimental data were obtained from tests on four rotor models of two, four, and five blades and, in general, agree quite well with the theoretical calculations. The theory indicates a method of evaluating scale effects on lifting air screws, and these corrections have been applied to the model results to derive general full-scale static thrust, torque, and figure-of-merit curves for constant-chord, constant-incidence rotors. Convenient charts are included that enable hovering flight performance to be calculated rapidly.

  1. Marketing Strategy of Integration as a Condition of Modernisation of the Lift Industry

    OpenAIRE

    Zamlinskaya Olga V.

    2013-01-01

    The article justifies selection of a marketing strategy of Ukrainian companies of lift servicing, which would provide an opportunity to ensure their economic growth and modernisation. Having analysed literature, it systemises features of classification of marketing strategies and identifies new approaches and strategy types. It offers solution of the problem of modernisation of the lift industry of Ukraine by means of selection of the marketing strategy of growth in the form of horizontal con...

  2. Monitoring Disasters by Use of Instrumented Robotic Aircraft

    Science.gov (United States)

    Wegener, Steven S.; Sullivan, Donald V.; Dunagan, Steven E.; Brass, James A.; Ambrosia, Vincent G.; Buechel, Sally W.; Stoneburner, Jay; Schoenung, Susan M.

    2009-01-01

    Efforts are under way to develop data-acquisition, data-processing, and data-communication systems for monitoring disasters over large geographic areas by use of uninhabited aerial systems (UAS) robotic aircraft that are typically piloted by remote control. As integral parts of advanced, comprehensive disaster- management programs, these systems would provide (1) real-time data that would be used to coordinate responses to current disasters and (2) recorded data that would be used to model disasters for the purpose of mitigating the effects of future disasters and planning responses to them. The basic idea is to equip UAS with sensors (e.g., conventional video cameras and/or multispectral imaging instruments) and to fly them over disaster areas, where they could transmit data by radio to command centers. Transmission could occur along direct line-of-sight paths and/or along over-the-horizon paths by relay via spacecraft in orbit around the Earth. The initial focus is on demonstrating systems for monitoring wildfires; other disasters to which these developments are expected to be applicable include floods, hurricanes, tornadoes, earthquakes, volcanic eruptions, leaks of toxic chemicals, and military attacks. The figure depicts a typical system for monitoring a wildfire. In this case, instruments aboard a UAS would generate calibrated thermal-infrared digital image data of terrain affected by a wildfire. The data would be sent by radio via satellite to a data-archive server and image-processing computers. In the image-processing computers, the data would be rapidly geo-rectified for processing by one or more of a large variety of geographic-information- system (GIS) and/or image-analysis software packages. After processing by this software, the data would be both stored in the archive and distributed through standard Internet connections to a disaster-mitigation center, an investigator, and/or command center at the scene of the fire. Ground assets (in this case

  3. Three-dimensional micro assembly of a hinged nickel micro device by magnetic lifting and micro resistance welding

    International Nuclear Information System (INIS)

    The three-dimensional micro assembly of hinged nickel micro devices by magnetic lifting and micro resistance welding is proposed here. By an electroplating-based surface machining process, the released nickel structure with the hinge mechanism can be fabricated. Lifting of the released micro structure to different tilted angles is accomplished by controlling the positions of a magnet beneath the device. An in situ electro-thermal actuator is used here to provide the pressing force in micro resistance welding for immobilizing the tilted structure. The proposed technique is shown to immobilize micro devices at controlled angles ranging from 14° to 90° with respect to the substrate. Design parameters such as the electro-thermal actuator and welding beam width are also investigated. It is found that there is a trade-off in beam width design between large contact pressure and low thermal deformation. Different dominated effects from resistivity enhancement and contact area enlargement during the welding process are also observed in the dynamic resistance curves. Finally, a lifted and immobilized electro-thermal bent-beam actuator is shown to displace upward about 27.7 µm with 0.56 W power input to demonstrate the capability of electrical transmission at welded joints by the proposed 3D micro assembly technique

  4. Biomechanical exploration on dynamic modes of lifting.

    Science.gov (United States)

    Gagnon, M; Smyth, G

    1992-03-01

    Whatever the lifting method used, dynamic factors appear to have an effect on the safe realization of movement, and NIOSH guidelines recommend smooth lifting with no sudden acceleration effects. On the other hand, inertial forces may play an important role in the process of transfer of momentum to the load. The direction by which these inertial forces may affect the loadings on body structures and processes of energy transfers cannot be determined a priori. A biomechanical experiment was performed to examine if there were differences in the execution processes between a slow-continuous lift and an accelerated-continuous lift, and also between accelerated lifts either executed continuously or interrupted with a pause. The lifts were executed from a height of 15 cm to a height of 185 cm above the head and with two different loads (6.4 and 11.6 kg). Five experienced workers in manual materials handling were used as subjects. Films and force platforms recordings supplied the data; dynamic segmental analyses were performed to calculate net muscular moments at each joint; a planar single-muscle equivalent was used to estimate compression loadings at L5/S1; total mechanical work, joint work distribution, and energy transfers were determined from a kinetic approach based on the integration of joint power as a function of time. Analyses of variance with repeated measures were applied to the three treatments. The results showed that joint muscular moments, spinal loadings, mechanical work, and muscular utilization ratios were generally increased by the presence of acceleration without inducing benefits of improved energy transfers; therefore slower lifts with reduced acceleration may be safer when handling moderately heavy loads. The maximum values of kinematic and kinetic factors were generally not affected by the pause, but the occurrence of jerks in the movement (acceleration, ground forces, and muscular moments) suggests that the pause may not be indicated when

  5. 78 FR 79599 - Airworthiness Directives; Various Aircraft Equipped With Wing Lift Struts

    Science.gov (United States)

    2013-12-31

    ...: Airworthiness Directive 99-01-05 R1, Amendment 39-17688 (78 FR 73997, December 10, 2013), will require... published in the Federal Register on January 16, 2013 (78 FR 3356). No other part of the preamble or... Equipped With Wing Lift Struts AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final...

  6. Auralization of novel aircraft configurations

    OpenAIRE

    Arntzen, M.; Bertsch, E.L.; Simons, D.G.

    2015-01-01

    A joint initiative of NLR, DLR, and TU Delft has been initiated to streamline the process of generating audible impressions of novel aircraft configurations. The integrated approach adds to the value of the individual tools and allows predicting the sound of future aircraft before they actually fly. Hence, an existing process for the aircraft design and system noise prediction at DLR has been upgraded to generate the required input data for an aircraft auralization framework developed by NLR ...

  7. Generalised Eisenhart lift of the Toda chain

    OpenAIRE

    Cariglia, Marco; Gibbons, Gary

    2013-01-01

    The Toda chain of nearest neighbour interacting particles on a line can be described both in terms of geodesic motion on a manifold with one extra dimension, the Eisenhart lift, or in terms of geodesic motion in a symmetric space with several extra dimensions. We examine the relationship between these two realisations and discover that the symmetric space is a generalised, multi-particle Eisenhart lift of the original problem, that reduces to the standard Eisenhart lift. Such generalised Eise...

  8. EXPERIMENTAL RESEARCHES OF THE AEROHYDRAULIC WATER LIFT

    Directory of Open Access Journals (Sweden)

    Kizyun Z. V.

    2014-03-01

    Full Text Available In the article, we have presented the experimental researches of the aerohydraulic water lift. The influence of the pressure on the aerohydraulic water lift and water giving height on productivity has been researched as well as we have made a multifactorial research of productivity of aerohydraulic water lift. It has been established that productivity of the aerohydraulic water lift depends on the difference between pressure and water giving height. Influences of diameters of submitting and nutritious pipelines on productivity have been established

  9. Brief analysis of lifting technology used in two cranes rotary lifting method for CPR1000 in main system equipment

    International Nuclear Information System (INIS)

    The lifting of equipment which located in the main system of NI is an important link of erection. The lifting process of heavy equipment is characterized by complicated process, difficult technology, high safety requirement, and plenty of manpower and resources. So the lifting of NI heavy equipment is a critical and key technical issue for the construction of nuclear power plant. With the booming of nuclear power industry, it makes positive and realistic sense to summarize the proven technique of lifting, create new procedure, and promote the development of hoisting technology for heavy equipment of nuclear power plant. As a kind of social wealth, the lifting technique of heavy equipment shall be summarized, improved and spread to be a good reference for broadening our mind and guiding the lifting operation. (authors)

  10. Characterization of gas-lift instabilities

    OpenAIRE

    Hu, Bin

    2005-01-01

    This dissertation mainly investigates the occurrence and characteristics of density-wave instability in gas-lift wells. The investigation is based on a simplified gas-lift system, in which water and air are used as producing fluid and lifting gas respectively, and heat transfer effect is neglected.To carry out the investigation, both linear stability analysis and numerical simulation are performed. The linear stability analysis is based on a homogenous two-phase flow model and the numerical s...

  11. PREDICTION OF AIRCRAFT NOISE LEVELS

    Science.gov (United States)

    Clark, B. J.

    1994-01-01

    Methods developed at the NASA Lewis Research Center for predicting the noise contributions from various aircraft noise sources have been incorporated into a computer program for predicting aircraft noise levels either in flight or in ground test. The noise sources accounted for include fan inlet and exhaust, jet, flap (for powered lift), core (combustor), turbine, and airframe. Noise propagation corrections are available in the program for atmospheric attenuation, ground reflections, extra ground attenuation, and shielding. The capacity to solve the geometrical relationships between an aircraft in flight and an observer on the ground has been included in the program to make it useful in evaluating noise estimates and footprints for various proposed engine installations. The program contains two main routines for employing the noise prediction routines. The first main routine consists of a procedure to calculate at various observer stations the time history of the noise from an aircraft flying at a specified set of speeds, orientations, and space coordinates. The various components of the noise are computed by the program. For each individual source, the noise levels are free field with no corrections for propagation losses other than spherical divergence. The total spectra may then be corrected for the usual effects of atmospheric attenuation, extra ground attenuation, ground reflection, and aircraft shielding. Next, the corresponding values of overall sound pressure level, perceived noise level, and tone-weighted perceived noise level are calculated. From the time history at each point, true effective perceived noise levels are calculated. Thus, values of effective perceived noise levels, maximum perceived noise levels, and tone-weighted perceived noise levels are found for a grid of specified points on the ground. The second main routine is designed to give the usual format of one-third octave sound pressure level values at a fixed radius for a number of user

  12. IDENTIFICATION OF AIRCRAFT HAZARDS

    International Nuclear Information System (INIS)

    Aircraft hazards were determined to be potentially applicable to a repository at Yucca Mountain in the ''Monitored Geological Repository External Events Hazards Screening Analysis'' (BSC 2004, Section 6.4.1). That determination was conservatively based on limited knowledge of flight data in the area of concern and on crash data for aircraft of the type flying near Yucca Mountain. The purpose of this report is to identify specific aircraft hazards that may be applicable to a Monitored Geologic Repository (MGR) at Yucca Mountain using NUREG-0800, ''Standard Review Plan for the Review of Safety Analysis Reports for Nuclear Power Plants'' (NRC 1987, Section 3.5.1.6), as guidance for the inclusion or exclusion of identified aircraft hazards. NUREG-0800 is being used here as a reference because some of the same considerations apply. The intended use of this report is to provide inputs for further screening and analysis of the identified aircraft hazards based on the criteria that apply to Category 1 and 2 event sequence analyses as defined in 10 CFR 63.2 (see Section 4). The scope of this technical report includes the evaluation of military, private, and commercial use of airspace in the 100-mile regional setting of the MGR at Yucca Mountain with the potential for reducing the regional setting to a more manageable size after consideration of applicable screening criteria (see Section 7)

  13. IDENTIFICATION OF AIRCRAFT HAZARDS

    Energy Technology Data Exchange (ETDEWEB)

    K.L. Ashley

    2005-03-23

    Aircraft hazards were determined to be potentially applicable to a repository at Yucca Mountain in the ''Monitored Geological Repository External Events Hazards Screening Analysis'' (BSC 2004, Section 6.4.1). That determination was conservatively based on limited knowledge of flight data in the area of concern and on crash data for aircraft of the type flying near Yucca Mountain. The purpose of this report is to identify specific aircraft hazards that may be applicable to a Monitored Geologic Repository (MGR) at Yucca Mountain using NUREG-0800, ''Standard Review Plan for the Review of Safety Analysis Reports for Nuclear Power Plants'' (NRC 1987, Section 3.5.1.6), as guidance for the inclusion or exclusion of identified aircraft hazards. NUREG-0800 is being used here as a reference because some of the same considerations apply. The intended use of this report is to provide inputs for further screening and analysis of the identified aircraft hazards based on the criteria that apply to Category 1 and 2 event sequence analyses as defined in 10 CFR 63.2 (see Section 4). The scope of this technical report includes the evaluation of military, private, and commercial use of airspace in the 100-mile regional setting of the MGR at Yucca Mountain with the potential for reducing the regional setting to a more manageable size after consideration of applicable screening criteria (see Section 7).

  14. Identification of Aircraft Hazards

    Energy Technology Data Exchange (ETDEWEB)

    K. Ashley

    2006-12-08

    Aircraft hazards were determined to be potentially applicable to a repository at Yucca Mountain in ''Monitored Geological Repository External Events Hazards Screening Analysis'' (BSC 2005 [DIRS 174235], Section 6.4.1). That determination was conservatively based upon limited knowledge of flight data in the area of concern and upon crash data for aircraft of the type flying near Yucca Mountain. The purpose of this report is to identify specific aircraft hazards that may be applicable to a monitored geologic repository (MGR) at Yucca Mountain, using NUREG-0800, ''Standard Review Plan for the Review of Safety Analysis Reports for Nuclear Power Plants'' (NRC 1987 [DIRS 103124], Section 3.5.1.6), as guidance for the inclusion or exclusion of identified aircraft hazards. The intended use of this report is to provide inputs for further screening and analysis of identified aircraft hazards based upon the criteria that apply to Category 1 and Category 2 event sequence analyses as defined in 10 CFR 63.2 [DIRS 176544] (Section 4). The scope of this report includes the evaluation of military, private, and commercial use of airspace in the 100-mile regional setting of the repository at Yucca Mountain with the potential for reducing the regional setting to a more manageable size after consideration of applicable screening criteria (Section 7).

  15. Identification of Aircraft Hazards

    International Nuclear Information System (INIS)

    Aircraft hazards were determined to be potentially applicable to a repository at Yucca Mountain in ''Monitored Geological Repository External Events Hazards Screening Analysis'' (BSC 2005 [DIRS 174235], Section 6.4.1). That determination was conservatively based upon limited knowledge of flight data in the area of concern and upon crash data for aircraft of the type flying near Yucca Mountain. The purpose of this report is to identify specific aircraft hazards that may be applicable to a monitored geologic repository (MGR) at Yucca Mountain, using NUREG-0800, ''Standard Review Plan for the Review of Safety Analysis Reports for Nuclear Power Plants'' (NRC 1987 [DIRS 103124], Section 3.5.1.6), as guidance for the inclusion or exclusion of identified aircraft hazards. The intended use of this report is to provide inputs for further screening and analysis of identified aircraft hazards based upon the criteria that apply to Category 1 and Category 2 event sequence analyses as defined in 10 CFR 63.2 [DIRS 176544] (Section 4). The scope of this report includes the evaluation of military, private, and commercial use of airspace in the 100-mile regional setting of the repository at Yucca Mountain with the potential for reducing the regional setting to a more manageable size after consideration of applicable screening criteria (Section 7)

  16. 49 CFR 1560.107 - Use of watch list matching results by covered aircraft operators.

    Science.gov (United States)

    2010-10-01

    ... SECURE FLIGHT PROGRAM Collection and Transmission of Secure Flight Passenger Data for Watch List Matching § 1560.107 Use of watch list matching results by covered aircraft operators. A covered aircraft operator... 49 Transportation 9 2010-10-01 2010-10-01 false Use of watch list matching results by...

  17. 14 CFR 119.53 - Wet leasing of aircraft and other arrangements for transportation by air.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Wet leasing of aircraft and other arrangements for transportation by air. 119.53 Section 119.53 Aeronautics and Space FEDERAL AVIATION... Chapter § 119.53 Wet leasing of aircraft and other arrangements for transportation by air. (a)...

  18. Emission of ions and charged soot particles by aircraft engines

    OpenAIRE

    Sorokin, A.; Vancassel, X.; P. Mirabel

    2003-01-01

    In this article, a model which examines the formation and evolution of chemiions in an aircraft engine is proposed. This model which includes chemiionisation, electron thermo-emission, electron attachment to soot particles and to neutral molecules, electron-ion and ion-ion recombination, ion-soot interaction, allows the determination of the ion concentration at the exit of the combustor and at the nozzle exit of the engine. It also allows the determination ...

  19. Design, characterization and application of the Multiple Air-lift Loop bioreactor.

    OpenAIRE

    Bakker, W.A.M.

    1995-01-01

    A new bioreactor is introduced: the Multiple Air-lift Loop reactor (MAL). The MAL consists of a series of air-lift loop reactors within one vessel. With the MAL, a new type of geometry for air-lift reactors with an internal loop is introduced. This new geometry was characterized with respect to hydrodynamics, mixing and oxygen transfer. The hydrodynamics were described by an existing model. Hydrodynamics, mixing and oxygen transfer in the new reactor configuration were comparable to that in c...

  20. Administrative regulations concerning the carriage of dangerous substances by civil aircraft

    International Nuclear Information System (INIS)

    The Regulations, which entered into force on the date they were adopted, apply to the transport of dangerous substances by civil aircraft in Norway and by aircraft registered in Norway for transport outside Norwegian territory. They provide that such substances, including radioactive materials, must be carried in accordance with the IATA Restricted Articles Regulations

  1. Benefits of VTOL aircraft in offshore petroleum logistics support

    Science.gov (United States)

    Wilcox, D. E.; Shovlin, M. D.

    1975-01-01

    The mission suitability and potential economic benefits of advanced VTOL aircraft were investigated for logistics support of petroleum operations in the North Sea and the Gulf of Mexico. Concepts such as the tilt rotor and lift/cruise fan are promising for future operations beyond 150 miles offshore, where their high cruise efficiency provides savings in trip time, fuel consumption, and capital investment. Depending upon mission requirements, the aircraft operating costs are reduced by as much as 20 percent to 50 percent from those of current helicopters.

  2. Computational Aerodynamic Prediction for Integration of an Advanced Reconnaissance Pod on a 5th Generation Fighter Type Aircraft

    Directory of Open Access Journals (Sweden)

    De Paolis P

    2015-06-01

    Full Text Available In this paper a computational aerodynamic prediction to support the aeromechanical integration of an advanced reconnaissance pod on a 5th generation fighter type aircraft is presented. The aim of the activity was to compare the aerodynamic characteristics of the new pod to a previous one already cleared on the same aircraft fleet, given verified inertial and structural similarity. Verifying the aforementioned aerodynamic similarity without involving extensive flight test activity was a must, to save time and to reduce costs. A two steps approach was required by the Certification Authority to verify, initially, the performance data compatibility in terms of aerodynamic coefficients of the old pod with the new one, in order to allow performance flight manual data interchangeability (a quantitative comparison was required; afterwards, a qualitative assessment was conducted to verify the absence of unsteadiness induced by the introduction in the external structure of the new pod of an auxiliary antenna case. Computational results are presented both for Straight and Level Un-accelerated Flight and SteadySideslip flight conditions at different Angles of Attack.

  3. CM values of regularized theta lifts

    OpenAIRE

    Ehlen, Stephan Jakob

    2013-01-01

    In this thesis, special values of regularized theta lifts at complex multiplication (CM) points are studied. In particular, it is shown that CM values of Borcherds products can be expressed in terms of finitely many Fourier coefficients of certain harmonic weak Maass forms of weight one. As it turns out, these coefficients are logarithms of algebraic integers whose prime ideal factorization is determined by cycles on an arithmetic curve that parametrize special endomorphisms of CM elliptic cu...

  4. Onboard space - and aircraft dosimetry by means of different methods

    Czech Academy of Sciences Publication Activity Database

    Spurný, František; Jadrníčková, Iva

    Buenos Aires: SAR, 2008. s. 478-478. [International Congress of the International Radiation Protection Association /12./. 19.10.2008-24.10.2008, Buenos Aires] Grant ostatní: Evropské společenství(XE) ILSRA - 2004 - 248 Institutional research plan: CEZ:AV0Z10480505 Keywords : dosimetry onboard spacecraft * aircraft crew exposure * detectors Subject RIV: BG - Nuclear, Atomic and Molecular Physics, Colliders

  5. A Knowledge Based Approach for Automated Modelling of Extended Wing Structures in Preliminary Aircraft Design

    OpenAIRE

    Dorbath, Felix; Nagel, Björn; Gollnick, Volker

    2011-01-01

    This paper introduces the concept of the ELWIS model generator for Finite Element models of aircraft wing structures. The physical modelling of the structure is extended beyond the wing primary structures, to increase the level of accuracy for aircraft which diverge from existing configurations. Also the impact of novel high lift technologies on structural masses can be captured already in the early stages of design by using the ELWIS models. The ELWIS model generator is able to c...

  6. Thermodynamic efficiency of present types of internal combustion engines for aircraft

    Science.gov (United States)

    Lucke, Charles E

    1917-01-01

    Report presents requirements of internal combustion engines suitable for aircraft. Topics include: (1) service requirements for aeronautic engines - power versus weight, reliability, and adaptability factors, (2) general characteristics of present aero engines, (3) aero engine processes and functions of parts versus power-weight ratio, reliability, and adaptability factors, and (4) general arrangement, form, proportions, and materials of aero parts - power-weight ratio, reliability, and adaptability.

  7. Liftings of Reduction Maps for Quaternion Algebras

    OpenAIRE

    Cornut, Christophe; Jetchev, Dimitar

    2010-01-01

    We construct liftings of reduction maps from CM points to supersingular points for general quaternion algebras and use these liftings to establish a precise correspondence between CM points on indefinite quaternion algebras with a given conductor and CM points on certain corresponding totally definite quaternion algebras.

  8. [Removal of Cr from tannery sludge by bioleaching in air-lift reactor: a pilot study].

    Science.gov (United States)

    Chen, Hao; Zhou, Li-xiang; Li, Chao

    2007-09-01

    A bioleaching process performed in 280 L air-lift reactor was developed for extracting Cr from tannery sludge. Cr removal efficiency under different aeration amount with a range from 1.0 m3/h to 3.0 m3/h was investigated. The results showed that the sludge could be homogeneous quickly for different aeration treatment even if aeration amount was as low as 1.0 m3/h. But the obvious effect of aeration amount on pH decrease and subsequent Cr dissolution in tannery sludge during bioleaching was observed. If the aeration amount was below 1.5 m3/h, it at least took 90 h to reach 80% Cr removal efficiency. In the light of Cr removal efficiency and energy consume, the aeration amount of 2.0 m3/h was considered as an optimum one for bioleaching in this trial. Cr removal efficiency could reach above 92.5% at 72 h. In the sludge bioleaching system dissolved oxygen increased obviously with the decrease of pH. Eventually, dissolved oxygen rised to 5 mg/L or more when aeration amount was maintained at 2.0 m3/h or more. Therefore, it was suggested that the aeration amount in ALR could be adjusted to a lower level in the late stage of tannery sludge bioleaching in order to save operation cost. PMID:17990555

  9. Patterning of epitaxial VO2 microstructures by a high-temperature lift-off process

    International Nuclear Information System (INIS)

    The growing field of oxide-electronics demands adequate fabrication methods that do not impair the material’s beneficial properties. To this end, we present a modified lift-off lithography method replacing the conventional polymer mask with an AlOx based mask. It can sustain the high-temperature and reactive gasses conditions commonly needed for oxide deposition, and is effectively wet-etched in dilute NaOH solutions. Here we demonstrate patterning of VO2 films. With its metal–insulator transition (MIT) near room temperature, it is attractive for various applications including sensors and transistors. But patterning is challenging since its properties are very sensitive to fabrication processes. We demonstrate patterning of 3 μm wide VO2 electrodes and show they preserve the MIT magnitude and epitaxial growth of the non-patterned films. Some thinning of the VO2 is also observed. This process can be useful for patterning other materials that require harsh deposition conditions, and are resilient to low NaOH concentrations. (paper)

  10. Cosmic radiation and airline pilots. Exposure patterns of Norwegian pilots flying aircraft not used by SAS

    Energy Technology Data Exchange (ETDEWEB)

    Tveten, U.

    1997-05-01

    The work which is presented in this report is part of a Norwegian epidemiological project, carried out in cooperation between Institutt for Energiteknikk (IFE), the Norwegian Cancer Registry (NCR) and the Norwegian Radiation Protection Authority (NRPA). The project has been partially financed by the Norwegian Research Council. Originating from the Norwegian project, a number of similar projects have been started or are in the planning stage in a number of European countries. The present report lays the ground for estimation of individual exposure histories to cosmic radiation of pilots flying a great diversity of different aircrafts. Aircrafts that appear in the time-tables of the Scandinavian Airline System (SAS) have been treated in an earlier report. The results presented in this report (radiation doserates for the different types of aircrafts in the different years) will, in a later stage of the project be utilized to estimate the individual radiation exposure histories. The major sources of information used as basis for the work in this report is information provided by several active pilots, members of the Pilots Associations, along with calculations performed using US Federal Aviation Administration`s computer code CARI-3N. 2 refs.

  11. Cosmic radiation and airline pilots. Exposure patterns of Norwegian pilots flying aircraft not used by SAS

    International Nuclear Information System (INIS)

    The work which is presented in this report is part of a Norwegian epidemiological project, carried out in cooperation between Institutt for Energiteknikk (IFE), the Norwegian Cancer Registry (NCR) and the Norwegian Radiation Protection Authority (NRPA). The project has been partially financed by the Norwegian Research Council. Originating from the Norwegian project, a number of similar projects have been started or are in the planning stage in a number of European countries. The present report lays the ground for estimation of individual exposure histories to cosmic radiation of pilots flying a great diversity of different aircrafts. Aircrafts that appear in the time-tables of the Scandinavian Airline System (SAS) have been treated in an earlier report. The results presented in this report (radiation doserates for the different types of aircrafts in the different years) will, in a later stage of the project be utilized to estimate the individual radiation exposure histories. The major sources of information used as basis for the work in this report is information provided by several active pilots, members of the Pilots Associations, along with calculations performed using US Federal Aviation Administration's computer code CARI-3N. 2 refs

  12. Correlation of Puma airloads: Lifting-line and wake calculation

    Science.gov (United States)

    Bousman, William G.; Young, Colin; Gilbert, Neil; Toulmay, Francois; Johnson, Wayne; Riley, M. J.

    1989-01-01

    A cooperative program undertaken by organizations in the United States, England, France, and Australia has assessed the strengths and weaknesses of four lifting-line/wake methods and three CFD methods by comparing their predictions with the data obtained in flight trials of a research Puma. The Puma was tested in two configurations: a mixed bladed rotor with instrumented rectangular tip blades, and a configuration with four identical swept tip blades. The results are examined of the lifting-line predictions. The better lifting-line methods show good agreement with lift at the blade tip for the configuration with four swept tips; the moment is well predicted at 0.92 R, but deteriorates outboard. The predictions for the mixed bladed rotor configuration range from fair to good. The lift prediction is better for the swept tip blade than for the rectangular tip blade, but the reasons for this cannot be determined because of the unmodeled effects of the mixed bladed rotor.

  13. 75 FR 31803 - Notice of Issuance of Final Determination Concerning a Lift Unit for an Overhead Patient Lift System

    Science.gov (United States)

    2010-06-04

    .... The unit is manufactured in 3 basic models: (1) 242, which has a lifting capacity up to 440 pounds; (2) 243, which has a lifting capacity up to 507 pounds; and (3) 250, which has a lifting capacity up to... lift system. The system is capable of lifting and transporting patients with limited mobility,...

  14. Fabrication of nanoscale Bi Hall sensors by lift-off techniques for applications in scanning probe microscopy

    International Nuclear Information System (INIS)

    Bismuth Hall effect sensors with active sizes in the range of 0.1–2 μm have been fabricated by electron beam lithography and lift-off techniques for applications in scanning Hall probe microscopy. The Hall coefficients, offset resistances and minimum detectable fields of the sensors have been systematically characterised as a function of device size. The minimum detectable field of 100 nm probes at 300 K and dc currents of 5 μA was found to be Bmin = 0.9 mT Hz−0.5 with scope for up to a factor of ten reduction by using higher Hall probe currents. This is significantly lower than in similar samples fabricated by focused ion beam (FIB) milling of continuous Bi films, suggesting that the elimination of FIB damage and Ga+ ion incorporation through the use of lift-off techniques leads to superior figures of merit. A number of ways in which the room temperature performance of our sensors could be further improved are discussed. (paper)

  15. Lifting index of the niosh lifting equation and low back pain

    Directory of Open Access Journals (Sweden)

    Eliana Remor Teixeira

    2011-09-01

    Full Text Available The purpose of this study is to assess the relationship of the Lifting Index obtained through the application of the NIOSH Lifting Equation and the incidence of low back pain among forty-eight workers involved in manual lifting tasks. It was applied the equation in eleven tasks and the workers were interviewed. The most unfavorable conditions presented themselves in the lifting destination. The variables that most contributed to the inadequate values of the Lifting Index were: the horizontal location, the lifting frequency and the vertical distance, beyond the high weight of the load. The incidence of low back pain in the last twelve months was 19%, whereas the incidence of work-related low back pain in the same period was 10%. In 72.7% of the tasks evaluated the Composite Lifting Index was more than three, which are considered as high ergonomic risk.

  16. Occupational lifting of heavy loads and preterm birth:

    DEFF Research Database (Denmark)

    Runge, Stine Bjerrum; Pedersen, Jacob Krabbe; Svendsen, Susanne Wulff; Juhl, Mette; Bonde, Jens Peter; Nybo Andersen, Anne-Marie

    2013-01-01

    To examine the association between occupational lifting during pregnancy and preterm birth. The risk of preterm birth was estimated for total burden lifted per day and number of medium and heavy loads lifted per day.......To examine the association between occupational lifting during pregnancy and preterm birth. The risk of preterm birth was estimated for total burden lifted per day and number of medium and heavy loads lifted per day....

  17. Bed-Load Transport Rate Based on the Entrainment Probabilities of Sediment Grains by Rolling and Lifting

    CERN Document Server

    Li, Jun-De; Lin, Binliang

    2016-01-01

    A function for the bed-load sediment transport rate is derived. This is achieved from the first principle by using the entrainment probabilities of the sediment grains by rolling and lifting, and by introducing two travel lengths, respectively, for the first time. The predictions from the new bed-load function agree well with the experimental results over the entire experimental range and show significant improvement over the commonly used formula for bed-load transport rate. The new function shows that, in terms of contributing to the bed-load transport rate, the total entrainment probability of the sediment grains is a weighted summation of those by the lifted and rolling grains, rather than a simple addition of the two. The function has also been used to predict the total entrainment probability, saltation length and the bed layer thickness at high bed-load transport rate. These predictions all agree well with the experimental results. It is found that, on average, the travel length for the rolling sand gr...

  18. Turboprop aircraft against terrorism: a SWOT analysis of turboprop aircraft in CAS operations

    Science.gov (United States)

    Yavuz, Murat; Akkas, Ali; Aslan, Yavuz

    2012-06-01

    Today, the threat perception is changing. Not only for countries but also for defence organisations like NATO, new threat perception is pointing terrorism. Many countries' air forces become responsible of fighting against terorism or Counter-Insurgency (COIN) Operations. Different from conventional warfare, alternative weapon or weapon systems are required for such operatioins. In counter-terrorism operations modern fighter jets are used as well as helicopters, subsonic jets, Unmanned Aircraft Systems (UAS), turboprop aircraft, baloons and similar platforms. Succes and efficiency of the use of these platforms can be determined by evaluating the conditions, the threats and the area together. Obviously, each platform has advantages and disadvantages for different cases. In this research, examples of turboprop aircraft usage against terrorism and with a more general approach, turboprop aircraft for Close Air Support (CAS) missions from all around the world are reviewed. In this effort, a closer look is taken at the countries using turboprop aircraft in CAS missions while observing the fields these aircraft are used in, type of operations, specifications of the aircraft, cost and the maintenance factors. Thus, an idea about the convenience of using these aircraft in such operations can be obtained. A SWOT analysis of turboprop aircraft in CAS operations is performed. This study shows that turboprop aircraft are suitable to be used in counter-terrorism and COIN operations in low threat environment and is cost benefical compared to jets.

  19. Emission of ions and charged soot particles by aircraft engines

    Directory of Open Access Journals (Sweden)

    A. Sorokin

    2003-01-01

    Full Text Available In this article, a model which examines the formation and evolution of chemiions in an aircraft engine is proposed. This model which includes chemiionisation, electron thermo-emission, electron attachment to soot particles and to neutral molecules, electron-ion and ion-ion recombination, ion-soot interaction, allows the determination of the ion concentration at the exit of the combustor and at the nozzle exit of the engine. It also allows the determination of the charge of the soot particles. For the engine considered, the upper limit for the ion emission index EIi is of the order of (2-5 x1016 ions/kg-fuel if ion-soot interactions are ignored and the introduction of ion-soot interactions lead about to a 50% reduction. The results also show that most of the soot particles are either positively or negatively charged, the remaining neutral particles representing approximately 20% of the total particles. A comparison of the model results with the available ground-based experimental data obtained on the ATTAS research aircraft engines during the SULFUR experiments (Schumann, 2002 shows an excellent agreement.

  20. Lift-contractions.

    OpenAIRE

    Golovach, Petr A.; Paulusma, Daniël; Kamiski, Marcin; Thilikos, Dimitrios M.

    2014-01-01

    We introduce and study a partial order on graphs – lift-contractions. A graph H is a lift-contraction of a graph G if H can be obtained from G by a sequence of edge lifts and edge contractions. We give sufficient conditions for a connected graph to contain every n-vertex graph as a lift-contraction and describe the struc-ture of graphs with an excluded lift-contraction.

  1. Investigation of the Applicability of the Free-wing Principle to Light, General Aviation Aircraft

    Science.gov (United States)

    Porter, R. F.; Luce, R. G.; Brown, J. H., Jr.

    1972-01-01

    Gust-alleviation benefits for aircraft employing an unconventional wing, free to pivot about a spanwise axis forward of its aerodynamic center and subject only to aerodynamic pitching moments imposed by lift and drag forces and a trailing-edge control surface are reviewed.

  2. Analytical study of a free-wing/free-trimmer concept. [for gust alleviation and high lift

    Science.gov (United States)

    Porter, R. F.; Hall, D. W.; Brown, J. H., Jr.; Gregorek, G. M.

    1978-01-01

    The free-wing/free-trimmer is a NASA-Conceived extension of the free-wing concept intended to permit the use of high-lift flaps. Wing pitching moments are balanced by a smaller, external surface attached by a boom or equivalent structure. The external trimmer is, itself, a miniature free wing, and pitch control of the wing-trimmer assembly is effected through a trailing-edge control tab on the trimmer surface. The longitudinal behavior of representative small free-wing/free-trimmer aircraft was analyzed. Aft-mounted trimmer surfaces are found to be superior to forward trimmers, although the permissible trimmer moment arm is limited, in both cases, by adverse dynamic effects. Aft-trimmer configurations provide excellent gust alleviation and meet fundamental stick-fixed stability criteria while exceeding the lift capabilities of pure free-wing configurations.

  3. Incremental wind tunnel testing of high lift systems

    Science.gov (United States)

    Victor, Pricop Mihai; Mircea, Boscoianu; Daniel-Eugeniu, Crunteanu

    2016-06-01

    Efficiency of trailing edge high lift systems is essential for long range future transport aircrafts evolving in the direction of laminar wings, because they have to compensate for the low performance of the leading edge devices. Modern high lift systems are subject of high performance requirements and constrained to simple actuation, combined with a reduced number of aerodynamic elements. Passive or active flow control is thus required for the performance enhancement. An experimental investigation of reduced kinematics flap combined with passive flow control took place in a low speed wind tunnel. The most important features of the experimental setup are the relatively large size, corresponding to a Reynolds number of about 2 Million, the sweep angle of 30 degrees corresponding to long range airliners with high sweep angle wings and the large number of flap settings and mechanical vortex generators. The model description, flap settings, methodology and results are presented.

  4. The influence of air duct geometry on air jet direction in aircraft cabin ventilated by mixing ventilation.

    Science.gov (United States)

    Fišer, J.; Jícha, M.

    2013-04-01

    The paper deals with instigation of influence of air duct geometry on air jet direction in aircraft cabin ventilated by mixing ventilation. CFD approach was used for investigation and model geometry was based on small aircraft cabin mock-up geometry. Model was also equipped by nine seats and five manikins that represent passengers. The air jet direction was observed for selected ambient environment parameters and several types of air duct geometry and influence of main air duct geometry on jets direction is discussed. The model was created in StarCCM+ ver. 6.04.014 software and polyhedral mesh was used.

  5. The influence of air duct geometry on air jet direction in aircraft cabin ventilated by mixing ventilation.

    Directory of Open Access Journals (Sweden)

    Jícha M.

    2013-04-01

    Full Text Available The paper deals with instigation of influence of air duct geometry on air jet direction in aircraft cabin ventilated by mixing ventilation. CFD approach was used for investigation and model geometry was based on small aircraft cabin mock-up geometry. Model was also equipped by nine seats and five manikins that represent passengers. The air jet direction was observed for selected ambient environment parameters and several types of air duct geometry and influence of main air duct geometry on jets direction is discussed. The model was created in StarCCM+ ver. 6.04.014 software and polyhedral mesh was used.

  6. Piloted Simulation Study of the Effects of High-Lift Aerodynamics on the Takeoff Noise of a Representative High-Speed Civil Transport

    Science.gov (United States)

    Glaab, Louis J.; Riley, Donald R.; Brandon, Jay M.; Person, Lee H., Jr.; Glaab, Patricia C.

    1999-01-01

    As part of an effort between NASA and private industry to reduce airport-community noise for high-speed civil transport (HSCT) concepts, a piloted simulation study was initiated for the purpose of predicting the noise reduction benefits that could result from improved low-speed high-lift aerodynamic performance for a typical HSCT configuration during takeoff and initial climb. Flight profile and engine information from the piloted simulation were coupled with the NASA Langley Aircraft Noise Prediction Program (ANOPP) to estimate jet engine noise and to propagate the resulting source noise to ground observer stations. A baseline aircraft configuration, which also incorporated different levels of projected improvements in low-speed high-lift aerodynamic performance, was simulated to investigate effects of increased lift and lift-to-drag ratio on takeoff noise levels. Simulated takeoff flights were performed with the pilots following a specified procedure in which either a single thrust cutback was performed at selected altitudes ranging from 400 to 2000 ft, or a multiple-cutback procedure was performed where thrust was reduced by a two-step process. Results show that improved low-speed high-lift aerodynamic performance provides at least a 4 to 6 dB reduction in effective perceived noise level at the FAA downrange flyover measurement station for either cutback procedure. However, improved low-speed high-lift aerodynamic performance reduced maximum sideline noise levels only when using the multiple-cutback procedures.

  7. Active structural acoustic control of aircraft interior flow noise via the use of active trim panels

    OpenAIRE

    Mahnken, Brian W.

    1996-01-01

    Modem jet aircraft interior noise can be categorized into two main types: tonal noise caused by engine imbalance or blade passage, and mid frequency broadband noise resulting from turbulent flow. This project addresses aircraft interior flow noise caused by a flow separation over the crown of the aircraft. The noise control approach is to mount piezoelectric actuators to the aircraft interior cockpit crown trim panel and use them to actively control aircraft interior noise with...

  8. 78 FR 3356 - Airworthiness Directives; Various Aircraft Equipped With Wing Lift Struts

    Science.gov (United States)

    2013-01-16

    ... wing lift struts. That AD superseded AD 93-10-06, amendment 39-8586 (58 FR 29965, May 25, 1993), and... cracking found on the wing lift strut forks. AD 99-01-05, amendment 39-10972 (63 FR 72132, December 31...- 10972 (63 FR 72132, December 31, 1998). This AD clarifies the FAA's intention that if a sealed wing...

  9. Lifting scheme of symmetric tight wavelets frames

    Institute of Scientific and Technical Information of China (English)

    ZHUANG BoJin; YUAN WeiTao; PENG LiZhong

    2008-01-01

    This paper proposes a method to realize the lifting scheme of tight frame wavelet filters. As for 4-channel tight frame wavelet filter, the tight frame transforms' ma-trix is 2×4, but the lifting scheme transforms' matrix must be 4×4. And in the case of 3-channel tight frame wavelet filter, the transforms' matrix is 2×3, but the lifting scheme transforms' matrix must be 3×3. In order to solve this problem, we intro-duce two concepts: transferred polyphase matrix for 4-channel filters and trans-ferred unitary matrix for 3-channel filters. The transferred polyphase matrix is sym-metric/antisymmetric. Thus, we use this advantage to realize the lifting scheme.

  10. Modeling and performance of pig-lift

    Energy Technology Data Exchange (ETDEWEB)

    Santos, Odair G. dos; Alhanati, Francisco J.S.; Bordalo, Sergio N. [Universidade Estadual de Campinas, SP (Brazil). Faculdade de Engenharia Mecanica. Dept. de Engenharia de Petroleo]. E-mail: bordalo@dep.fem.unicamp.br

    1997-07-01

    Artificial lift is used in petroleum when the energy of the reservoir is not enough to sustain the flow of oil in the well up to the surface with satisfactory economic return. The gas-lift is a widely used method of artificial lift: in some cases, the continuous gas lift (CGL) is not efficient, and one must implement the intermittent gas-lift (IGL), for which there are different design options. There are some empirical and questionable rules of thumb to choose between the CGL and IGL, but almost no material exists in the literature for the selection among the different intermittent gas-lift design; furthermore, there are no published models or behavior studies of their dynamics to help in the selection and design of IGL systems. This work presents a model to study the novel IGL WITH PIG. In this system, a foam-pig separates the oil and gas flowing in the well, to prevent fall-back of oil; a double column is used inside the well. This paper presents sample results for some conditions of the petroleum reservoir. This work can aid the engineer in the determination of the optimum values of the operational parameters, and in the choice of the IGL design for particular field conditions. (author)

  11. Wind tunnel investigation of a high lift system with pneumatic flow control

    Science.gov (United States)

    Victor, Pricop Mihai; Mircea, Boscoianu; Daniel-Eugeniu, Crunteanu

    2016-06-01

    Next generation passenger aircrafts require more efficient high lift systems under size and mass constraints, to achieve more fuel efficiency. This can be obtained in various ways: to improve/maintain aerodynamic performance while simplifying the mechanical design of the high lift system going to a single slotted flap, to maintain complexity and improve the aerodynamics even more, etc. Laminar wings have less efficient leading edge high lift systems if any, requiring more performance from the trailing edge flap. Pulsed blowing active flow control (AFC) in the gap of single element flap is investigated for a relatively large model. A wind tunnel model, test campaign and results and conclusion are presented.

  12. On the injectivity of the Kudla-Millson lift and surjectivity of the Borcherds lift.

    OpenAIRE

    Bruinier, Jan H.; Funke, J.

    2010-01-01

    We consider the Kudla-Millson lift from elliptic modular forms of weight (p+q)/2 to closed q-forms on locally symmetric spaces corresponding to the orthogonal group O(p,q). We study the L^2-norm of the lift following the Rallis inner product formula. We compute the contribution at the Archimedian place. For locally symmetric spaces associated to even unimodular lattices, we obtain an explicit formula for the L^2-norm of the lift, which often implies that the lift is injective. For O(p,2) we d...

  13. Catalytic Generation of Lift Gases for Balloons

    Science.gov (United States)

    Zubrin, Robert; Berggren, Mark

    2011-01-01

    A lift-gas cracker (LGC) is an apparatus that generates a low-molecular-weight gas (mostly hydrogen with smaller amounts of carbon monoxide and/or carbon dioxide) at low gauge pressure by methanol reforming. LGCs are undergoing development for use as sources of buoyant gases for filling zero-gauge-pressure meteorological and scientific balloons in remote locations where heavy, high-pressure helium cylinders are not readily available. LGCs could also be used aboard large, zero-gauge-pressure, stratospheric research balloons to extend the duration of flight.

  14. Bioleaching of heavy metals from contaminated sediment by indigenous sulfur-oxidizing bacteria in an air-lift bioreactor: effects of sulfur concentration.

    Science.gov (United States)

    Chen, Shen-Yi; Lin, Jih-Gaw

    2004-01-01

    The effects of sulfur concentration on the bioleaching of heavy metals from the sediment by indigenous sulfur-oxidizing bacteria were investigated in an air-lift reactor. Increasing the sulfur concentration from 0.5 to 5 g/l enhanced the rates of pH reduction, sulfate production and metal solubilization. A Michaelis-Menten type equation was used to explain the relationships between sulfur concentration, sulfate production and metal solubilization in the bioleaching process. After 8 days of bioleaching, 97-99% of Cu, 96-98% of Zn, 62-68% of Mn, 73-87% of Ni and 31-50% of Pb were solubilized from the sediment, respectively. The efficiency of metal solubilization was found to be related to the speciation of metal in the sediment. From economical consideration, the recommended sulfur dosage for the bioleaching of metals from the sediment is 3g/l. PMID:15276736

  15. AFC-Enabled Simplified High-Lift System Integration Study

    Science.gov (United States)

    Hartwich, Peter M.; Dickey, Eric D.; Sclafani, Anthony J.; Camacho, Peter; Gonzales, Antonio B.; Lawson, Edward L.; Mairs, Ron Y.; Shmilovich, Arvin

    2014-01-01

    The primary objective of this trade study report is to explore the potential of using Active Flow Control (AFC) for achieving lighter and mechanically simpler high-lift systems for transonic commercial transport aircraft. This assessment was conducted in four steps. First, based on the Common Research Model (CRM) outer mold line (OML) definition, two high-lift concepts were developed. One concept, representative of current production-type commercial transonic transports, features leading edge slats and slotted trailing edge flaps with Fowler motion. The other CRM-based design relies on drooped leading edges and simply hinged trailing edge flaps for high-lift generation. The relative high-lift performance of these two high-lift CRM variants is established using Computational Fluid Dynamics (CFD) solutions to the Reynolds-Averaged Navier-Stokes (RANS) equations for steady flow. These CFD assessments identify the high-lift performance that needs to be recovered through AFC to have the CRM variant with the lighter and mechanically simpler high-lift system match the performance of the conventional high-lift system. Conceptual design integration studies for the AFC-enhanced high-lift systems were conducted with a NASA Environmentally Responsible Aircraft (ERA) reference configuration, the so-called ERA-0003 concept. These design trades identify AFC performance targets that need to be met to produce economically feasible ERA-0003-like concepts with lighter and mechanically simpler high-lift designs that match the performance of conventional high-lift systems. Finally, technical challenges are identified associated with the application of AFC-enabled highlift systems to modern transonic commercial transports for future technology maturation efforts.

  16. Fabrication of flexible superhydrophobic films by lift-up soft-lithography and decoration with Ag nanoparticles

    International Nuclear Information System (INIS)

    Superhydrophobic films with excellent flexibility have been fabricated by combining the lift-up soft-lithography technique and chemical reduction of [Ag(NH3)2]+ ions to Ag nanoparticles (NPs) on the surface of silica spheres which are patterned on the polydimethylsiloxane (PDMS) films. Scanning electron microscopy (SEM) images reveal the presence of raspberry-like hierarchical structures on the PDMS films. The influence of the amount of Ag NPs and the size of the silica spheres on the wettability of the soft films is investigated carefully. Because PDMS films are elastomeric materials, our superhydrophobic films offer great flexibility. The resulting films can be easily transferred from one substrate surface to another without destroying their superhydrophobicity. These flexible and superhydrophobic films can be used repeatedly to satisfy a wide range of applications.

  17. Impact of Aircraft Performance Characteristics on Air Traffic Delays

    OpenAIRE

    Aydan CAVCAR; CAVCAR, Mustafa

    2004-01-01

    Air transportation has been suffering for decades from delays caused by air traffic congestion. This paper presents the effect of aircraft performance differences on air traffic delays. Rate of climb and cruising speeds of 70 different aircraft types are compared to demonstrate performance differences in the current transport aircraft fleet. The effect of these performance differences on air traffic delays is proved by a deterministic calculation of delays for a departure queue cons...

  18. Design of a Three Surfaces R/C Aircraft Model

    Directory of Open Access Journals (Sweden)

    D. P. Coiro

    2002-01-01

    Full Text Available Design of a three lifting surfaces radio-controlled model has been carried out at Dipartimento di Progettazione Aeronautica (DPA by the authors in the last year. The model is intended to be a UAV prototype and is now under construction. The main goal of this small aircraft's design is to check the influence of the canard surface on the aircraft's aerodynamic characteristics and flight behavior, especially at high angles of attack. The aircraft model is also intended to be a flying platform to test sensors, measurement and acquisition systems for research purposes and a valid and low-cost teaching instrument for flight dynamics and flight maneuvering. The aircraft has been designed to fly with and without canard, and all problems relative to aircraft balance and stability have been carefully analyzed and solved. The innovative configuration and the mixed wooden-composite material structure has been obtained with very simple shapes and all the design is focused on realizing a low-cost model. A complete aerodynamic analysis of the configuration up to high angles of attack and a preliminary aircraft stability and performance prediction will be presented.

  19. Energetics of oscillating lifting surfaces using integral conservation laws

    Science.gov (United States)

    Ahmadi, Ali R.; Widnall, Sheila E.

    1987-01-01

    The energetics of oscillating flexible lifting surfaces in two and three dimensions is calculated by the use of integral conservation laws in inviscid incompressible flow for general and harmonic transverse oscillations. Total thrust is calculated from the momentum theorem and energy loss rate due to vortex shedding in the wake from the principle of conservation of mechanical energy. Total power required to maintain the oscillations and hydrodynamic efficiency are also determined. In two dimensions, the results are obtained in closed form. In three dimensions, the distribution of vorticity on the lifting surface is also required as input to the calculations. Thus, unsteady lifting-surface theory must be used as well. The analysis is applicable to oscillating lifting surfaces of arbitrary planform, aspect ratio, and reduced frequency and does not require calculation of the leading-edge thrust.

  20. The Model Of One-Type Aircraft Fleet Behaviour While Service And Advantages SHM V. NDT Implementation

    Directory of Open Access Journals (Sweden)

    Lewitowicz Jerzy

    2014-12-01

    Full Text Available The paper defines the essence of durability characteristics of the designing structure of an airframe in terms of flight safety. Particular attention is drawn to one of the main factors influencing the durability characteristics of the airframe – diagnostics system for the health assessment of the airframe during the process of operation. The effectiveness of the use of integrated solutions to the structure of the airframe providing a continuous assessment of the technical condition is presented. Continuous diagnostics system integrated with the airframe, SHM, is classified as an intelligent solution. This paper presents a model of the behavior of one-type aircraft operating in the air operator’s fleet in terms of susceptibility to failure. Justified assumption in the description of this behavior, in the form of a “bathtub curve”. The analysis is supported by real data of failures. The benefits of using a continuous diagnostics system integrated with the airframe, SHM, is interpreted in relation to the classical approach with the use of non-destructive testing, NDT, for the three phases of the bathtub curve.

  1. Lift and wakes of flying snakes

    CERN Document Server

    Krishnan, Anush; Vlachos, Pavlos P; Barba, L A

    2013-01-01

    Flying snakes use a unique method of aerial locomotion: they jump from tree branches, flatten their bodies and undulate through the air to produce a glide. The shape of their body cross-section during the glide plays an important role in generating lift. This paper presents a computational investigation of the aerodynamics of the cross-sectional shape. We performed two-dimensional simulations of incompressible flow past the anatomically correct cross-section of the species Chrysopelea paradisi, showing that a significant enhancement in lift appears at an angle of attack of 35 degrees, above Reynolds numbers 2000. Previous experiments on physical models also obtained an increased lift, at the same angle of attack. The flow is inherently three-dimensional in physical experiments, due to fluid instabilities, and it is thus intriguing that the enhanced lift appears also in the two-dimensional simulations. The simulations point to the lift enhancement arising from the early separation of the boundary layer on the ...

  2. A Development of the Lifting Tools for 40 .deg. Sector Sub-assembly and ITER Components

    International Nuclear Information System (INIS)

    The lifting tools described in this paper are special tools used to lift and transfer the VV, TFC and pre-assembled 40 .deg sectors at sector sub-assembly tool placed in assembly building from the upending tool to the sector sub-assembly tool or to the Tokamak pit. The lifting tools consists of; the sector lifting tool, which is used universally for the major ITER components, and some lifting attachments for connecting components to the sector lifting tool to meet their lifting configurations. The functions, interfaces, features and configurations of the lifting tools are introduced as a result of their preliminary or final design. The results of the structural analysis to verify the stability of the lifting tools are described as well. The preliminary design of the lifting tools, including the sector lifting tool and associated lifting attachments, have been developed by KODA to satisfy the ITER assembly plan, procedure, environments, interfaces with associated tools or ITER components and technical requirements requested by IO. The structural stability of the lifting tools has been studied using ANSYS with an applied dead weight of the relevant components for example: VV, TFC and 40 .deg sector. For the heaviest load condition, the 40 .deg sector (about 1200 tons), a structural analysis has been carried out and these results are summarized in this paper. Based on the conceptual design proposed by the IO, the preliminary design of the sector lifting tool and associated lifting attachments have been developed to satisfy ITER assembly procedure, technical and functional requirements by KODA. Conclusions are summarized as following. Firstly, the sector lifting tool and associated lifting attachments have been developed by KODA to meet requirements of each lifting configuration for VV, TFC and VV/VVTS/TFC 40 .deg sector in their horizontal and vertical state. And for common use for the lifting of major components like VV and TFC, inboard and outboard cross beams were

  3. The power induced effects module: A FORTRAN code which estimates lift increments due to power induced effects for V/STOL flight

    Science.gov (United States)

    Sandlin, Doral R.; Howard, Kipp E.

    1991-01-01

    A user friendly FORTRAN code that can be used for preliminary design of V/STOL aircraft is described. The program estimates lift increments, due to power induced effects, encountered by aircraft in V/STOL flight. These lift increments are calculated using empirical relations developed from wind tunnel tests and are due to suckdown, fountain, ground vortex, jet wake, and the reaction control system. The code can be used as a preliminary design tool along with NASA Ames' Aircraft Synthesis design code or as a stand-alone program for V/STOL aircraft designers. The Power Induced Effects (PIE) module was validated using experimental data and data computed from lift increment routines. Results are presented for many flat plate models along with the McDonnell Aircraft Company's MFVT (mixed flow vectored thrust) V/STOL preliminary design and a 15 percent scale model of the YAV-8B Harrier V/STOL aircraft. Trends and magnitudes of lift increments versus aircraft height above the ground were predicted well by the PIE module. The code also provided good predictions of the magnitudes of lift increments versus aircraft forward velocity. More experimental results are needed to determine how well the code predicts lift increments as they vary with jet deflection angle and angle of attack. The FORTRAN code is provided in the appendix.

  4. ENFICA-FC: Design of transport aircraft powered by fuel cell & flight test of zero emission 2-seater aircraft powered by fuel cells fueled by hydrogen

    OpenAIRE

    Cestino, Enrico; Borello, Fabio; Romeo, Giulio

    2013-01-01

    Fuel cells could become the main power source for small general aviation aircraft or could replace APU and internal sub-systems on larger aircraft, to obtain all-electric or more-electric air vehicles. There are several potential advantages of using such a power source, that range from environmental and economic issues to performance and operability aspects. A preliminary design is reported. Also, the paper contains a description of testing activities related to experimental flights of an all...

  5. ANALYSIS OF VIBROACOUSTIC SIGNALS RECORDED IN THE PASSENGER LIFT CABIN

    Directory of Open Access Journals (Sweden)

    Kamil Szydło

    2016-06-01

    Full Text Available The analysis of private tests is presented in the article. The applicable tests refer to accelerations, the level of the sound pressure as well as to the sound power emitted by the passenger lift cabin at different technical conditions of the lift. For a group of lifting devices the accelerations were tested at three axes with the use of an accelerometer. The accelerometer was placed in the central part of the cabin with simultaneous measurement of the acoustic parameters with the sound analyzer equipped with the sound volume double microphone probe. The attempt was made to determine the impact of the frame - cabin system construction as well as the lift technical condition on the recorded parameters. It can allow to establish the limit values of the lift structure parameters under which a rapid drop of comfort takes place while travelling in the lift as well as to indicate those construction elements the modification of which would affect the improvement of the operation noiselessness.

  6. Feasibility study of modern airships, phase 1. Volume 2: Parametric analysis (task 3). [lift, weight (mass)

    Science.gov (United States)

    Lancaster, J. W.

    1975-01-01

    Various types of lighter-than-air vehicles from fully buoyant to semibuoyant hybrids were examined. Geometries were optimized for gross lifting capabilities for ellipsoidal airships, modified delta planform lifting bodies, and a short-haul, heavy-lift vehicle concept. It is indicated that: (1) neutrally buoyant airships employing a conservative update of materials and propulsion technology provide significant improvements in productivity; (2) propulsive lift for VTOL and aerodynamic lift for cruise significantly improve the productivity of low to medium gross weight ellipsoidal airships; and (3) the short-haul, heavy-lift vehicle, consisting of a simple combination of an ellipsoidal airship hull and existing helicopter componentry, provides significant potential for low-cost, near-term applications for ultra-heavy lift missions.

  7. Motor of Lift RSG-GAS Performance Analysis after Repair

    International Nuclear Information System (INIS)

    The out of order an equipment is ordinary natural process happened, above all the equipment be used continually with very old time, as for as out of order can be resulted from kinds of cause. Lift motor out of order can be result by motor is broken or happened the body shorten then affected do not function it the lift, so until done rewinding process. The rewinding is furl to repeat at motor coils. Motor of Lift represent main activator machine turning around shares pulley. Lift Motor will work if there is called in normal operation condition or the moment manual switch if done maintenance. Motor used at lift is motor three phases with two speeds that is low speed and high speed. Rewinding process must be done removed the motor from Lift machine and have to be done by professional workshop. In during function test take place, temperature at coil reach 70oC (exceeding boundary permitted). After done installation addition thermal at motor coil hence his temperature become normal that is only reach 50 oC. (author)

  8. Effects of wing lift and weight on landing-gear loads

    Science.gov (United States)

    Lindquist, Dean C

    1952-01-01

    The effects of wing lift and weight on maximum landing gear loads were investigated by drop testing a small landing gear with oleo shock strut in the Langley impact basin. Lift forces were mechanically applied to the dropping mass to produce wing lift factors between 1000 and 2500 pounds. The results show the relationship between lift force, weight, and landing-gear loads for a range of vertical velocities between 0 and 12 feet per second.

  9. Experimental Investigation of Gas-Lift Use in Nuclear Reactors

    International Nuclear Information System (INIS)

    This work briefly describes the selection of type of a two-phase flow, suitable for intensifying of a natural flow of nuclear reactors with liquid fuel – cooling mixture molten salts and the description of a „Two-phase flow demonstrator“ (TFD) used for experimental study of the „gas-lift“ system, and its influence on the support of natural convection. The experimental device works with water and the air is used as a gas. The used perspex limits the temperature to 60°C. There are stated relations for the description of a natural flow in model device and relations for determination of suitable liquid/gas ratio of the gas-lift in the study. There is described the measuring device and the application of the TFD sensor. The flow rate of water is measured by the induction flow meter that gives a voltage signal, which is brought into a computer for processing. Measuring of the velocity distribution and the size of the bubbles is performed by using the PIV method (Particle Image Velocimetry). There was created a model of dispersive bubble flow for application in nuclear reactors. The basic calculation is performed by using the homogeneous flow, where is considered, that the velocity of the fluid and the gas is equal and there is measured the relative share of the gas in homogeneous mixture with the fluid for this case. There are considered the temperature, pressure and flow rate velocity changes of the fluid and gas in the gas-lift cylinder and their influence on the size and velocity of the bubbles for the heat and mass transport of this mixture by the gas-lift cylinder. (author)

  10. NUMERICAL MODELING AND DYNAMIC SIMULATIONS OF NONLINEAR AEROTHERMOELASTIC OF A DOUBLE-WEDGE LIFTING SURFACE

    Directory of Open Access Journals (Sweden)

    ARIF A. EBRAHEEM AL-QASSAR

    2008-12-01

    Full Text Available The design of the re-entry space vehicles and high-speed aircrafts requires special attention to the nonlinear thermoelastic and aerodynamic instabilities of their structural components. The thermal effects are important since temperature environment influences significantly the static and dynamic behaviors of flight structures in supersonic/hypersonic regimes. To contribute to the understanding of dynamic behavior of these “hot” structures, a double-wedge lifting surface with combined freeplay and cubic stiffening structural nonlinearities in both plunging and pitching degrees-of-freedom operating in supersonic/hypersonic flight speed regimes has been analyzed. A third order Piston Theory Aerodynamics is used to evaluate the applied nonlinear unsteady aerodynamic loads. The loss of torsional stiffness that may be incurred by lifting surfaces subjected to axial stresses induced by aerodynamic heating is also considered. The aerodynamic heating effect is estimated based on the adiabatic wall temperature due to high speed airstreams. Modelling issues as well as simulation results have been presented and pertinent conclusions outlined. It is highlighted that a serious loss of torsional stiffness may induce the dynamic instability of the lifting surfaces. The influence of various parameters such as flight condition, thickness ratio, freeplays and pitching stiffness nonlinearity are also discussed.

  11. Conversion of the dual training aircraft (DC into single control advanced training aircraft (SC. Part I

    Directory of Open Access Journals (Sweden)

    Ioan ŞTEFĂNESCU

    2011-03-01

    Full Text Available Converting the DC school jet aircraft into SC advanced training aircraft - and use them forthe combat training of military pilots from the operational units, has become a necessity due to thebudget cuts for Air Force, with direct implications on reducing the number of hours of flight assignedto operating personnel for preparing and training.The purpose of adopting such a program is to reduce the number of flight hours allocated annuallyfor preparing and training in advanced stages of instruction, for every pilot, by more intensive use ofthis type of aircraft, which has the advantage of lower flight hour costs as compared to a supersoniccombat plane.

  12. Tornado lift

    CERN Document Server

    Ivanchin, Alexander

    2010-01-01

    It is shown that one of the causes for tornado is Tornado Lift. At increasing vortex diameter its kinetic energy decreases to keep the moment of momentum constant. A kinetic energy gradient of such vortex is Tornado Lift. Evaluation shows that contribution of Tornado Lift in air lifting in a tornado is comparable to buoyancy according to the order of magnitude.

  13. Hoisting facility for lifting/descent maneuvers of storage container lids on the fabrication line and inside the stand-by repository

    International Nuclear Information System (INIS)

    The storage containers for intermediate storing of CANDU spent nuclear fuel are nuclear equipment composed of two main sub-assemblies: the lid in the shape of a cylindrical bell and the container assembly provided with a special structure allowing positioning 60 fuel clusters into a grid. The masses of these components are too large to be manually maneuvered on the fabrication line what led to design and execution of devices driven by means of hoisting facilities. Thus, the lid of the storage container the mass of which amounts up to 250 Kg is manipulated during machining operations by means of a special device allowing both blocking and lifting as well as descending and unblocking in safe conditions for both personnel and the geometrical parameters of the lid. Blocking / unblocking of the facility against the lid is achieved by the manual positioning of the lifting facility hook in each of the two lifting rings which the facility is provided with. The technical characteristics of the facility are: - lifting load, 250 kg; - external diameter, 1132 mm; - height, 686 mm; - functioning position, vertical; - own weight, 270 kg. A photo is given showing the device with the container lid in the state 'blocked', freely suspended

  14. 75 FR 17754 - Certificate of Alternative Compliance for the Lift Boat GARY CHIASSON ELEVATOR

    Science.gov (United States)

    2010-04-07

    ... SECURITY Coast Guard Certificate of Alternative Compliance for the Lift Boat GARY CHIASSON ELEVATOR AGENCY... Compliance was issued for the lift boat GARY CHIASSON ELEVATOR as required by 33 U.S.C. 1605(c) and 33 CFR 81... Regulations, Parts 81 and 89, has been issued for the lift boat GARY CHIASSON ELEVATOR. The Certificate...

  15. KAPPEL Propeller. Development of a Marine Propeller with Non-planar Lifting Surfaces

    DEFF Research Database (Denmark)

    Kappel, J.; Andersen, Poul

    2002-01-01

    The principle of non-planar lifting surfaces is applied to the design of modern aircraft wings to obtain better lift to drag ratios. Whereas a pronounced fin or "winglet" at the wingtip has been developed for aircraft, the application of the non-planar principle to marine propellers, dealt with in...... this paper, has led to the KAPPEL propeller with blades curved towards the suction side integrating the fin or winglet into the propeller blade. The combined theoretical, experimental and practical approach to develop and design marine propellers with non-planar lifting surfaces has resulted in...... propellers with higher efficiency and lower levels of noise and vibration excitation compared to conventional propellers designed for the same task. Conventional and KAPPEL propellers have been compared for a medium sized container ship and a product tanker. In total nine of these unconventional and two...

  16. HYDRODYNAMIC BEHAVIOR AND ABSORPTION OF CARBON DIOXIDE BY CHEMICAL REACTION WITH GLUCOSAMINE IN AN AIR-LIFT REACTOR

    OpenAIRE

    Alicia García-Abuín; Diego Gómez-Díaz; Navaza, José M.; Isabel Vidal-Tato

    2010-01-01

    In this work, it has been studied the behavior of aqueous solutions of glucosamine used as absorbent phase in the carbon dioxide capture process using an air-lift reactor. The experimental results indicate that the reagent (glucosamine) shows a similar behavior related to absorption rate, than previously observed for aqueous solutions of other amines widely used for carbon dioxide capture. The value of mass transfer rate has been determined, as well as the effect of these operation conditions...

  17. Short-term variation of cosmic radiation measured by aircraft under constant flight conditions

    Science.gov (United States)

    Lee, Jaejin; Nam, Uk-Won; Pyo, Jeonghyun; Kim, Sunghwan; Kwon, Yong-Jun; Lee, Jaewon; Park, Inchun; Kim, Myung-Hee Y.; Dachev, Tsventan P.

    2015-11-01

    The temporal variations in cosmic radiation on aircraft under constant flight conditions were measured by a Liulin detector. Rather than a commercial long-distance aircraft, we used a military reconnaissance aircraft performing a circular flight at a constant altitude over the Korean Peninsula. At 9144 m (30,000 ft), the mean and standard deviation of the radiation dose rate (among 35 measurements) was 2.3 and 0.17 μSv/h, respectively. The experiment yielded two observational results. First, the dose rate changed over a flight time of 5-7 h; second, no strong correlation was revealed between the cosmic rays observed from the ground-based neutron monitor and the radiation doses at aircraft altitude. These observations can provide insight into the short-term variation of cosmic radiation at aviation altitudes. When discarding various negligible factors, it is postulated that the changes in the geomagnetic field and the air density still could affect the variation of cosmic radiation at aircraft altitude. However, various factors are less known about the dependence on the cosmic radiation. Therefore, investigations of possible factors are also warranted at the monitoring points of space weather.

  18. Lifts of projective congruence groups, II

    DEFF Research Database (Denmark)

    Kiming, Ian

    2014-01-01

    We continue and complete our previous paper ``Lifts of projective congruence groups'' concerning the question of whether there exist noncongruence subgroups of  that are projectively equivalent to one of the groups  or . A complete answer to this question is obtained: In case of  such noncongruence...

  19. Wingless Flight: The Lifting Body Story

    Science.gov (United States)

    Reed, R. Dale; Lister, Darlene (Editor); Huntley, J. D. (Editor)

    1997-01-01

    Wingless Flight tells the story of the most unusual flying machines ever flown, the lifting bodies. It is my story about my friends and colleagues who committed a significant part of their lives in the 1960s and 1970s to prove that the concept was a viable one for use in spacecraft of the future. This story, filled with drama and adventure, is about the twelve-year period from 1963 to 1975 in which eight different lifting-body configurations flew. It is appropriate for me to write the story, since I was the engineer who first presented the idea of flight-testing the concept to others at the NASA Flight Research Center. Over those twelve years, I experienced the story as it unfolded day by day at that remote NASA facility northeast of los Angeles in the bleak Mojave Desert. Benefits from this effort immediately influenced the design and operational concepts of the winged NASA Shuttle Orbiter. However, the full benefits would not be realized until the 1990s when new spacecraft such as the X-33 and X-38 would fully employ the lifting-body concept. A lifting body is basically a wingless vehicle that flies due to the lift generated by the shape of its fuselage. Although both a lifting reentry vehicle and a ballistic capsule had been considered as options during the early stages of NASA's space program, NASA initially opted to go with the capsule. A number of individuals were not content to close the book on the lifting-body concept. Researchers including Alfred Eggers at the NASA Ames Research Center conducted early wind-tunnel experiments, finding that half of a rounded nose-cone shape that was flat on top and rounded on the bottom could generate a lift-to-drag ratio of about 1.5 to 1. Eggers' preliminary design sketch later resembled the basic M2 lifting-body design. At the NASA Langley Research Center, other researchers toyed with their own lifting-body shapes. Meanwhile, some of us aircraft-oriented researchers at the, NASA Flight Research Center at Edwards Air

  20. Lifts of convex sets and cone factorizations

    CERN Document Server

    Gouveia, João; Thomas, Rekha

    2011-01-01

    In this paper we address the basic geometric question of when a given convex set is the image under a linear map of an affine slice of a given closed convex cone. Such a representation or 'lift' of the convex set is especially useful if the cone admits an efficient algorithm for linear optimization over its affine slices. We show that the existence of a lift of a convex set to a cone is equivalent to the existence of a factorization of an operator associated to the set and its polar via elements in the cone and its dual. This generalizes a theorem of Yannakakis that established a connection between polyhedral lifts of a polytope and nonnegative factorizations of its slack matrix. Symmetric lifts of convex sets can also be characterized similarly. When the cones live in a family, our results lead to the definition of the rank of a convex set with respect to this family. We present results about this rank in the context of cones of positive semidefinite matrices. Our methods provide new tools for understanding ...

  1. Generation of transparent conductive electrodes by laser consolidation of LIFT printed ITO nanoparticle layers

    Science.gov (United States)

    Baum, M.; Kim, H.; Alexeev, I.; Piqué, A.; Schmidt, M.

    2013-06-01

    Indium tin oxide (ITO) is one of the few materials available that display a high transparency in the visible wavelength region and at the same time can conduct electrical currents. Thus it is widespread in many optoelectronic applications such as displays or solar cells. Layers of this material are commonly deposited by vacuum deposition methods which are not compatible with inexpensive production methods such as roll-to-roll processing or printed electronics in general. In this work, we demonstrate the generation of arbitrarily shaped ITO layers by laser induced forward transfer of ITO nanoparticles. The transferred particle ink volumes range in the sub picoliter regime. Feature sizes as small as 20 μm are produced without any outward flow or "coffee-stain" effects. Furthermore, the feasibility of excimer laser consolidation of these nanoparticulate layers in ambient air for the generation of dense ITO films is shown. Conductivities of over 4000 Ω-1 m-1 were achieved. The presented methods are a promising alternative for the generation of transparent conducting layers for the inexpensive production of optoelectronics.

  2. Several Different Types of Compressed Garbage Truck Hopper Lifting Locking Mechanism%垃圾压缩车料斗举升锁紧机构的几种不同型式

    Institute of Scientific and Technical Information of China (English)

    彭海鸿

    2014-01-01

    Compression type garbage truck is used for the special purpose vehicle collection, compression and transport garbage, commonly used at home and abroad. The hopper lifting locking in a variety of ways, this paper introduces several different types of compressed garbage truck hopper lifting locking mechanism for reference.%压缩式垃圾车是用于收集、压缩和运输生活垃圾的专用汽车,在国内外普遍使用。其料斗举升锁紧方式多种多样,介绍几种不同方式,以备同行参考。

  3. Assessment of aircraft noise sources variability using an acoustic camera

    NARCIS (Netherlands)

    Snellen, M.; Merino Martinez, R.; Simons, D.G.

    2015-01-01

    Noise assessment around airports is hampered due to the observed large variability in noise levels for fly-overs of the same aircraft type, which is not considered by the current models. This paper assumes that the noise variability is due to variations in the aircraft emitted noise, neglecting the

  4. Lifting operations and lifting equipment

    NARCIS (Netherlands)

    Douwes, M.

    2013-01-01

    Lifting operations are inherent to many occupations in the construction industry. They can be performed manually or using lifting equipment. Both manual lifting and mechanical lifting operations can put construction workers at great risk of injury or health symptoms causing sick leave or disability.

  5. Reynolds-Number Scaling Effects on the EUROPEAN High Lift Configurations

    OpenAIRE

    Rudnik, R.; Germain, Eric

    2009-01-01

    Within the European High-Lift projects I and II, extensive experimental and numerical investigations on the aerodynamics of high-lift configurations have been carried out. The studies are conducted using the KH3Y windtunnel model DLR F11, which is representative of a wide-body commercial aircraft. A step-by-step complexity increase up to a complete high-lift configuration, including pylon, nacelle, and nacelle strake, is carried out to identify and separate the lift and drag behavior for the ...

  6. Friction characteristics of 20 x 4.4, type 7, aircraft tires constructed with different tread rubber compounds

    Science.gov (United States)

    Dreher, R. C.; Yager, T. J.

    1976-01-01

    A test program was conducted at the Langley aircraft landing loads and traction facility to evaluate the friction characteristics of 20 x 4.4, type, aircraft tires constructed with experimental cut-resistant, tread rubber compounds. These compounds consisted of different blends of natural rubber (NR) and an alfin catalyzed styrene-butadiene copolymer rubber (SBR). One tire having a blend of 30 SBR and 70 NR and another having a blend of 60 SBR and 40 NR in the tread were tested together with a standard production tire with no SBR content in the tread rubber. The results of this investigation indicated that the test tires constructed with the special cut-resistant tread rubber compositions did not suffer any significant degradation in tire friction capability when compared with the standard tire. In general, tire friction capability decreased with increasing speed and surface wetness condition. As yaw angle increased, tire braking capability decreased while tire cornering capability increased. Tread-wear data based on number of brake cycles, however, suggested that the tires with alfin SBR blends experienced significantly greater wear than the standard production tire.

  7. Aircraft Electric/Hybrid-Electric Power and Propulsion Workshop Perspective of the V/STOL Aircraft Systems Tech Committee

    Science.gov (United States)

    Hange, Craig E.

    2016-01-01

    This presentation will be given at the AIAA Electric Hybrid-Electric Power Propulsion Workshop on July 29, 2016. The workshop is being held so the AIAA can determine how it can support the introduction of electric aircraft into the aerospace industry. This presentation will address the needs of the community within the industry that advocates the use of powered-lift as important new technologies for future aircraft and air transportation systems. As the current chairman of the VSTOL Aircraft Systems Technical Committee, I will be presenting generalized descriptions of the past research in developing powered-lift and generalized observations on how electric and hybrid-electric propulsion may provide advances in the powered-lift field.

  8. Gas and hydrogen isotopic analyses of volcanic eruption clouds in Guatemala sampled by aircraft

    Science.gov (United States)

    Rose, W.I., Jr.; Cadle, R.D.; Heidt, L.E.; Friedman, I.; Lazrus, A.L.; Huebert, B.J.

    1980-01-01

    Gas samples were collected by aircraft entering volcanic eruption clouds of three Guatemalan volcanoes. Gas chromatographic analyses show higher H2 and S gas contents in ash eruption clouds and lower H2 and S gases in vaporous gas plumes. H isotopic data demonstrate lighter isotopic distribution of water vapor in ash eruption clouds than in vaporous gas plumes. Most of the H2O in the vaporous plumes is probably meteoric. The data are the first direct gas analyses of explosive eruptive clouds, and demonstrate that, in spite of atmospheric admixture, useful compositional information on eruptive gases can be obtained using aircraft. ?? 1980.

  9. Combined Effect of Aircraft Noise and Pollutant Emissions by using ANN Model to Determine Healthy Risk Level

    OpenAIRE

    SETIA KURNIAWAN, Jermanto; KATILI, Irwan; MOERSIDIK, Setyo Sarwanto; Khardi, Salah

    2013-01-01

    Aircraft noise and pollutant emissions are an important part of the sources of pollution around airport that directly or indirectly will affect harmful to human health and ecosystems. The effects of aircraft noise and emissions on the populations around airport are deal with annoying and sometimes dangerous. In order to address this issue, the research propose an integrating model of aircraft noise and pollutant emissions by combining effects of both noise and pollutant emissions using Artifi...

  10. Effective density measurements of fresh particulate matter emitted by an aircraft engine

    Science.gov (United States)

    Abegglen, Manuel; Durdina, Lukas; Mensah, Amewu; Brem, Benjamin; Corbin, Joel; Rindlisbacher, Theo; Wang, Jing; Lohmann, Ulrike; Sierau, Berko

    2014-05-01

    Introduction Carbonaceous particulate matter (commonly referred to as soot), once emitted into the atmosphere affects the global radiation budget by absorbing and scattering solar radiation. Furthermore, it can alter the formation, lifetime and distribution of clouds by acting as cloud condensation nuclei (CCN) or ice nuclei (IN). The ability of soot particles to act as CCN and IN depends on their size, morphology and chemical composition. Soot particles are known to consist of spherical, primary particles that tend to arrange in chain-like structures. The structure of soot particles typically changes in the atmosphere when the particles are coated with secondary material, thus changing their radiative and cloud microphysical properties. Bond et al. (Journal of Geophysical Research, 2013: Bounding the Role of Black Carbon in the Climate System.) estimated the total industrial-era (1750 to 2005) climate forcing of black carbon to be 1.1 W/m2 ranging from the uncertainty bonds of 0.17 W/m2 to 2.1 W/m2. Facing the large uncertainty range, there is a need for a better characterization of soot particles abundant in the atmosphere. We provide experimental data on physical properties such as size, mass, density and morphology of freshly produced soot particles from a regularly used aircraft engine and from four laboratory generated soot types. This was done using a Differential Mobility Analyzer (DMA) and a Centrifugal Particle Mass Analyzer (CPMA), a relatively new instrument that records mass distributions of aerosol particles. Experimental Aircraft engine exhaust particles were collected and analysed during the Aviation Particle Regulatory Instrumentation Demonstration Experiments (A-PRIDE) campaigns in a test facility at the Zurich airport in November 2012 and August 2013. The engines were operated at different relative thrust levels spanning 7 % to 100 %. The sample was led into a heated line in order to prevent condensation of water and evolution of secondary

  11. Volume reduction of radiocesium-contaminated soil by air-lift washing process. Demonstration studies in Iitate and Kawauchi village

    International Nuclear Information System (INIS)

    A small system was developed for volume reduction of radiocesium-contaminated soils. Included in this system was a 100-L air-lift washing chamber, a coagulation tank, and a dewatering apparatus. Soil samples (137Cs 6.2 x 103 - 1.9 x 104 Bq/kg) collected from a parking area in Iitate village, Fukushima Prefecture were put through this soil washing chamber. Results showed that 14-17% (dry weight) of the soil particles were ideally recovered with 75-86% of 137Cs (3.0 x 104 - 7.4 x 104 Bq/kg). Soil samples collected from an area with bamboo bushes, showed that 53-55% of the soil particle's weight were recovered with 87-89% of 137Cs (3.0 x 104 - 7.4 x 104 Bq/kg). Soil samples collected from a farm load and ditch in Kawauchi village (1.0 x 103 - 7.3 x 103 Bq/kg) were treated by soil washing, coagulation, and dewatering in series. Results showed that 10-14% weight of the soil particles were recovered as dewatered cake (4.4 x 103 - 3.1 x 104 Bq/kg) with only 43-46% of 137Cs. These results confirm soil-characteristic-dependency from the volume reduction efficiency of radiocesium-contaminated soils. (author)

  12. Numerical analysis of drag and lift reduction of square cylinder

    Directory of Open Access Journals (Sweden)

    Prasenjit Dey

    2015-12-01

    Full Text Available Flow around an extended triangular solid (thorn attached to a square cylinder is investigated numerically. The numerical analysis is carried out at low Reynolds number, Re = 100 & 180 for different non-dimensional thorn lengths (l΄ = 0. 2, 0.4 & 0.6, different inclination angles (θ = 5°, 10°, 15° and 20° and two different thorn positions. It is found that drag and lift reduction can be achieved by attaching the thorn on a square cylinder. It is observed that the fluctuation of the drag force as well as the lift force is reduced and there is a comparatively large variation of drag and lift when the thorn is placed at the front stagnation point instead of placing at rear stagnation point. The reduction of drag and lift coefficient are directly proportional to thorn length and thorn inclination angle. It is found that the drag and lift are minimized by 16% & 46% for Re = 100 respectively, and 22% & 60% for Re = 180 compared to a square model (without thorn.

  13. Thermodynamic correction of particle concentrations measured by underwing probes on fast flying aircraft

    Science.gov (United States)

    Weigel, R.; Spichtinger, P.; Mahnke, C.; Klingebiel, M.; Afchine, A.; Petzold, A.; Krämer, M.; Costa, A.; Molleker, S.; Jurkat, T.; Minikin, A.; Borrmann, S.

    2015-12-01

    Particle concentration measurements with underwing probes on aircraft are impacted by air compression upstream of the instrument body as a function of flight velocity. In particular for fast-flying aircraft the necessity arises to account for compression of the air sample volume. Hence, a correction procedure is needed to invert measured particle number concentrations to ambient conditions that is commonly applicable for different instruments to gain comparable results. In the compression region where the detection of particles occurs (i.e. under factual measurement conditions), pressure and temperature of the air sample are increased compared to ambient (undisturbed) conditions in certain distance away from the aircraft. Conventional procedures for scaling the measured number densities to ambient conditions presume that the particle penetration speed through the instruments' detection area equals the aircraft speed (True Air Speed, TAS). However, particle imaging instruments equipped with pitot-tubes measuring the Probe Air Speed (PAS) of each underwing probe reveal PAS values systematically below those of the TAS. We conclude that the deviation between PAS and TAS is mainly caused by the compression of the probed air sample. From measurements during two missions in 2014 with the German Gulfstream G-550 (HALO - High Altitude LOng range) research aircraft we develop a procedure to correct the measured particle concentration to ambient conditions using a thermodynamic approach. With the provided equation the corresponding concentration correction factor ξ is applicable to the high frequency measurements of each underwing probe which is equipped with its own air speed sensor (e.g. a pitot-tube). ξ-values of 1 to 0.85 are calculated for air speeds (i.e. TAS) between 60 and 260 m s-1. From HALO data it is found that ξ does not significantly vary between the different deployed instruments. Thus, for the current HALO underwing probe configuration a parameterisation of

  14. Laser-induced forward transfer (LIFT) of congruent voxels

    Science.gov (United States)

    Piqué, Alberto; Kim, Heungsoo; Auyeung, Raymond C. Y.; Beniam, Iyoel; Breckenfeld, Eric

    2016-06-01

    Laser-induced forward transfer (LIFT) of functional materials offers unique advantages and capabilities for the rapid prototyping of electronic, optical and sensor elements. The use of LIFT for printing high viscosity metallic nano-inks and nano-pastes can be optimized for the transfer of voxels congruent with the shape of the laser pulse, forming thin film-like structures non-lithographically. These processes are capable of printing patterns with excellent lateral resolution and thickness uniformity typically found in 3-dimensional stacked assemblies, MEMS-like structures and free-standing interconnects. However, in order to achieve congruent voxel transfer with LIFT, the particle size and viscosity of the ink or paste suspensions must be adjusted to minimize variations due to wetting and drying effects. When LIFT is carried out with high-viscosity nano-suspensions, the printed voxel size and shape become controllable parameters, allowing the printing of thin-film like structures whose shape is determined by the spatial distribution of the laser pulse. The result is a new level of parallelization beyond current serial direct-write processes whereby the geometry of each printed voxel can be optimized according to the pattern design. This work shows how LIFT of congruent voxels can be applied to the fabrication of 2D and 3D microstructures by adjusting the viscosity of the nano-suspension and laser transfer parameters.

  15. Evaluation of structure integrity of the lifting handle of CRB

    International Nuclear Information System (INIS)

    Since visual inspection was applied to inspect the control rod blades (CRBs) of nuclear power plants in Taiwan, indications have been found in areas such as roller-pin hole, sheath and tie-rod of CRB. Many preliminary safety analyses with conservative assumptions have been conducted to endorse the continuing operation of the units. The objective of this study is to evaluate the structural integrity of those CRBs during lifting operation. Detailed finite element models of the lifting handle of the CRB are built with emphasis on the postulated crack near the roller-pin hole. Both the D-215 type CRB and the Marathon type CRB are evaluated. It is concluded that the structural integrity is guaranteed even under the worst postulated situation

  16. Shape Design of Lifting body Based on Genetic Algorithm

    OpenAIRE

    Yongyuan Li; Yi Jiang; Chunping Huang

    2010-01-01

    This paper briefly introduces the concept and history of lifting body, and puts forward a new method for the optimization of lifting body. This method has drawn lessons from the die line design of airplane is used to parametric numerical modeling for the lifting body, and extract the characterization of shape parameters as design variables, a combination of lifting body reentry vehicle aerodynamic conditions, aerodynamic heating, volumetric Rate and the stability of performance. Multi-objecti...

  17. Clinical application of palatal lift appliance in velopharyngeal incompetence

    Directory of Open Access Journals (Sweden)

    S Premkumar

    2011-01-01

    Full Text Available The presence of nasal air leak in cleft palate patients with velopharyngeal incompetence leads to characteristic nasal snort. The efficacy of the palatal lift appliance in patients with adequate velopharyngeal tissue with incompetence was tested. Speech quality improved after the wearing of palatal lift appliance. Palatal lift appliances are simple and efficient in reducing the nasal air leak. Ongoing speech therapy is necessary and advised for patients receiving palatal lift.

  18. Connectivity in Random Lifts of Graphs: New Techniques and Results

    OpenAIRE

    Silas, Shashwat

    2016-01-01

    We relate a randomly generated subgroup of the symmetric group on $n$ elements to random $n$-lifts of a graph. We use this relationship to bound the probability that a random $n$-lift of a graph with minimum degree $\\delta$ is $\\delta$-connected (for $\\delta \\ge 5$) and prove several related results. We also study homotopy invariants in random lifts and iterated random lifts.

  19. Advances in Engineering Research : Volume 4, Environmental impacts of the future technologies of commercial aircraft

    OpenAIRE

    Khardi, Salah; KURNIAWAN, J

    2013-01-01

    Assessment of pollutant emissions (CO, HC and NOx) and fuel consumption of aircraft LTO cycles at Soekarno Hatta InternationalAirport is carried out for the first time. We stressed, by aircraft type, the large aircraft which represent the greatest contribution of pollutant emissions in and around this airport.Analysis is performed to precise theirmagnitude in relationship with fuel consumption. Distribution of aircraft pollutants for different operational modes (taxiing and takeoffs) is provi...

  20. Modeling of aircraft pollutant emissions of LTO cycles around Soekarno Hatta international airport

    OpenAIRE

    Khardi, Salah; SETIA KURNIAWAN, Jermanto

    2013-01-01

    Assessment of pollutant emissions (CO, HC and NOx) and fuel consumption of aircraft LTO cycles at Soekarno Hatta InternationalAirport is carried out for the first time. We stressed, by aircraft type, the large aircraft which represent the greatest contribution of pollutant emissions in and around this airport.Analysis is performed to precise theirmagnitude in relationship with fuel consumption. Distribution of aircraft pollutants for different operational modes (taxiing and takeoffs) is provi...

  1. Degradation of tetracycline in aqueous media by ozonation in an internal loop-lift reactor

    International Nuclear Information System (INIS)

    The degradation of tetracycline by ozone was investigated in this paper. In the laboratory scale experiments, the effect of major parameters, including pH, gas flow rate, gaseous ozone concentration, hydrogen peroxide concentration and hydroxyl radical scavenger (tert-butyl alcohol) on the degradation of tetracycline was studied. A pseudo-first order kinetic model was used to simulate the experimental results. The results indicated that the tetracycline degradation rate increased with pH, gaseous ozone concentration and gas flow rate. The addition of hydrogen peroxide or hydroxyl radical scavenger had little effect on tetracycline removal, indicating that the direct oxidation of tetracycline by ozone was dominant process and the radical contribution to the tetracycline oxidation could be neglected. The main intermediates were separated and identified as well as the simple degradation pathway of tetracycline was proposed. The COD removal reached to 35% after 90 min reaction. The acute toxicity experiments illustrated that the Daphnia magna mortality reached the maximum after 25 min ozonation and then decreased to zero after 90 min ozonation.

  2. Degradation of tetracycline in aqueous media by ozonation in an internal loop-lift reactor

    Energy Technology Data Exchange (ETDEWEB)

    Wang Yan [Department of Environmental Engineering, Wuhan University, P.O. Box C319, Luoyu Road 129, Wuhan 430079 (China); Zhang Hui, E-mail: eeng@whu.edu.cn [Department of Environmental Engineering, Wuhan University, P.O. Box C319, Luoyu Road 129, Wuhan 430079 (China); Zhang Jianhua; Lu Chen; Huang Qianqian; Wu Jie; Liu Fang [Department of Environmental Engineering, Wuhan University, P.O. Box C319, Luoyu Road 129, Wuhan 430079 (China)

    2011-08-15

    The degradation of tetracycline by ozone was investigated in this paper. In the laboratory scale experiments, the effect of major parameters, including pH, gas flow rate, gaseous ozone concentration, hydrogen peroxide concentration and hydroxyl radical scavenger (tert-butyl alcohol) on the degradation of tetracycline was studied. A pseudo-first order kinetic model was used to simulate the experimental results. The results indicated that the tetracycline degradation rate increased with pH, gaseous ozone concentration and gas flow rate. The addition of hydrogen peroxide or hydroxyl radical scavenger had little effect on tetracycline removal, indicating that the direct oxidation of tetracycline by ozone was dominant process and the radical contribution to the tetracycline oxidation could be neglected. The main intermediates were separated and identified as well as the simple degradation pathway of tetracycline was proposed. The COD removal reached to 35% after 90 min reaction. The acute toxicity experiments illustrated that the Daphnia magna mortality reached the maximum after 25 min ozonation and then decreased to zero after 90 min ozonation.

  3. Conditional moment closure modeling of a lifted turbulent flame

    Institute of Scientific and Technical Information of China (English)

    JIANG Yong; QIU Rong; ZHOU Wei; FAN Weicheng

    2005-01-01

    Results obtained using conditional moment closure (CMC) approach to modeling a lifted turbulent hydrogen flame are presented. Predictions are based on k-ε-g turbulent closure, a 23-step chemical mechanism and a radially averaged CMC model. The objectives are to find out how radially averaged CMC can represent a lifted flame and which mechanism of flame stabilization can be described by this modeling method. As a first stage of the study of multi-dimensional CMC for large eddy simulation (LES) of the lifted turbulent flames, the effect of turbulence upon combustion is included, the high-order compact finite- difference scheme (Padé) is used and previously developed characteristic-wave-based boundary conditions for multi- component perfect gas mixtures are here extended to their conditional forms but the heat release due to combustion is not part of the turbulent calculations. Attention is focused to the lift-off region of the flame which is commonly considered as a cold flow. Comparison with published experimental data and the computational results shows that the lift-off height can be accurately determined, and Favre averaged radial profiles of temperature and species mole fractions are also reasonably well predicted. Some of the current flame stabilization mechanisms are discussed.

  4. 19 CFR 122.132 - Sealing of aircraft liquor kits.

    Science.gov (United States)

    2010-04-01

    ... 19 Customs Duties 1 2010-04-01 2010-04-01 false Sealing of aircraft liquor kits. 122.132 Section... OF THE TREASURY AIR COMMERCE REGULATIONS Aircraft Liquor Kits § 122.132 Sealing of aircraft liquor kits. (a) Sealing required. Aircraft liquor kits shall be sealed on board the aircraft by...

  5. Determination of standards for transportation of radioactive material by aircrafts

    International Nuclear Information System (INIS)

    The notification is defined under the provisions of the regulations for execution of the aviation law. Terms of exclusive loading and container are explained. Transportable radioactive materials hereunder exclude naturally igniting fluid materials, substances necessary to be contained in vessels which filtrate interior gas with filters or refrigerate contents with cooling devices, etc., or BM loads necessary to be continuously ventilated. Radioactive materials to be conveyed as radioactive loads and L loads are prescribed with tables attached. Technical standards for radioactive loads are stipulated for L, A, BM and BU loads respectively. Confirmation of safety of radioactive loads may be made by examiniation of documents prepared by persons acknowledged proper by the Minister of Transportation. Radioactive materials are uranium 233 and 235, plutonium 238, 239 and 241, their compounds and those materials which include one or more than two of such substances. Materials whose quantities or quantities of components are less than 15 grams and natural or depleted uranium are excluded. The maximum doses of containers with radioactive loads shall not exceed for an hour 200 mili-rem on the surface and 10 mili-rem at a distance of 1 meter from the surface. Confirmation of safety of transport, method of loading, prevention of criticality, restriction of mixed shipment, transport index, signals and others are provided for in detail. (Okada, K.)

  6. Photoresist-Free Patterning by Mechanical Abrasion of Water-Soluble Lift-Off Resists and Bare Substrates: Toward Green Fabrication of Transparent Electrodes

    OpenAIRE

    Adam D Printz; Esther Chan; Celine Liong; Martinez, René S.; Darren J Lipomi

    2013-01-01

    This paper describes the fabrication of transparent electrodes based on grids of copper microwires using a non-photolithographic process. The process--"abrasion lithography"--takes two forms. In the first implementation (Method I), a water-soluble commodity polymer film is abraded with a sharp tool, coated with a conductive film, and developed by immersion in water. Water dissolves the polymer film and lifts off the conductive film in the unabraded areas. In the second implementation (Method ...

  7. North American Pollution Outflow and the Trapping of Convectively Lifted Pollution by Upper-Level Anticyclone

    OpenAIRE

    Li, Qinbin; Jacob, Daniel J.; Park, Rokjin J.; Wang, Yuxuan; Heald, Colette L.; Hudman, Rynda; Yantosca, Robert M.; Martin, Randall V.; Evans, Mathew

    2005-01-01

    We examine the major outflow pathways for North American pollution to the Atlantic in summer by conducting a 4-year simulation with the GEOS-CHEM global chemical transport model, including a coupled ozone-aerosol simulation with 1° × 1° horizontal resolution for summer 2000. The outflow is driven principally by cyclones tracking eastward across North America at 45–55°N, every 5 days on average. Anthropogenic and fire effluents from western North America are mostly transported north and east, ...

  8. Influences on lifetime of wire ropes in traction lifts

    Science.gov (United States)

    Vogel, W.

    2016-05-01

    Traction lifts are complex systems with rotating and translating moving masses, springs and dampers and several system inputs from the lifts and the users. The wire ropes are essential mechanical elements. The mechanical properties of the ropes in use depend on the rope construction, the load situation, nonlinearities and the lift dimensions. The mechanical properties are important for the proper use in lifts and the ride quality. But first of all the wire ropes (for all other suspension means as well) have to satisfy the safety relevant requirements sufficient lifetime, reliable determination of discard and sufficient and limited traction capacity. The lifetime of the wire ropes better the number of trips until rope discard depends on a lot of parameters of the rope and the rope application eg use of plastic deflection sheaves and reverse bending layouts. New challenges for rope lifetime are resulting from the more or less open D/d-ratio limits possible by certificates concerning the examination of conformity by notified bodies. This paper will highlight the basics of wire rope technology, the endurance and lifetime of wire ropes running over sheaves, and the different influences from the ropes and more and more important from the lift application parameters. Very often underestimated are the influences of transport, storage, installation and maintenance. With this background we will lead over to the calculation methods of wire rope lifetime considering the actual findings of wire rope endurance research. We'll show in this paper new and innovative facts as the influence of rope length and size factor in the lifetime formular, the reduction of lifetime caused by traction grooves, the new model for the calculation in reverse bending operations and the statistically firmed possibilities for machine roomless lifts (MRL) under very small bending conditions.

  9. 14 CFR 23.369 - Rear lift truss.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Rear lift truss. 23.369 Section 23.369 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT AIRWORTHINESS... lift truss. (a) If a rear lift truss is used, it must be designed to withstand conditions of...

  10. Policy and the evaluation of aircraft noise

    NARCIS (Netherlands)

    Kroesen, M.; Molin, E.J.E.; Van Wee, G.P.

    2010-01-01

    In this paper, we hypothesize and test the ideas that (1) people’s subjectivity in relation to aircraft noise is shaped by the policy discourse, (2) this results in a limited number of frames towards aircraft noise, (3) the frames inform people how to think and feel about aircraft noise and (4) the

  11. Design and Performance of Lift-Offset Rotorcraft for Short-Haul Missions

    Science.gov (United States)

    Johnson, Wayne; Moodie, Alex M.; Yeo, Hyeonsoo

    2012-01-01

    The design and performance of compound helicopters utilizing lift-offset rotors are examined, in the context of short-haul, medium-size civil and military missions. The analysis tools used are the comprehensive analysis CAMRAD II and the sizing code NDARC. Following correlation of the comprehensive analysis with existing lift-offset aircraft flight test data, the rotor performance model for the sizing code was developed, and an initial estimate was made of the rotor size and key hover and cruise flight conditions. The rotor planform and twist were optimized for those conditions, and the sizing code rotor performance model updated. Two models for estimating the blade and hub weight of lift-offset rotors are discussed. The civil and military missions are described, along with the aircraft design assumptions. The aircraft are sized for 30 passengers or 6600 lb payload, with a range of 300 nm. Civil and military aircraft designs are described for each of the rotor weight models. Disk loading and blade loading were varied to optimize the designs, based on gross weight and fuel burn. The influence of technology is shown, in terms of rotor hub drag and rotor weight.

  12. Digital Mobile Planetarium: Lifting astronomical concepts presented by teachers in the city of Caraguatatuba, Brazil

    Science.gov (United States)

    Voelzke, Marcos Rincon; Pereira Gonzaga, Edson

    2015-08-01

    In this work, a survey of alternative conceptions about basic concepts of Astronomy was carried out on the North Coast of São Paulo with 478 people, visitors of the Digital Mobile Planetarium (DMP). Rodolfo Langhi’s thought about alternative conceptions (2005), considered very important, was the base for this study, choosen because it allows to identify these concepts before the intervention methodology, which renders possible to prepare contextualized presentations and helps to propose to teachers - and consequently to students - to compare what they already know with the new information obtained in the sessions at the DMP of the University Cruzeiro do Sul. This is a case study with a quantitative survey and a qualitative analysis of data on astronomical concepts collected through a questionnaire.

  13. Study optimizes gas lift in Gulf of Suez field

    Energy Technology Data Exchange (ETDEWEB)

    Abdel-Waly, A.A. [King Saud Univ., Riyadh (Saudi Arabia); Darwish, T.A.; Osman Salama, A. [Cairo Univ., Giza (Egypt); El-Naggar, M. [Gulf of Suez Petroleum Co., Cairo (Egypt)

    1996-06-24

    A study using PVT data combined with fluid and multiphase flow correlations optimized gas lift in the Ramadan field, Nubia C, oil wells, in the Gulf of Suez. Selection of appropriate correlations followed by multiphase flow calculations at various points of injection (POI) were the first steps in the study. After determining the POI for each well from actual pressure and temperature surveys, the study constructed lift gas performance curves for each well. Actual and optimum operating conditions were compared to determine the optimal gas lift. The study indicated a net 2,115 bo/d could be gained from implementing its recommendations. The actual net oil gained as a result of this optimization and injected gas reallocation was 2,024 bo/d. The paper discusses the Ramadan field, fluid properties, multiphase flow, production optimization, and results.

  14. Wiener-Process-Type Evasive Aircraft Actions are Indeed Optimal Against Anti-Aircraft Guns: Wiener's Data Revisited

    OpenAIRE

    V. Kreinovieh; О. Kosheleva

    2015-01-01

    In his 1940s empirical study of evasive aircraft actions, N. Wiener, the father of cybernetics, found out that the pilot’s actions follow a Wienertype-process. In this paper, we explain this empirical result by showing that such evasive actions are indeed optimal against the 1940s anti-aircraft guns.

  15. An investigation of team lifting using psychophysical methods

    OpenAIRE

    Lee, Suzanne Elin

    1995-01-01

    Lifting is one of the major causes of back injury in the workplace. Often, workers are told to ask for the help of another worker when the load is too great to be lifted alone, yet the effects of these team lifts have not been researched until recently. This experiment investigated some of the variables which may affect the results of team lifting tasks. The psychophysical methodology has been used for almost 30 years in trying to determine the maximum acceptable weight of lift...

  16. Shock-Assisted Superficial Hexagonal-to-Cubic Phase Transition in GaN/Sapphire Interface Induced by Using Ultra-violet Laser Lift-Of Techniques

    International Nuclear Information System (INIS)

    Ultra-violet (KrF excimer laser, λ = 248 nm) laser lift-of (LLO) techniques have been operated to the GaN/sapphire structure to separate GaN from the sapphire substrate. Hexagonal to cubic phase transformation induced by the ultra-violet laser lift-of (UV-LLO) has been characterized by micro-Raman spectroscopy, micro-photoluminescence, along with high-resolution transmission electron microscopy (HRTEM). HRTEM indicates that UV-LLO induced phase transition takes place above the LLO interface, without phase transition under the LLO interface. The formed cubic GaN often exists as nanocrystal grains attaching on the bulk hexagonal GaN. The half-loop-cluster-like UV-LLO interface indicates that the LLO-induced shock waves has generated and played an assistant role in the decomposition of the hexagonal GaN and in the formation of cubic GaN grains at the LLO surface

  17. Monitoring and forecasting of great radiation hazards for spacecraft and aircrafts by online cosmic ray data

    International Nuclear Information System (INIS)

    We show that an exact forecast of great radiation hazard in space, in the magnetosphere, in the atmosphere and on the ground can be make by using high-energy particles (few GeV/nucleon and higher) whose transportation from the Sun is characterized by a much bigger diffusion coefficient then for small and middle energy particles. Therefore, high energy particles come from the Sun much earlier (8-20 min after acceleration and escaping onto solar wind) than the main part of smaller energy particles (more than 30-60min later), causing radiation hazard for electronics and personal health, as well as spacecraft and aircrafts. We describe here principles of an automatic set of programs that begin with ''FEP-Search'', used to determine the beginning of a large FEP event. After a positive signal from ''FEP-Research/Spectrum'', and then ''FEP-Research/Time of Ejection'', ''FEP-Research /Source'' and ''FEP-Research/Diffusion'', which online determine properties of FEP generation and propagation. On the basis of the Obtained information, the next set of programs immediately start to work: ''FEP-Forecasting/Spacecrafts'', ''FEP-Forecasting/Aircrafts'', ''FEP-Forecasting/Aircrafts'', ''FEP-Forecasting/Ground'', which determine the expected differential and integral fluxes and total fluency for spacecraft on different orbits, aircrafts on different airline, and on the ground, depending on altitude and cutoff rigidity. If the level of radiation hazard is expected to be dangerous for high level technology or/and personal health, the following programs will be used ''FEP=Alert/Spacecrafts'', ''FEP-Alert/Aircrafts'', ''FEP-Alert/Ground''. (orig.)

  18. Adsorption of hexavalent chromium by crosslinked chitosan-iron(III) in an air-lift reactor.

    Science.gov (United States)

    Demarchi, Carla Albertina; Rodrigues, Clóvis Antonio

    2016-01-01

    Column experiments were conducted in an airlift reactor containing a certain amount of crosslinked chitosan-iron(III) (Ch-Fe), to examine the effects of adsorbent mass, flow rate, and influent concentrations on Cr(VI) removal. The breakthrough time increased with an increase in Ch-Fe mass, but decreased with an increase in initial Cr(VI) concentration. The exhaustion time decreased with an increase in initial Cr(VI) concentration. The capacity at the breakthrough point increased with an increase in Ch-Fe mass, flow rate, and initial Cr(VI) concentration. The capacity at the exhaustion point increased with an increase in flow rate, but showed no specific trend with an increase in initial Cr(VI) concentration. The bed volumes at breakthrough point increased with an increase in Ch-Fe, flow rate and Cr(VI) concentration. The adsorbent exhaustion decreased with an increase in flow rate and Ch-Fe, but increased with an increase in initial Cr(VI) concentration. Columns with large amounts of Ch-Fe are preferable for obtaining optimal results during the adsorption process. The higher the flow velocity, the better the column performance. The Thomas, Clark and Yoon-Nelson models were applied to the experimental results. Good agreement was observed between the predicted theoretical breakthrough curves and the experimental results. PMID:26901729

  19. Experimental and simulated control of lift using trailing edge devices

    International Nuclear Information System (INIS)

    Two active aerodynamic load control (AALC) devices coupled with a control algorithm are shown to decrease the change in lift force experienced by an airfoil during a change in freestream velocity. Microtabs are small (1% chord) surfaces deployed perpendicular to an airfoil, while microjets are pneumatic jets with flow perpendicular to the surface of the airfoil near the trailing edge. Both devices are capable of producing a rapid change in an airfoil's lift coefficient. A control algorithm for microtabs has been tested in a wind tunnel using a modified S819 airfoil, and a microjet control algorithm has been simulated for a NACA 0012 airfoil using OVERFLOW. In both cases, the AALC devices have shown the ability to mitigate the changes in lift during a gust

  20. Aerodynamics/ACEE: Aircraft energy efficiency

    Science.gov (United States)

    1981-01-01

    An overview is presented of a 10 year program managed by NASA which seeks to make possible the most efficient use of energy for aircraft propulsion and lift as well as provide a technology that can be used by U.S. manufacturers of air transports and engines. Supercritical wings, winglets, vortex drag reduction, high lift, active control, laminar flow control, and aerodynamics by computer are among the topics discussed. Wind tunnel models in flight verification of advanced technology, and the design, construction and testing of various aircraft structures are also described.

  1. The lifting scheme of 4-channel orthogonal wavelet transforms

    Institute of Scientific and Technical Information of China (English)

    PENG Lizhong; CHU Xiaoyong

    2006-01-01

    The 4-channel smooth wavelets with linear phase and orthogonality are designed from the 2-channel orthogonal wavelets with high transfer vanishing moments. Reversely, for simple lifting scheme of such 4-channel orthogonal wavelet transforms, a new 2-channel orthogonal wavelet associated with this 4-channel wavelet is constructed. The new 2-channel wavelet has at least the same number of vanishing moments as the associated 4-channel one. Finally, by combining the two such 2-channel wavelet systems, the lifting scheme of 4-channel orthogonal wavelet transform, which has simple structure and is easy to apply, is presented.

  2. Static mechanical properties of 30 x 11.5 - 14.5, type 8 aircraft tires of bias-ply and radial-belted design

    Science.gov (United States)

    Davis, Pamela A.; Lopez, Mercedes C.

    1988-01-01

    An investigation was conducted to determine the static mechanical properties of a 30 x 11.5 to 14.5, Type 8, bias-ply and radial-belted aircraft tire. The properties measured were the spring rate and damping characteristics of each tire from vertical- and lateral-loading hysteresis loops. Mass moment of inertia tests were also conducted. The results of the study are presented along with a discussion of the advantages and disadvantages of each type of tire.

  3. Considerations of Unmanned Aircraft Classification for Civil Airworthiness Standards

    Science.gov (United States)

    Maddalon, Jeffrey M.; Hayhurst, Kelly J.; Morris, A. Terry; Verstynen, Harry A.

    2013-01-01

    The use of unmanned aircraft in the National Airspace System (NAS) has been characterized as the next great step forward in the evolution of civil aviation. Although use of unmanned aircraft systems (UAS) in military and public service operations is proliferating, civil use of UAS remains limited in the United States today. This report focuses on one particular regulatory challenge: classifying UAS to assign airworthiness standards. Classification is useful for ensuring that meaningful differences in design are accommodated by certification to different standards, and that aircraft with similar risk profiles are held to similar standards. This paper provides observations related to how the current regulations for classifying manned aircraft, based on dimensions of aircraft class and operational aircraft categories, could apply to UAS. This report finds that existing aircraft classes are well aligned with the types of UAS that currently exist; however, the operational categories are more difficult to align to proposed UAS use in the NAS. Specifically, the factors used to group manned aircraft into similar risk profiles do not necessarily capture all relevant UAS risks. UAS classification is investigated through gathering approaches to classification from a broad spectrum of organizations, and then identifying and evaluating the classification factors from these approaches. This initial investigation concludes that factors in addition to those currently used today to group manned aircraft for the purpose of assigning airworthiness standards will be needed to adequately capture risks associated with UAS and their operations.

  4. Numerical modelling of the internal mixing by coagulation of black carbon particles in aircraft exhaust

    Energy Technology Data Exchange (ETDEWEB)

    Ohlsson, S.; Stroem, J. [Stockholm Univ. (Sweden). Dept. of Meteorology

    1997-12-31

    When exhaust gases from an aircraft engine mix with ambient air the humidity may reach water saturation and water droplets will form on the available cloud condensation nuclei (CCN). It is still not resolved if the CCN, on which the cloud droplets form, are mainly particles present in the ambient air or particles emitted by the aircraft. It the exhaust from a jet engine the particles are believed to consist mainly of black carbon (BC) and sulfate. The aim is to study, with the help of a numerical model, how a two-component aerosol (i.e. BC and sulfate) in an exhaust trail may be transformed in terms of hygroscopicity by coagulation mixing and how this may depend on the sulfur content in the fuel. (R.P.) 15 refs.

  5. Treatment of multiple fractures in a patient wounded by aircraft bombing

    Directory of Open Access Journals (Sweden)

    Golubović Zoran

    2010-01-01

    Full Text Available Introduction Aircraft cluster bombs can cause severe fractures characterized by extensive destruction of affected tissues and organs. Case Outline We present the methods and results of treatment of multiple fractures (left supracondilar humeral fracture, comminuted fracture of the distal right tibia, fracture of right trochanter major without dislocation and fracture of the right second metacarpal bone in a 24-year old soldier after multiple wounding by a cluster bomb. After short pre-operative preparation a surgical debridement of all wounds was done in general anesthesia and the fractures of the humerus and tibia were stabilized with the Mitkovic-type external fixator after adequate reposition. For the reconstruction of bone defect of the tibia we used the method of bone transport using the Ilizarov external fixator. Conclusion Radical wound debridement, abundant rinsing, leaving the wound open, administration of antibiotics and antitetanus immunization, external fixation and early reconstruction of soft tissue and bone defects are the basic elements of the treatment of serious fractures caused by war injuries and aimed at saving the extremities. .

  6. Estimation Methods for Determination of Drag Characteristics of Fly-by-Wire Aircraft

    Directory of Open Access Journals (Sweden)

    G. Girija

    2001-01-01

    Full Text Available "In this paper, several parameter/state estimation approaches for the determination of drag polars from flight data are described and evaluated for a fly-by-wire (FBW aircraft. Both model-based approaches (MBAs and non-model-based approaches (NMBAs are considered. Dynamic response data from roller coaster and wind- up-turn manoeuvres are generated in a FBW aircraft flight simulator at different flight conditions and the typical performance results are presented. A novel approach to estimate the drag polar has been evaluated. It has been found that the NMBAs perform better than the MBAs. Classically, the MBAs have been used for the determination of drag polars. The merits of an NMBA are that it does not require specification of the detailed model of the aerodynamic coefficients and it can be suitably used for online estimation of drag polars from the flight data of aerospace vehicles

  7. Treatment of multiple fractures in a patient wounded by aircraft bombing

    OpenAIRE

    Golubović Zoran; Stojiljković Predrag; Mitković Milorad; Trenkić Srbobran; Vukašinović Zoran; Lešić Aleksandar; Košutić Milomir; Milić Dragan; Najman Stevo; Golubović Ivan; Višnjić Aleksandar

    2010-01-01

    Introduction Aircraft cluster bombs can cause severe fractures characterized by extensive destruction of affected tissues and organs. Case Outline We present the methods and results of treatment of multiple fractures (left supracondilar humeral fracture, comminuted fracture of the distal right tibia, fracture of right trochanter major without dislocation and fracture of the right second metacarpal bone) in a 24-year old soldier after multiple wounding by a cluster bomb. After short pre-operat...

  8. MONITORING AND MODELLING OF AIR POLLUTION PRODUCED BY AIRCRAFT ENGINE EMISSION INSIDE THE ATHENS INTERNATIONAL AIRPORT

    Directory of Open Access Journals (Sweden)

    Oleksander I. Zaporozhets

    2009-04-01

    Full Text Available  Experimental measuring of air pollution inside the airport, produced by aircraft engine emission during accelaration and take-off on the runway. Measurement data were used for verification of modelling results according to complex model «PolEmiCa». It consists of the following basic components: engine emission inventory calculation; transport of the contaminants by engine jets, dispersion of the contaminants in atmosphere due to wind and atmospheric turbulence.

  9. Myoelectric activity and sequencing of selected trunk muscles during isokinetic lifting.

    Science.gov (United States)

    Noe, D A; Mostardi, R A; Jackson, M E; Porterfield, J A; Askew, M J

    1992-02-01

    Trained weight lifters lift heavy loads without a concomitant degree of acute low-back injuries. To study the process by which large loads are lifted with minimal injury, integrated electromyographic signals were recorded from four large muscle groups: gluteus maximus, quadriceps, latissimus dorsi, and erector spinae in 4 weight lifters and 11 asymptomatic control subjects. These signals were recorded during a floor-to-knuckle-height isokinetic lift (dead lift) at 30.5 and 45.7 cm/sec. The signals were normalized for the height of the lift and the maximal isokinetic integrated electromyographic activity. The weight lifters achieved maximal force at 50% of maximal lift height, whereas the control subjects achieved it at 67%. Although not statistically significant, the weight lifters used the gluteus maximus more during the early stages of the lift, perhaps contributing to earlier development of force. This process would stabilize the pelvis and permit the erector spinae to extend the trunk more efficiently. The weight lifter then completed the lift with prolonged and increasing activity in the quadriceps. This technique may minimize the required force in the erector spinae and the forces on the low-back structures. Clinical implications include more effective strength training of lifting muscle groups other than spinal extensors and the teaching of lifting strategies employed by weight lifters in low-back rehabilitation and work-hardening programs. PMID:1532462

  10. Maintenance program developmentandImport /Export of Aircraft in USA

    OpenAIRE

    Takele, Teklu

    2009-01-01

    AbstractThis thesis discuss how United Parcel Service (UPS) develop its aircraft maintenanceprogram after import of McDonnell Douglas MD-11aircraft and the process of exporting newMD-11 aircraft from manufacturer in USA to European operator as passenger aircraft. It alsodiscusses the process of importing the same types of aircraft as freight carrier. The aircraftundergo, through different modifications at Singapore Technologies Aerospace (STA)conversion from passenger to freight carrier, a pr...

  11. Airfoil Selection for a Lift Type Vertical Axis Wind Turbine%升力型垂直轴风力机翼型的选择

    Institute of Scientific and Technical Information of China (English)

    孙晓晶; 陆启迪; 黄典贵; 吴国庆

    2012-01-01

    At present,there are many different types of airfoils that have been used in lift-type vertical axis wind turbines.In order to study the influence of different airfoils on the lift-type vertical axis wind turbine performance,two-dimensional numerical simulation of flow around a Darrieus-type straight-bladed vertical axis wind turbine was conducted in this paper with the aid of computational fluid dynamics software and sliding mesh method.Numerical results suggest that NACA0018 airfoil is the most suitable airfoil section used by a lift-type vertical axis wind turbine rotors as it can allow the wind turbine to achieve the highest wind energy utilization efficiency.%目前升力型垂直轴风力机采用的翼型多种多样,为了研究不同翼型对升力型垂直轴风力机风能利用率的影响,本文采用计算流体力学软件和滑移网格技术对升力型直叶片垂直轴风力机进行二维流场的数值模拟。结果表明,对于升力型垂直轴风力机,当选择NACA0018翼型可以达到最高的风能利用率。

  12. A Grounded Theory Study of Aircraft Maintenance Technician Decision-Making

    Science.gov (United States)

    Norcross, Robert

    Aircraft maintenance technician decision-making and actions have resulted in aircraft system errors causing aircraft incidents and accidents. Aircraft accident investigators and researchers examined the factors that influence aircraft maintenance technician errors and categorized the types of errors in an attempt to prevent similar occurrences. New aircraft technology introduced to improve aviation safety and efficiency incur failures that have no information contained in the aircraft maintenance manuals. According to the Federal Aviation Administration, aircraft maintenance technicians must use only approved aircraft maintenance documents to repair, modify, and service aircraft. This qualitative research used a grounded theory approach to explore the decision-making processes and actions taken by aircraft maintenance technicians when confronted with an aircraft problem not contained in the aircraft maintenance manuals. The target population for the research was Federal Aviation Administration licensed aircraft and power plant mechanics from across the United States. Nonprobability purposeful sampling was used to obtain aircraft maintenance technicians with the experience sought in the study problem. The sample population recruitment yielded 19 participants for eight focus group sessions to obtain opinions, perceptions, and experiences related to the study problem. All data collected was entered into the Atlas ti qualitative analysis software. The emergence of Aircraft Maintenance Technician decision-making themes regarding Aircraft Maintenance Manual content, Aircraft Maintenance Technician experience, and legal implications of not following Aircraft Maintenance Manuals surfaced. Conclusions from this study suggest Aircraft Maintenance Technician decision-making were influenced by experience, gaps in the Aircraft Maintenance Manuals, reliance on others, realizing the impact of decisions concerning aircraft airworthiness, management pressures, and legal concerns

  13. Coriolis effects enhance lift on revolving wings.

    Science.gov (United States)

    Jardin, T; David, L

    2015-03-01

    At high angles of attack, an aircraft wing stalls. This dreaded event is characterized by the development of a leading edge vortex on the upper surface of the wing, followed by its shedding which causes a drastic drop in the aerodynamic lift. At similar angles of attack, the leading edge vortex on an insect wing or an autorotating seed membrane remains robustly attached, ensuring high sustained lift. What are the mechanisms responsible for both leading edge vortex attachment and high lift generation on revolving wings? We review the three main hypotheses that attempt to explain this specificity and, using direct numerical simulations of the Navier-Stokes equations, we show that the latter originates in Coriolis effects. PMID:25871040

  14. Vortex lift and insect flight

    Czech Academy of Sciences Publication Activity Database

    Dvořák, Rudolf

    Prague: Institute of Thermomechanics AS CR, v. v. i., 2011 - (Příhoda, J.; Kozel, K.), s. 25-28 ISBN 978-80-87012-32-1. [Topical Problems of Fluid Mechanics 2011. Praha (CZ), 16.02.2011-17.02.2011] R&D Projects: GA ČR(CZ) GAP101/10/1329 Institutional research plan: CEZ:AV0Z20760514 Keywords : vortex lift * insect flight * micro-air-vehiclesvortex lift Subject RIV: JU - Aeronautics, Aerodynamics, Aircrafts

  15. Lowering the Error Floor of LDPC Codes Using Cyclic Liftings

    CERN Document Server

    Asvadi, Reza; Ahmadian-Attari, Mahmoud

    2010-01-01

    Cyclic liftings are proposed to lower the error floor of low-density parity-check (LDPC) codes. The liftings are designed to eliminate dominant trapping sets of the base code by removing the short cycles which form the trapping sets. We derive a necessary and sufficient condition for the cyclic permutations assigned to the edges of a cycle $c$ of length $\\ell(c)$ in the base graph such that the inverse image of $c$ in the lifted graph consists of only cycles of length strictly larger than $\\ell(c)$. The proposed method is universal in the sense that it can be applied to any LDPC code over any channel and for any iterative decoding algorithm. It also preserves important properties of the base code such as degree distributions, encoder and decoder structure, and in some cases, the code rate. The proposed method is applied to both structured and random codes over the binary symmetric channel (BSC). The error floor improves consistently by increasing the lifting degree, and the results show significant improvemen...

  16. Scaling of Lift Degradation Due to Anti-Icing Fluids Based Upon the Aerodynamic Acceptance Test

    Science.gov (United States)

    Broeren, Andy P.; Riley, James T.

    2012-01-01

    In recent years, the FAA has worked with Transport Canada, National Research Council Canada (NRC) and APS Aviation, Inc. to develop allowance times for aircraft operations in ice-pellet precipitation. These allowance times are critical to ensure safety and efficient operation of commercial and cargo flights. Wind-tunnel testing with uncontaminated anti-icing fluids and fluids contaminated with simulated ice pellets had been carried out at the NRC Propulsion and Icing Wind Tunnel (PIWT) to better understand the flowoff characteristics and resulting aerodynamic effects. The percent lift loss on the thin, high-performance wing model tested in the PIWT was determined at 8 angle of attack and used as one of the evaluation criteria in determining the allowance times. Because it was unclear as to how performance degradations measured on this model were relevant to an actual airplane configuration, some means of interpreting the wing model lift loss was deemed necessary. This paper describes how the lift loss was related to the loss in maximum lift of a Boeing 737-200ADV airplane through the Aerodynamic Acceptance Test (AAT) performed for fluids qualification. A loss in maximum lift coefficient of 5.24 percent on the B737-200ADV airplane (which was adopted as the threshold in the AAT) corresponds to a lift loss of 7.3 percent on the PIWT model at 8 angle of attack. There is significant scatter in the data used to develop the correlation related to varying effects of the anti-icing fluids that were tested and other factors. A statistical analysis indicated the upper limit of lift loss on the PIWT model was 9.2 percent. Therefore, for cases resulting in PIWT model lift loss from 7.3 to 9.2 percent, extra scrutiny of the visual observations is required in evaluating fluid performance with contamination.

  17. Evidence for predictive control in lifting series of virtual objects.

    Science.gov (United States)

    Mawase, Firas; Karniel, Amir

    2010-06-01

    The human motor control system gracefully behaves in a dynamic and time varying environment. Here, we explored the predictive capabilities of the motor system in a simple motor task of lifting a series of virtual objects. When a subject lifts an object, she/he uses an expectation of the weight of the object to generate a motor command. All models of motor learning employ learning algorithms that essentially expect the future to be similar to the previously experienced environment. In this study, we asked subjects to lift a series of increasing weights and determined whether they extrapolated from past experience and predicted the next weight in the series even though that weight had never been experienced. The grip force at the beginning of the lifting task is a clean indication of the motor expectation. In contrast to the motor learning literature asserting adaptation by means of expecting a weighted average based on past experience, our results suggest that the motor system is able to predict the subsequent weight that follows a series of increasing weights. PMID:20428856

  18. Lift-off of large-scale ultrathin nanomembranes

    International Nuclear Information System (INIS)

    Ultrathin silicon-based nanomembranes hold significant promise for advancements in applications ranging from separations to tissue engineering. Widespread application of these membranes has been hindered by their small active area, which typically ranges from square micrometers to square millimeters. These membranes are typically supported on silicon chips as small windows as a result of a time-consuming through-wafer etch process. This approach results in a relatively low active area and can be challenging to integrate into devices because of the rigid silicon support. In this paper, a lift-off approach is demonstrated wherein the membrane is supported by a polymeric scaffold and separated from the wafer to enable fabrication of membrane sheets (>75 cm2) with >80% active area. The wafer-scale lift-off process is demonstrated with 50 nm thick microporous and nanoporous silicon nitride (SiN) membranes. Release of large-scale SiN membranes is accomplished with both wet and dry lift-off techniques. The dry approach uses XeF2 gas to etch a sacrificial silicon film, while the wet etch uses buffered oxide etchant to remove a silicon dioxide sacrificial layer. Finally, it is demonstrated that lift-off membranes have excellent optical properties and can be used to support cell culture on a conventional scale. (paper)

  19. Optimization Design of a 5kW Lift Type Vertical Axis Wind Turbine With Wind Shield-Growth Patterns%5kW遮蔽-增速升力型垂直轴风力机优化设计

    Institute of Scientific and Technical Information of China (English)

    姬俊峰; 邓召义; 蒋磊; 黄典贵

    2012-01-01

    本文详细介绍了5 kW遮蔽-增速垂直轴风力机的结构特点及主要参数。利用正交优化设计方法,采用计算流体力学软件,针对5 kW风力机,在叶片个数和遮蔽板安装位置半径一定的情况下,对翼型弦长、叶片转动扫掠面的半径、风轮旋转速度、遮蔽-增速板个数、遮蔽-增速板与叶片间的气动间隙以及遮蔽-增速板的安装角六个参数进行优化计算,找出一组最佳设计参数,进而设计出5 kW遮蔽-增速升力型垂直轴风力机,并对设计出的有遮蔽板与无遮蔽板两类型风力机的变工况特性进行比较分析。%This paper is devoted to a detailed study of the characteristics of the structure and most important aerodynamic design parameters of a 5 kW lift type vertical axis wind turbine with wind shield-growth patterns.As the number of turbine blades and the installation location of wind shield-growth patterns have been previously set,the computational fluid dynamics code was adopted in this study to obtain the numerical results and then six parameters,including blade airfoil chord length,radius of turbine rotor,rotational speed of the wind turbine,number of wind shield-growth patterns,clearance between the turbine blades and surrounding wind shield-growth patterns and installation angle of wind shield-growth patterns,were all optimized by using an orthogonal optimization algorithm.Based on the optimized parameters obtained,a 5 kW lift type vertical axis wind turbine can be designed.In addition,the performance characteristics of the designed wind turbine with and without wind shield-growth patterns were analyzed and compared under variable wind conditions.

  20. Penetrating injury of the lungs and multiple injuries of lower extremities caused by aircraft bombs splinters

    Directory of Open Access Journals (Sweden)

    Golubović Zoran

    2010-01-01

    Full Text Available Introduction. Injuries caused by aircraft bombs cause severe damages to the human body. They are characterized by massive destruction of injured tissues and organs, primary contamination by polymorph bacterial flora and modified reactivity of the body. Upon being wounded by aircraft bombs projectiles a victim simultaneously sustains severe damages of many organs and organ systems due to the fact that a large number of projectiles at the same time injure the chest, stomach, head and extremities. Case report. We presented a patient, 41 years of age, injured by aircraft bomb with hemo-pneumothorax and destruction of the bone and soft tissue structures of the foot, as well as the treatment result of such heavy injuries. After receiving thoracocentesis and short reanimation, the patient underwent surgical procedure. The team performed thoracotomy, primary treatment of the wound and atypical resection of the left lung. Thoracic drains were placed. The wounds on the lower leg and feet were treated primarily. Due to massive destruction of bone tissue of the right foot by cluster bomb splinters, and impossibility of reconstruction of the foot, guillotine amputation of the right lower leg was performed. Twelve days after the wounding caused by cluster bomb splinters, soft tissue of the left lower leg was covered by Tirsch free transplantant and the defect in the area of the left foot was covered by dorsalis pedis flap. The transplant and flap were accepted and the donor sites were epithelized. Twenty-six days following the wounding reamputation was performed and amputation stump of the right lower leg was closed. The patient was given a lower leg prosthesis with which he could move. Conclusion. Upon being wounded by aircraft bomb splinters, the injured person sustains severe wounds of multiple organs and organ systems due to simultaneous injuries caused by a large number of projectiles. It is necessary to take care of the vital organs first because they

  1. Monitoring and forecasting of great radiation hazards for spacecraft and aircrafts by online cosmic ray data

    Directory of Open Access Journals (Sweden)

    L. I. Dorman

    2005-11-01

    Full Text Available We show that an exact forecast of great radiation hazard in space, in the magnetosphere, in the atmosphere and on the ground can be made by using high-energy particles (few GeV/nucleon and higher whose transportation from the Sun is characterized by a much bigger diffusion coefficient than for small and middle energy particles. Therefore, high energy particles come from the Sun much earlier (8-20 min after acceleration and escaping into solar wind than the main part of smaller energy particles (more than 30-60 min later, causing radiation hazard for electronics and personal health, as well as spacecraft and aircrafts. We describe here principles of an automatic set of programs that begin with "FEP-Search", used to determine the beginning of a large FEP event. After a positive signal from "FEP-Search", the following programs start working: "FEP-Research/Spectrum", and then "FEP-Research/Time of Ejection", "FEP-Research /Source" and "FEP-Research/Diffusion", which online determine properties of FEP generation and propagation. On the basis of the obtained information, the next set of programs immediately start to work: "FEP-Forecasting/Spacecrafts", "FEP-Forecasting/Aircrafts", "FEP-Forecasting/Ground", which determine the expected differential and integral fluxes and total fluency for spacecraft on different orbits, aircrafts on different airlines, and on the ground, depending on altitude and cutoff rigidity. If the level of radiation hazard is expected to be dangerous for high level technology or/and personal health, the following programs will be used "FEP-Alert/Spacecrafts", "FEP-Alert/ Aircrafts", "FEP-Alert/Ground".

  2. 基于 PLC 的垂直升降式立体车库控制系统设计%Design of Control System for Vertical Garage of Lifting Type Based on PLC

    Institute of Scientific and Technical Information of China (English)

    王虎军; 马殷元

    2016-01-01

    The vertical garage of lifting type is effective programs to solve the problem of hard parking in the center of a city.This paper designed a control system of the vertical garage of lifting type and made the Siemens 300 series PLC as controller to describe the hardware components of the control system and the input and output port assign-ments, analyze how to program the main program and automatic control subroutine, and propose hardware and soft-ware methods to improve the safety and reliability of garage control system.The control system meets the functional requirements of the parking garage with high reliability.%垂直升降式立体车库是解决城市中心停车难的有效方案。设计了以西门子300系列PLC为主控制器的垂直升降式立体车库控制系统。阐述了该控制系统的硬件组成及输入输出口分配方案,编写了主程序和自动控制子程序,提出了提高车库控制系统安全与可靠性的相关设计。该控制系统能满足立体车库的功能需求并具有较高的可靠性。

  3. 49 CFR 178.811 - Bottom lift test.

    Science.gov (United States)

    2010-10-01

    ... qualification of all IBC design types designed to be lifted from the base. (b) Special preparation for the bottom lift test. The IBC must be loaded to 1.25 times its maximum permissible gross mass, the load being evenly distributed. (c) Test method. All IBC design types must be raised and lowered twice by a...

  4. A lifting surface approximation for roll stall of Micro Aerial Vehicles

    Science.gov (United States)

    Shields, Matt; Mohseni, Kamran

    2012-11-01

    The lateral stability of Micro Aerial Vehicles (MAVs) has been known to be adversely affected by the low aspect ratio (LAR) nature of these aircraft. While this has typically been attributed to the small moments of inertia about the plane of symmetry, recent experimental results display the development of a significant roll stability derivative (Cl , β) for flat plate (0% camber) wings. The roll moment can be attributed to the asymmetric development of the tip vortices of a yawed wing and the resulting deviation from the wing loading at zero sideslip. Furthermore, results indicate that a harmonic yaw oscillation at increasing angular velocities results in a delay effect as the formation of the tip vortex is affected by the rotation of the wing; that is, the roll moment does not reach its steady value at a given yaw angle until after the model yaws past the angle. A model based on modified lifting surface theory is developed to determine the influence of the induced velocities of the skewed tip vortices on the lateral loading of both the static and oscillating wing; experimentally determined parameters are used to compensate for the separated flow experienced by MAV wings and not considered in conventional lifting surface methods.

  5. Calculation of wing response to gusts and blast waves with vortex lift effect

    Science.gov (United States)

    Chao, D. C.; Lan, C. E.

    1983-01-01

    A numerical study of the response of aircraft wings to atmospheric gusts and to nuclear explosions when flying at subsonic speeds is presented. The method is based upon unsteady quasi-vortex lattice method, unsteady suction analogy and Pade approximant. The calculated results, showing vortex lag effect, yield reasonable agreement with experimental data for incremental lift on wings in gust penetration and due to nuclear blast waves.

  6. Preliminary Study on Effect of Aviation Fuel in the Safety Evaluation of Nuclear Power Plant Crashed by Aircraft

    Energy Technology Data Exchange (ETDEWEB)

    Jin, Byeong Moo; Jeon, Se Jin; Lee, Yun Seok; Kim, Young Jin [Daewoo E and C Co., Suwon (Korea, Republic of)

    2011-10-15

    As the safety assessments of nuclear power plants for the hypothetical large civil aircraft crash should be made mandatory, studies on large aircraft-nuclear power plant impact analyses and assessments are actively in progress. The large civil aircraft are being operated with a large amount of fuel and the fuel can be assumed to contribute to the impact loads at the impact. The fuel, i.e., the internal liquid can be considered as added masses classically in the evaluation of the impact load. According to the recent experimental research, it has been shown that the impact load of high speed impacting body with internal liquid is much higher than that of the mass-equivalent impacting body. In this study, the impact loads according to the existence of the internal liquid are computed by numerical methods and the safety assessment of nuclear power plant crashed by large civil aircraft are performed as an application

  7. Hierarchical Colored Timed Petri Nets for Maintenance Process Modeling of Civil Aircraft

    Institute of Scientific and Technical Information of China (English)

    FU Cheng-cheng; SUN You-chao; LU Zhong

    2008-01-01

    Civil aircraft maintenance process simulation model is an effective method for analyzing the maintainability of a civil aircraft. First, we present the Hierarchical Colored Timed Petri Nets for maintenance process modeling of civil aircraft. Then, we expound a general method of civil aircraft maintenance activities, determine the maintenance level for decomposition, and propose the methods of describing logic of relations between the maintenance activities based on Petri Net. Finally, a time Colored Petri multi-level network modeling and simulation procedures and steps are given with the maintenance example of the landing gear burst tire of a certain type of aircraft. The feasibility of the method is proved by the example.

  8. The integral lifting of sky-dome of 2RX security cover of nuclear power station

    International Nuclear Information System (INIS)

    The experiences of the integral lifting of sky-dome of 2RX security cover, weighted 170.5 tons, in the second period construction of Qinshan Nuclear Power Station is introduced, especially in four aspects of preparing jobs of lifting, simulating lifting, testing lifting, and formal lifting

  9. Experimental Study of Air-Lift Pumps Characteristics

    OpenAIRE

    Naji F. Al-Saqer; Mohammed E. Al-Shibani

    2014-01-01

    The mean aim of this work is to study the Air-lift pumps characteristics according to design parameters such as the percentage of the distance between throat section and nozzle and the driving air pressure, suction head and also study the effect of each parameter on the air lift pump characteristics in order to have a better performance of such pump under various conditions. A certain geometry for air-lift pump designed and manufactured. The experiments show that there must be ...

  10. Engine selection for transport and combat aircraft.

    Science.gov (United States)

    Dugan, J. F., Jr.

    1972-01-01

    Review of the procedures used to select engines for transport and combat aircraft by illustrating the procedures for a long haul CTOL transport, a short haul VTOL transport, a long range SST, and a fighter aircraft. For the CTOL transport, it is shown that advances in noise technology and advanced turbine cooling technology will greatly reduce the airplane performance penalties associated with achieving low noise goals. A remote lift fan powered by a turbofan air generator is considered for the VTOL aircraft. In this case, the lift fan pressure ratio which maximizes payload also comes closest to meeting the noise goal. High turbine temperature in three different engines is considered for the SST. Without noise constraints it leads to an appreciable drop in DOC, but with noise constraints the reduction in DOC is very modest. For the fighter aircraft it is shown how specific excess power requirements play the same role in engine selection as noise constraints for commercial airplanes.

  11. A wind tunnel investigation of the effects of micro-vortex generators and Gurney flaps on the high-lift characteristics of a business jet wing. M.S. Thesis

    Science.gov (United States)

    Martuccio, Michelle Therese

    1994-01-01

    A study of a full-scale, semi-span business jet wing has been conducted to investigate the potential of two types of high-lift devices for improving aircraft high-lift performance. The research effort involved low-speed wind-tunnel tests of micro-vortex generators and Gurney flaps applied to the flap system of the business jet wing and included force and moment measurements, surface pressure surveys and flow visualization on the wing and flap. Results showed that the micro-vortex generators tested had no beneficial effects on the longitudinal force characteristics in this particular application, while the Gurney flaps were an effective means of increasing lift. However, the Gurney flaps also caused an increase in drag in most circumstances.

  12. AEROSTATIC AND AERODYNAMIC MODULES OF A HYBRID BUOYANT AIRCRAFT: AN ANALYTICAL APPROACH

    Directory of Open Access Journals (Sweden)

    Anwar Ul Haque

    2015-05-01

    Full Text Available An analytical approach is essential for the estimation of the requirements of aerodynamic and aerostatic lift for a hybrid buoyant aircraft. Such aircrafts have two different modules to balance the weight of aircraft; aerostatic module and aerodynamic module. Both these modules are to be treated separately for estimation of the mass budget of propulsion systems and required power. In the present work, existing relationships of aircraft and airship are reviewed for its further application for these modules. Limitations of such relationships are also disussed and it is precieved that it will provide a strating point for better understanding of design anatomy of such aircraft.

  13. A lifting line model to investigate the influence of tip feathers on wing performance

    International Nuclear Information System (INIS)

    Bird wings have been studied as prototypes for wing design since the beginning of aviation. Although wing tip slots, i.e. wings with distinct gaps between the tip feathers (primaries), are very common in many birds, only a few studies have been conducted on the benefits of tip feathers on the wing's performance, and the aerodynamics behind tip feathers remains to be understood. Consequently most aircraft do not yet copy this feature. To close this knowledge gap an extended lifting line model was created to calculate the lift distribution and drag of wings with tip feathers. With this model, is was easily possible to combine several lifting surfaces into various different birdwing-like configurations. By including viscous drag effects, good agreement with an experimental tip slotted reference case was achieved. Implemented in C++ this model resulted in computation times of less than one minute per wing configuration on a standard notebook computer. Thus it was possible to analyse the performance of over 100 different wing configurations with and without tip feathers. While generally an increase in wing efficiency was obtained by splitting a wing tip into distinct, feather-like winglets, the best performance was generally found when spreading more feathers over a larger dihedral angle out of the wing plane. However, as the results were very sensitive to the precise geometry of the feather fan (especially feather twist) a careless set-up could just as easily degrade performance. Hence a detailed optimization is recommended to realize the full benefits by simultaneously optimizing feather sweep, twist and dihedral angles. (paper)

  14. Unsteady Lift and Drag Characteristics of Cavitating Clark Y-11.7% Hydrofoil

    International Nuclear Information System (INIS)

    Unsteady cavitating flow and lift/drag characteristics of a two-dimensional Clark Y- 11.7% hydrofoil are experimentally investigated in order to clarify the relation between the lift drop mechanism and the unsteady cavity behavior. Unsteady lift and drag forces are measured by strain gauges attached on the cantilever supporting the hydrofoil, assuming the negligible bending moment. In combination with the above force measurements, the cavitating flow is filmed from both top and side simultaneously using two high speed video cameras. It is clearly observed that, in larger attack angle conditions (4-10 degrees), the time-averaged lift coefficient slightly increases from that in the non-cavitating condition. After the slight increase, the lift gradually decreases then its steep decrease starts to occur. On the other hand, in a small attack angle case (2 degrees), little increase of the lift is observed, and just after that the sudden lift drop occurs. From the instantaneous frequency spectra of the lift, the followings are found; during the slight increase of the lift, the cavity is being a partial cavity in almost steady state, but during the subsequent gradual lift decrease, the partial cavity oscillates with cloud cavity shedding, in other word, the partial cavity oscillation occurs, whose frequency decreases with the growth of the cavity. During the sudden lift drop, the low frequency transitional cavity oscillation occurs, in which the cavity dramatically changes between partial and super cavities. The typical events of cavity behavior during the cavitation instabilities are found to be able to be related with the behavior of instantaneous lift force and pressure

  15. X-ray inspection of composite materials for aircraft structures using detectors of Medipix type

    Czech Academy of Sciences Publication Activity Database

    Jandejsek, Ivan; Jakůbek, J.; Jakůbek, M.; Průcha, P.; Krejčí, F.; Soukup, P.; Tureček, D.; Vavřík, Daniel; Žemlička, J.

    2014-01-01

    Roč. 9, May (2014), C05062. ISSN 1748-0221. [International workshop on radiation imaging detectors /15./. Paris, 23.06.2013-27.06.2013] Institutional support: RVO:68378297 Keywords : inspection with x-rays * detection of defects Subject RIV: JA - Electronics ; Optoelectronics, Electrical Engineering Impact factor: 1.399, year: 2014 http://iopscience.iop.org/1748-0221/9/05/C05062

  16. Assessment of aircraft noise sources variability using an acoustic camera

    OpenAIRE

    Snellen, M.; Merino Martinez, R.; Simons, D.G.

    2015-01-01

    Noise assessment around airports is hampered due to the observed large variability in noise levels for fly-overs of the same aircraft type, which is not considered by the current models. This paper assumes that the noise variability is due to variations in the aircraft emitted noise, neglecting the effect of the variable atmosphere, as previous work showed that its contribution is maximally 2 dB. In order to quantify and investigate the variability of noise levels during aircraft fly-overs, 1...

  17. 75 FR 51953 - Notification and Reporting of Aircraft Accidents or Incidents and Overdue Aircraft, and...

    Science.gov (United States)

    2010-08-24

    ... applicability of these regulations to unmanned aircraft systems (UAS). The proposed definition stated... unmanned aircraft system that takes place between the time that the system is activated with the purpose of... notification and reporting of aircraft accidents or incidents by adding a definition of ``unmanned......

  18. Simulation of Hydrodynamic RAM of Aircraft Fuel Tank by Ballistic Penetration and Detonation

    Science.gov (United States)

    Kim, Jong H.; Jun, Seung M.

    Airframe survivability and hydrodynamic ram effect of aircraft are investigated. Penetration and internal detonation of a simple tank and ICW(Intermediate Complexity Wing) are simulated by nonlinear explicit calculation. Structural rupture and fluid burst are analytically realized using general coupling of FSI(Fluid-Structure Interaction) and adaptive master-slave contact. Besides, multi-material Eulerian solver and porosity algorithm are employed to model explosive inside fuel and tank bays which are defined in multi-coupling surfaces. Structure and fluid results are animated on the same viewport for enhanced visualization.

  19. THEORETICAL AND EXPERIMENTAL ANALYSIS OF LOADING IMPACT FROM THE PROGRESSIVE GEAR ON THE LIFT BRAKING DISTANCE WITH THE USE OF THE FREE FALL METHOD

    OpenAIRE

    Paweł Lonkwic; Patryk Różyło

    2016-01-01

    The gear which is the central safety element of the friction drive lift during braking is exposed to overloading connected with changeable weight which loads the lift braking system. In the article the results of numerical analysis for braking process of CHP 2000 type progressive gear distinguished by an innovative design have been presented. The numerical analysis was conducted with the use of a simulation of the gear roller displacement depending on changeable loading with the support of Ab...

  20. Aging analyses of aircraft wire insulation

    Energy Technology Data Exchange (ETDEWEB)

    GILLEN,KENNETH T.; CLOUGH,ROGER LEE; CELINA,MATHIAS C.; AUBERT,JAMES H.; MALONE,G. MICHAEL

    2000-05-08

    Over the past two decades, Sandia has developed a variety of specialized analytical techniques for evaluating the long-term aging and stability of cable insulation and other related materials. These techniques have been applied to cable reliability studies involving numerous insulation types and environmental factors. This work has allowed the monitoring of the occurrence and progression of cable material deterioration in application environments, and has provided insights into material degradation mechanisms. It has also allowed development of more reliable lifetime prediction methodologies. As a part of the FAA program for intrusive inspection of aircraft wiring, they are beginning to apply a battery of techniques to assessing the condition of cable specimens removed from retired aircraft. It is anticipated that in a future part of this program, they may employ these techniques in conjunction with accelerated aging methodologies and models that the authros have developed and employed in the past to predict cable lifetimes. The types of materials to be assessed include 5 different wire types: polyimide, PVC/Glass/Nylon, extruded XL-polyalkene/PVDF, Poly-X, and XL-ETFE. This presentation provides a brief overview of the main techniques that will be employed in assessing the state of health of aircraft wire insulation. The discussion will be illustrated with data from their prior cable aging studies, highlighting the methods used and their important conclusions. A few of the techniques that they employ are widely used in aging studies on polymers, but others are unique to Sandia. All of their techniques are non-proprietary, and maybe of interest for use by others in terms of application to aircraft wiring analysis. At the end of this report is a list showing some leading references to papers that have been published in the open literature which provide more detailed information on the analytical techniques for elastomer aging studies. The first step in the

  1. Refined AFC-Enabled High-Lift System Integration Study

    Science.gov (United States)

    Hartwich, Peter M.; Shmilovich, Arvin; Lacy, Douglas S.; Dickey, Eric D.; Scalafani, Anthony J.; Sundaram, P.; Yadlin, Yoram

    2016-01-01

    A prior trade study established the effectiveness of using Active Flow Control (AFC) for reducing the mechanical complexities associated with a modern high-lift system without sacrificing aerodynamic performance at low-speed flight conditions representative of takeoff and landing. The current technical report expands on this prior work in two ways: (1) a refined conventional high-lift system based on the NASA Common Research Model (CRM) is presented that is more representative of modern commercial transport aircraft in terms of stall characteristics and maximum Lift/Drag (L/D) ratios at takeoff and landing-approach flight conditions; and (2) the design trade space for AFC-enabled high-lift systems is expanded to explore a wider range of options for improving their efficiency. The refined conventional high-lift CRM (HL-CRM) concept features leading edge slats and slotted trailing edge flaps with Fowler motion. For the current AFC-enhanced high lift system trade study, the refined conventional high-lift system is simplified by substituting simply-hinged trailing edge flaps for the slotted single-element flaps with Fowler motion. The high-lift performance of these two high-lift CRM variants is established using Computational Fluid Dynamics (CFD) solutions to the Reynolds-Averaged Navier-Stokes (RANS) equations. These CFD assessments identify the high-lift performance that needs to be recovered through AFC to have the CRM variant with the lighter and mechanically simpler high-lift system match the performance of the conventional high-lift system. In parallel to the conventional high-lift concept development, parametric studies using CFD guided the development of an effective and efficient AFC-enabled simplified high-lift system. This included parametric trailing edge flap geometry studies addressing the effects of flap chord length and flap deflection. As for the AFC implementation, scaling effects (i.e., wind-tunnel versus full-scale flight conditions) are addressed

  2. Current Status of NASA's Heavy Lift Plans

    Science.gov (United States)

    Creech, Steve

    2010-01-01

    Numerous studies since the Apollo Program of the 1960s have highlighted the benefits of - and the need for - a national heavy lift launch capability to support human exploration, science, national security, and commercial development of space. NASA's most recent and most refined effort to develop that heavy lift capability is the Ares V. Ares V is a key element of NASA's Constellation Program. It s overall goal s part of approved national space policy is to retire the Space Shuttle and develop its successor, complete the International Space Station, and resume human exploration beyond low Earth orbit (LEO), beginning with exploration of the Moon as a step to other destinations in the Solar System. Ares V s first role is that of cargo vehicle to carry a lunar lander into Earth orbit, rendezvous with astronauts launched on the smaller Ares I crew launch vehicle, and perform the trans lunar injection (TLI) mission to send the mated crew and lander vehicles to the Moon. The design reference missions (DRMs) envisioned for it also include direct lunar cargo flights and a human Mars mission. Although NASA's priority from the start of the Constellation Program to the present has been development of the Ares I and Orion crew vehicle to replace the retiring Shuttle fleet, the Ares team has made significant progress in understanding the performance, design trades, technology needs, mission scenarios, ground and flight operations, cost, and other factors associated with heavy lift development. The current reference configuration was selected during the Lunar Capabilities Concept Review (LCCR) in fall 2008. That design has served since then as a point of departure for further refinements and trades among five participating NASA field centers. Ares V development to date has benefited from progress on the Ares I due to commonality between the vehicles. The Ares I first stage completed a successful firing of a 5-segment solid rocket motor. The Ares I-X launch Numerous studies

  3. Model-Aided Design of Three-Phase Gas-Lift Reactor for Oxidation Accompanied by Catalyst Reversible Deactivation

    Czech Academy of Sciences Publication Activity Database

    Gogová, Zuzana; Hanika, Jiří

    2009-01-01

    Roč. 32, č. 12 (2009), s. 1929-1940. ISSN 0930-7516 R&D Projects: GA ČR(CZ) GD203/08/H032 Institutional research plan: CEZ:AV0Z40720504 Keywords : gas- lift reactor * multifunctional * design Subject RIV: CI - Industrial Chemistry, Chemical Engineering Impact factor: 1.266, year: 2009

  4. 'No clad lift-off' criterion and associated methodology developed by EDF and FRAMATOME-ANP on the basis of IFA-610 experiments

    International Nuclear Information System (INIS)

    At high burn-up, fuel rod internal pressure increase due to fission gas release along irradiation time can potentially bring fuel rod into 'cladding lift-off' situation, where pellet-clad gap is supposed to re-open and to increase leading to positive thermal feedback on fuel behaviour. In this situation, a rather quick degradation of the thermo-mechanical fuel rod behaviour is expected to occur and could cause the loss of rod integrity. IFA-610 test series was launched in 1997 by HRP in order to address clad 'lift-off' and thermal feedback phenomena in a high burn-up PWR fuel rod under overpressure conditions. Up to now seven different experiments have been performed in Halden using IFA-610 rig with UO2 and MOX fuel rods pre-irradiated in PWR up to high burn-ups. These experiments provided many relevant and consistent data showing that cladding lift-off is possible in a high burn-up fuel rod and that a high overpressure level, at least +130 bar, is required to induce any noticeable effect on fuel thermal behaviour. At high burn-up, fuel rod behaviour under overpressure conditions is similar for both UO2 and MOX fuels. Based on IFA-610 results, EDF, in cooperation with FRAMATOME-ANP, has developed an alternative rod pressure design methodology based on the 'no gap re-opening' criterion with its thermo-mechanical code CYRANO3 validated for IFA-610 simulation. This methodology has been licensed in 2001 by the French safety authorities and it allows EDF to benefit from additional margins for its current and future fuel managements. (Author)

  5. PERFORMANCE ANALYSIS OF IMAGE DENOISING IN LIFTING WAVELET TRANSFORM

    Directory of Open Access Journals (Sweden)

    G.M.Rajathi

    2012-11-01

    Full Text Available Images are contaminated by noise due to several unavoidable reasons, Poor image sensors, imperfect instruments, problems with data acquisition process, transmission errors and interfering natural phenomena are its main sources. Therefore, it is necessary to detect and remove noises present in the images. Reserving the details of an image and removing the random noise as far as possible is the goal of image denoising approaches . Lifting wavelet transform (LWTis based on the theory of lazy wavelet and completely recoverable filter banks,improving the wavelet and its performance through the lifting process under the condition of maintaining the feature of the wavelet compared with the classical constructions (DWT is rely on the Fourier transform. In this paper we compare the image denoising performance of LWT with DWT . We demonstrated through simulations with images contaminated by white Gaussian noise that exhibits performance in both PSNR (Peak Signal-to-Noise Ratio and visual effect.

  6. Assembly and lifting of Pearl-Chain arches

    DEFF Research Database (Denmark)

    Halding, Philip Skov; Hertz, Kristian Dahl; Viebæk, N.E.;

    2015-01-01

    buildings and bridges. The assembly and lifting of two Pearl-Chain arches, with a span of 13 m and rise of 1 m, is considered in this paper. Precast “Super-Light Deck” elements were used for the arches, which had a thickness of 22 cm. Both arches were successfully lifted, rotated in mid-air, and placed...

  7. On Liftings of Local Torus Actions to Fiber Bundles

    OpenAIRE

    Yoshida, Takahiko

    2007-01-01

    In this note we define a lifting of a local torus action modeled on the standard representation (we call it a local torus action for simplicity) to a principal torus bundle, and show that there is an obstruction class for the existence of liftings in the first cohomology of the fundamental group of the orbit space with coefficients in a certain module.

  8. On classical and quantum liftings

    OpenAIRE

    Accardi, L.; Chruściński, Dariusz; Kossakowski, Andrzej; Matsuoka, T.; Ohya, Masanori

    2011-01-01

    We analyze the procedure of lifting in classical stochastic and quantum systems. It enables one to `lift' a state of a system into a state of `system+reservoir'. This procedure is important both in quantum information theory and the theory of open systems. We illustrate the general theory of liftings by a particular class related to so called circulant states.

  9. Nuisance Caused by Aircraft Noise in the Vicinity of Tehran International Airport

    OpenAIRE

    Stan Frost; Khodabakhsh Karami

    1999-01-01

    Noise measurement and social questionnaire surveys in three residential areas around Mehrabad International Airport (Tehran, Iran) were based upon randomly selected dwellings in each area. A total of 193 individuals responded and many are annoyed and dissatisfied with aircraft noise and in consequence they would like to move. Aircraft noise is the strongest negative environmental factor affecting the residents in the vicinity of Mehrabad Airport and it could be a hazard for their health.

  10. Nuisance Caused by Aircraft Noise in the Vicinity of Tehran International Airport

    Directory of Open Access Journals (Sweden)

    Stan Frost

    1999-03-01

    Full Text Available Noise measurement and social questionnaire surveys in three residential areas around Mehrabad International Airport (Tehran, Iran were based upon randomly selected dwellings in each area. A total of 193 individuals responded and many are annoyed and dissatisfied with aircraft noise and in consequence they would like to move. Aircraft noise is the strongest negative environmental factor affecting the residents in the vicinity of Mehrabad Airport and it could be a hazard for their health.

  11. Mechanism isolates load weighing cell during lifting of load

    Science.gov (United States)

    Haigler, J. S.

    1966-01-01

    Load weighing cell used in conjuction with a hoist is isolated during lifting and manipulation of the load. A simple mechanism, attached to a crane hook, provides a screw adjustment for engaging the load cell during weighing of the load and isolating it from lift forces during hoisting of the load.

  12. Modeling and performance of intermittent gas-lift with plunger

    Energy Technology Data Exchange (ETDEWEB)

    Santos, Odair G. dos; Alhanati, Francisco J.S.; Bordalo, Sergio N. [Universidade Estadual de Campinas, SP (Brazil). Faculdade de Engenharia Mecanica. Dept. de Engenharia de Petroleo]. E-mail: bordalo@dep.fem.unicamp.br

    1997-07-01

    Artificial lift is used in petroleum production when the energy of the reservoir is not enough to sustain the flow of oil in the well up to the surface with satisfactory economic return. The gas-lift is a widely used method of artificial lift; in some cases, the continuous gas-lift (CGL) is not efficient, and one must implement the intermittent gas-lift; in some cases, the continuos gas-lift is not efficient, and one must implement the gas-lift (IGL), for which there are different design options. There are some empirical and questionable rules of thumb to choose between the CGL and IGL, but almost no material exists in the literature for the selection among the different intermittent gas-lift designs; furthermore, there are no published models or studies of their dynamics to help in the selection and design of IGL systems. This work presents a model to study the IGL WITH PLUNGER. In this system, a solid plunger separates the oil and gas flowing in the well, to prevent fall-back of oil. This paper presents sample results for some conditions of the petroleum reservoir, and for variations of the operational parameters. This work can aid the engineer in the determination of the optimum values of the operational parameters, and in the choice of the IGL design for particular field conditions. (author)

  13. Influence of Physical Therapists' Kinesiophobic Beliefs on Lifting Capacity in Healthy Adults

    NARCIS (Netherlands)

    Lakke, Sandra E.; Soer, Remko; Krijnen, Wim P.; van der Schans, Cees P.; Reneman, Michiel F.; Geertzen, Joannes

    2015-01-01

    Background. Physical therapists' recommendations to patients to avoid daily physical activity can be influenced by the therapists' kinesiophobic beliefs. Little is known about the amount of influence of a physical therapist's kinesiophobic beliefs on a patient's actual lifting capacity during a lift

  14. Research on the special lifting devices for steel box girders of Sutong Bridge

    Institute of Scientific and Technical Information of China (English)

    Chen Ming; Wu Qihe; Luo Chengbin; Zhou Hanfa

    2009-01-01

    Sutong Bridge is a cable-stayed bridge with a steel box girder and a main span of 1 088 m. The steel box girder of main span includes five portions: back span large unit, large block of pylon, standard girder, back span closure girder and middle span closure girder. Each back span large unit is fabricated by welding several deck segments together in factory, and is erected by floating crane. As navigational clearance of the main bridge is high, the traditional truss lifting device can' t satisfy the requirement of domestic lifting cranes for this kind of lifting height and weight. Hence, a kind of lighter lifting device for the erection of back span large units was accepted for this bridge. In this paper, the design and use of this lifting device is introduced.The upper structure used lifting gantry to install the standard girder segment by cantilever method. Because the bridge's navigation clearance is high, and the girder segment is wide and heavy, the meteorology and hydrology condition of the bridge district is abominable, and the requirements of long cable girder side pull-in, structure and performance propose high request to the lifting gantry. In this paper, the design and use key point of long cable pull-in angle adjustment device integrate into lifting gantry is introduced.

  15. Eisenhart lifts and symmetries of time-dependent systems

    CERN Document Server

    Cariglia, M; Gibbons, G W; Horvathy, P A

    2016-01-01

    Certain dissipative systems, such as Caldirola and Kannai's damped simple harmonic oscillator, may be modelled by time-dependent Lagrangian and hence time dependent Hamiltonian systems with $n$ degrees of freedom. In this paper we treat these systems, their projective and conformal symmetries as well as their quantisation from the point of view of the Eisenhart lift to a Bargmann spacetime in $n+2$ dimensions, equipped with its covariantly constant null Killing vector field. Reparametrization of the time variable corresponds to conformal rescalings of the Bargmann metric. We show how the Arnold map lifts to Bargmann spacetime. We contrast the greater generality of the Caldirola-Kannai approach with that of Arnold and Bateman. At the level of quantum mechanics, we are able to show how the relevant Schr\\"odinger equation emerges naturally using the techniques of quantum field theory in curved spacetimes, since a covariantly constant null Killing vector field gives rise to well defined one particle Hilbert space...

  16. Policy and the evaluation of aircraft noise

    OpenAIRE

    Kroesen, M.; Molin, E.J.E.; Van Wee, G.P.

    2010-01-01

    In this paper, we hypothesize and test the ideas that (1) people’s subjectivity in relation to aircraft noise is shaped by the policy discourse, (2) this results in a limited number of frames towards aircraft noise, (3) the frames inform people how to think and feel about aircraft noise and (4) the distribution of the frames in the population is dependent on structural variables related to the individual. To reveal subjects’ frames of aircraft noise a latent class model is estimated based on ...

  17. Grid connection of regenerating lift systems; Netzanbindung von rueckspeisenden Aufzugsanlagen

    Energy Technology Data Exchange (ETDEWEB)

    Skauradszun, Dominik [OPPENLAENDER Rechtsanwaelte, Stuttgart (Germany); Rohr, Stephan [ThyssenKrupp Aufzugswerke GmbH, Neuhausen auf den Fildern (Germany). Entwicklung Leistungselektronik

    2010-11-15

    With a glance at the energy efficiency, the authors of the contribution under consideration report on modern lifts and on accompanying questions of the energy right. The use of new technologies enables the installation of a cheaper energy recovery also in the case of lifts with low performance. Such lifts are not contained in the EEG (= Renewable Energy Law) and KWKG (= cogeneration protection act). The operator of a lift has to make a special contract with the provider of the power grid. In individual cases, a claim on acceptance and remuneration of the excess electricity can be subsumed, if connection, acceptance and remuneration are recompensed without reason. The VDI recommendation 4707 and the regulation EN ISO 25745 can be used for the interpretation of the normative factual characteristics in favour of the operators of lifts.

  18. Electro—magnetic control of shear flow over a cylinder for drag reduction and lift enhancement

    International Nuclear Information System (INIS)

    In this paper, the electro—magnetic control of a cylinder wake in shear flow is investigated numerically. The effects of the shear rate and Lorentz force on the cylinder wake, the distribution of hydrodynamic force, and the drag/lift phase diagram are discussed in detail. It is revealed that Lorentz force can be classified into the field Lorentz force and the wall Lorentz force and they affect the drag and lift forces independently. The drag/lift phase diagram with a shape of ''8'' consists of two closed curves, which correspond to the halves of the shedding cycle dominated by the upper and lower vortices respectively. The free stream shear (K > 0) induces the diagram to move downward and leftward, so that the average lift force directs toward the downside. With the upper Lorentz force, the diagram moves downwards and to the right by the field Lorentz force, thus resulting in the drag increase and the lift reduction, whereas it moves upward and to the left by the wall Lorentz force, leading to the drag reduction and the lift increase. Finally the diagram is dominated by the wall Lorentz force, thus moving upward and leftward. Therefore the upper Lorentz force, which enhances the lift force, can be used to overcome the lift loss due to the free stream shear, which is also obtained in the experiment. (electromagnetism, optics, acoustics, heat transfer, classical mechanics, and fluid dynamics)

  19. Modeling the Aerodynamic Lift Produced by Oscillating Airfoils at Low Reynolds Number

    CERN Document Server

    Khalid, Muhammad Saif Ullah

    2015-01-01

    For present study, setting Strouhal Number (St) as control parameter, numerical simulations for flow past oscillating NACA-0012 airfoil at 1,000 Reynolds Numbers (Re) are performed. Temporal profiles of unsteady forces; lift and thrust, and their spectral analysis clearly indicate the solution to be a period-1 attractor for low Strouhal numbers. This study reveals that aerodynamic forces produced by plunging airfoil are independent of initial kinematic conditions of airfoil that proves the existence of limit cycle. Frequencies present in the oscillating lift force are composed of fundamental (fs), even and odd harmonics (3fs) at higher Strouhal numbers. Using numerical simulations, shedding frequencies (f_s) were observed to be nearly equal to the excitation frequencies in all the cases. Unsteady lift force generated due to the plunging airfoil is modeled by modified van der Pol oscillator. Using method of multiple scales and spectral analysis of steady-state CFD solutions, frequencies and damping terms in th...

  20. Development of a hydrodynamic model for air-lift reactors

    Directory of Open Access Journals (Sweden)

    Carvalho E.

    2000-01-01

    Full Text Available In this paper, a 1D hydrodynamic model has been developed for gas hold-up and liquid circulation velocity prediction in air-lift reactors. The model is based on momentum balance equations and has been adjusted to experimental data collected on a pilot plant reactor equipped with two types of gas distributors and using water and water/butanol as the liquid phase. Different techniques of signal analysis have also been applied to pressure fluctuations in order to extract information about flow regimes and regime transitions. A good knowledge of the flow pattern is essential to establish adequate correlations for the hydrodynamic model.

  1. Local damage to Ultra High Performance Concrete structures caused by an impact of aircraft engine missiles

    Energy Technology Data Exchange (ETDEWEB)

    Riedel, Werner [Fraunhofer Institute for High-Speed Dynamics, Ernst-Mach-Institute, Eckerstrasse 4, D-79104 Freiburg (Germany); Noeldgen, Markus, E-mail: mnoeldgen@schuessler-plan.d [Fraunhofer Institute for High-Speed Dynamics, Ernst-Mach-Institute, Eckerstrasse 4, D-79104 Freiburg (Germany); Schuessler-Plan Engineering Ltd., St.-Franziskus-Str. 148, D-40470 Duesseldorf (Germany); Strassburger, Elmar; Thoma, Klaus [Fraunhofer Institute for High-Speed Dynamics, Ernst-Mach-Institute, Eckerstrasse 4, D-79104 Freiburg (Germany); Fehling, Ekkehard [University of Kassel, Chair of Structural Concrete, Kurt-Wolters Str. 3, D-34109 Kassel (Germany)

    2010-10-15

    Research highlights: {yields} Experimental series on UHPC panels subjected to aircraft engine impact. {yields} Improved ballistic limit of fiber reinforced UHPC in comparison to conventional R/C. {yields} Detailed investigation of failure mechanisms of fiber reinforced UHPC panel. - Abstract: The impact of an aircraft engine missile causes high stresses, deformations and a severe local damage to conventional reinforced concrete. As a consequence the design of R/C protective structural elements results in components with rather large dimensions. Fiber reinforced Ultra High Performance Concrete (UHPC) is a concrete based material which combines ultra high strength, high packing density and an improved ductility with a significantly increased energy dissipation capacity due to the addition of fiber reinforcement. With those attributes the material is potentially suitable for improved protective structural elements with a reduced need for material resources. The presented paper reports on an experimental series of scaled aircraft engine impact tests with reinforced UHPC panels. The investigations are focused on the material behavior and the damage intensity in comparison to conventional concrete. The fundamental work of is taken as reference for the evaluation of the results. The impactor model of a Phantom F4 GE-J79 engine developed and validated by Sugano et al. is used as defined in the original work. In order to achieve best comparability, the experimental configuration and method are adapted for the UHPC experiments. With 'penetration', 'scabbing' and 'perforation' all relevant damage modes defined in are investigated so that a full set of results are provided for a representative UHPC structural configuration.

  2. Local damage to Ultra High Performance Concrete structures caused by an impact of aircraft engine missiles

    International Nuclear Information System (INIS)

    Research highlights: → Experimental series on UHPC panels subjected to aircraft engine impact. → Improved ballistic limit of fiber reinforced UHPC in comparison to conventional R/C. → Detailed investigation of failure mechanisms of fiber reinforced UHPC panel. - Abstract: The impact of an aircraft engine missile causes high stresses, deformations and a severe local damage to conventional reinforced concrete. As a consequence the design of R/C protective structural elements results in components with rather large dimensions. Fiber reinforced Ultra High Performance Concrete (UHPC) is a concrete based material which combines ultra high strength, high packing density and an improved ductility with a significantly increased energy dissipation capacity due to the addition of fiber reinforcement. With those attributes the material is potentially suitable for improved protective structural elements with a reduced need for material resources. The presented paper reports on an experimental series of scaled aircraft engine impact tests with reinforced UHPC panels. The investigations are focused on the material behavior and the damage intensity in comparison to conventional concrete. The fundamental work of is taken as reference for the evaluation of the results. The impactor model of a Phantom F4 GE-J79 engine developed and validated by Sugano et al. is used as defined in the original work. In order to achieve best comparability, the experimental configuration and method are adapted for the UHPC experiments. With 'penetration', 'scabbing' and 'perforation' all relevant damage modes defined in are investigated so that a full set of results are provided for a representative UHPC structural configuration.

  3. Mechanical discrete simulator of the electro-mechanical lift with n:1 roping

    Science.gov (United States)

    Alonso, F. J.; Herrera, I.

    2016-05-01

    The design process of new products in lift engineering is a difficult task due to, mainly, the complexity and slenderness of the lift system, demanding a predictive tool for the lift mechanics. A mechanical ad-hoc discrete simulator, as an alternative to ‘general purpose’ mechanical simulators is proposed. Firstly, the synthesis and experimentation process that has led to establish a suitable model capable of simulating accurately the response of the electromechanical lift is discussed. Then, the equations of motion are derived. The model comprises a discrete system of 5 vertically displaceable masses (car, counterweight, car frame, passengers/loads and lift drive), an inertial mass of the assembly tension pulley-rotor shaft which can rotate about the machine axis and 6 mechanical connectors with 1:1 suspension layout. The model is extended to any n:1 roping lift by setting 6 equivalent mechanical components (suspension systems for car and counterweight, lift drive silent blocks, tension pulley-lift drive stator and passengers/load equivalent spring-damper) by inductive inference from 1:1 and generalized 2:1 roping system. The application to simulate real elevator systems is proposed by numeric time integration of the governing equations using the Kutta-Meden algorithm and implemented in a computer program for ad-hoc elevator simulation called ElevaCAD.

  4. Shape Design of Lifting body Based on Genetic Algorithm

    Directory of Open Access Journals (Sweden)

    Yongyuan Li

    2010-11-01

    Full Text Available This paper briefly introduces the concept and history of lifting body, and puts forward a new method for the optimization of lifting body. This method has drawn lessons from the die line design of airplane is used to parametric numerical modeling for the lifting body, and extract the characterization of shape parameters as design variables, a combination of lifting body reentry vehicle aerodynamic conditions, aerodynamic heating, volumetric Rate and the stability of performance. Multi-objective hybrid genetic algorithm is adopted to complete the aerodynamic shape optimization and design of hypersonic lifting body vehicle when under more variable and constrained condition in order to obtain the Pareto optimal solution of Common Aero Vehicle shape.

  5. Survival analysis of aging aircraft

    Science.gov (United States)

    Benavides, Samuel

    This study pushes systems engineering of aging aircraft beyond the boundaries of empirical and deterministic modeling by making a sharp break with the traditional laboratory-derived corrosion prediction algorithms that have shrouded real-world failures of aircraft structure. At the heart of this problem is the aeronautical industry's inability to be forthcoming in an accurate model that predicts corrosion failures in aircraft in spite of advances in corrosion algorithms or improvements in simulation and modeling. The struggle to develop accurate corrosion probabilistic models stems from a multitude of real-world interacting variables that synergistically influence corrosion in convoluted and complex ways. This dissertation, in essence, offers a statistical framework for the analysis of structural airframe corrosion failure by utilizing real-world data while considering the effects of interacting corrosion variables. This study injects realism into corrosion failures of aging aircraft systems by accomplishing four major goals related to the conceptual and methodological framework of corrosion modeling. First, this work connects corrosion modeling from the traditional, laboratory derived algorithms to corrosion failures in actual operating aircraft. This work augments physics-based modeling by examining the many confounding and interacting variables, such as environmental, geographical and operational, that impact failure of airframe structure. Examined through the lens of censored failure data from aircraft flying in a maritime environment, this study enhances the understanding between the triad of the theoretical, laboratory and real-world corrosion. Secondly, this study explores the importation and successful application of an advanced biomedical statistical tool---survival analysis---to model censored corrosion failure data. This well-grounded statistical methodology is inverted from a methodology that analyzes survival to one that examines failures. Third, this

  6. Development of a hydrodynamic model for air-lift reactors

    OpenAIRE

    Carvalho E.; Camarasa E.; Meleiro L.A.C.; Maciel Filho R.; Domingues A.; Vial Ch.; Wild G.; Poncin S.; Midoux N.; Bouillard J.

    2000-01-01

    In this paper, a 1D hydrodynamic model has been developed for gas hold-up and liquid circulation velocity prediction in air-lift reactors. The model is based on momentum balance equations and has been adjusted to experimental data collected on a pilot plant reactor equipped with two types of gas distributors and using water and water/butanol as the liquid phase. Different techniques of signal analysis have also been applied to pressure fluctuations in order to extract information about flow r...

  7. The development of a personal dosemeter for use by aircraft crew

    International Nuclear Information System (INIS)

    This paper describes preliminary work to develop a cosmic-radiation dosemeter for use by military aircraft crew. The dosemeter is based on a combination of CR-39 etched-track detectors and TLD-700 thermoluminescent detectors. It is intended that the CR-39 be used to assess the neutron dose, while the TLD-700 is used to assess the photon and charged particle dose. The sensitivity of CR-39 to the neutron component of cosmic radiation was estimated by irradiating samples of the plastic at the CERN-CEC High Energy Reference Field Facility. This facility produced a radiation field with a neutron spectrum resembling that of the neutron component of cosmic radiation a typical airflight altitudes. The response of the CR-39 was linear over the range of doses studied (0.2-6.0 mSv) and there was no significant fading in the six-month period after irradiation. The TLD-700 component of the dosemeter was calibrated using 137Cs gamma rays. The response of the TLD-700 was linear over the range of doses studied (0-1.1 mSv) with no significant fade in the six-month period after irradiation. It was concluded that a combination of CR-39 and TLD-700 detectors would provide an effective cosmic-radiation dosemeter for use by military aircraft crew. (author)

  8. Turbulent flow and heat transfer in vertical tubes under strong effects of lifting forces

    International Nuclear Information System (INIS)

    The problem is studied of the turbulent flow and heat transfer in vertical tubes, considering the lifting forces effect on the averaged flow as well on the turbulent transfer. Expressions for the pulse turbulent transfer coefficient and for the Prandtl turbulent number have been obtained by approximate solution of the turbulence energy balance equations and of the enthalpy pulsation intensity equations. The averaged motion and energy equation system of the boundary layers type is solved numerically. The calculated and experimentally measured profiles of the velocity, of the pulse turbulent transfer coefficient distribution, of the heat emission and resistance coefficients are given. The results of calculations performed for water and air at the lifting and dipping flow in the heated vertical tubes, are in a good agreement with the experimental data

  9. Recovery of DNA from latent fingerprint tape lifts archived against matte acetate.

    Science.gov (United States)

    Steadman, Shelly A; Hoofer, Steven R; Geering, Sarah C; King, Stephanie; Bennett, Marc A

    2015-05-01

    This study was driven by court order to examine methods to remove, extract, and STR-type potential DNA entrapped between latent fingerprint lifting tape and matte acetate that was collected from a 1977 crime scene. Results indicate that recovery of appreciable quantities of DNA is more challenging once adhesive is attached to matte acetate cards and even more difficult when fixed following black powder enhancement. STR amplification of extracts from entrapped fingermarks collected following the dusting/lifting procedure did not produce robust profiles, and extraneous peaks not expressed by print donors were detected for some samples. A hearing was set to argue whether there was DNA remaining to be tested, and if so, whether that DNA could be exculpatory in this postconviction matter. The studies herein provided the basis for the court's decision to not require the testing. PMID:25702951

  10. Fabricating Nanodots using Lift-Off of a Nanopore Template

    Science.gov (United States)

    Yang, Eui-Hyeok; Ramsey, Christopher R.; Bae, Youngsam; Choi, Daniel S.

    2008-01-01

    A process for fabricating a planar array of dots having characteristic dimensions of the order of several nanometers to several hundred nanometers involves the formation and use of a thin alumina nanopore template on a semiconductor substrate. The dot material is deposited in the nanopores, then the template is lifted off the substrate after the dots have been formed. This process is expected to be a basis for development of other, similar nanofabrication processes for relatively inexpensive mass production of nanometerscale optical, optoelectronic, electronic, and magnetic devices. Alumina nanopore templates are self-organized structures that result from anodization of aluminum under appropriate conditions. Alumina nanopore templates have been regarded as attractive for use in fabricating the devices mentioned above, but prior efforts to use alumina nanopore templates for this purpose have not been successful. One reason for the lack of success is that the aspect ratios (ratios between depth and diameter) of the pores have been too large: large aspect ratios can result in blockage of deposition and/or can prevent successful lift-off. The development of the present process was motivated partly by a requirement to reduce aspect ratios to values (of the order of 10) for which there is little or no blockage of deposition and attempts at lift-off are more likely to be successful. The fabrication process is outlined.

  11. CAD SIMULATION & FEM ANALYSIS OF AIRCRAFT LANDING GEAR MECHANISM

    OpenAIRE

    Nilesh W. Nirwan; Dilip G. Gangwani,

    2015-01-01

    Aircraft landing gear supports the entire weight of an aircraft during landing and ground operations. They are attached to primary structural members of the aircraft. The type of gear depends on the aircraft design and its intended use. Most landing gear has wheels to facilitate operation to and from hard surfaces, such as airport runways. Other gear feature skids for this purpose, such as those found on helicopters, balloon gondolas, and in the tail area of some tail dragger airc...

  12. Chemistry characterization of jet aircraft engine particulate matter by XPS: Results from APEX III

    Science.gov (United States)

    Vander Wal, Randy L.; Bryg, Victoria M.; Huang, Chung-Hsuan

    2016-09-01

    This paper reports X-ray photoelectron spectroscopy (XPS) analysis of jet exhaust particulate matter (PM) from a B737, Lear, ERJ and A300 aircraft during the APEX III NASA led field campaign. Carbon hybridization and bonding chemistry are identified by high-resolution scans about the C1s core-shell region. Significant organic content as gauged by the sp3/sp2 ratio is found across engines and powers. Polar oxygen functional groups include carboxylic, carbonyl and phenol with combined content of 20% or more. By survey scans various elements including transition metals are identified along with lighter elements such as S, N and O in the form of oxides. Additives within lubricants are probable sources of Na, Ba, Ca, Zn, P and possibly Sn. Elements present and their percentages varied significantly across all engines, not revealing any trend or identifiable cause for the differences, though the origin is likely the same for the same element when observed. This finding suggests that their collective presence could serve as an environmental tracer for identifying PM originating from aircraft engines and serving as a diagnostic for engine performance and wear.

  13. Chemistry Characterization of Jet Aircraft Engine Particulate by XPS: Results from APEX III

    Science.gov (United States)

    Vander Wal, Randy L.; Bryg, Victoria M.

    2014-01-01

    This paper reports XPS analysis of jet exhaust particulate from a B737, Lear, ERJ, and A300 aircraft during the APEX III NASA led field campaign. Carbon hybridization and bonding chemistry are identified by high-resolution scans about the C1s core-shell region. Significant organic content as gauged by the sp3/sp2 ratio is found across engines and platforms. Polar oxygen functional groups include carboxylic, carbonyl and phenol with combined content of 20 percent or more. By lower resolution survey scans various elements including transition metals are identified along with lighter elements such as S, N, and O in the form of oxides. Burning additives within lubricants are probable sources of Na, Ba, Ca, Zn, P and possibly Sn. Elements present and their percentages varied significantly across all engines, not revealing any trend or identifiable cause for the differences, though the origin is likely the same for the same element when observed. This finding suggests that their presence can be used as a tracer for identifying soots from aircraft engines as well as diagnostic for monitoring engine performance and wear.

  14. Development of Advanced High Lift Leading Edge Technology for Laminar Flow Wings

    Science.gov (United States)

    Bright, Michelle M.; Korntheuer, Andrea; Komadina, Steve; Lin, John C.

    2013-01-01

    This paper describes the Advanced High Lift Leading Edge (AHLLE) task performed by Northrop Grumman Systems Corporation, Aerospace Systems (NGAS) for the NASA Subsonic Fixed Wing project in an effort to develop enabling high-lift technology for laminar flow wings. Based on a known laminar cruise airfoil that incorporated an NGAS-developed integrated slot design, this effort involved using Computational Fluid Dynamics (CFD) analysis and quality function deployment (QFD) analysis on several leading edge concepts, and subsequently down-selected to two blown leading-edge concepts for testing. A 7-foot-span AHLLE airfoil model was designed and fabricated at NGAS and then tested at the NGAS 7 x 10 Low Speed Wind Tunnel in Hawthorne, CA. The model configurations tested included: baseline, deflected trailing edge, blown deflected trailing edge, blown leading edge, morphed leading edge, and blown/morphed leading edge. A successful demonstration of high lift leading edge technology was achieved, and the target goals for improved lift were exceeded by 30% with a maximum section lift coefficient (Cl) of 5.2. Maximum incremental section lift coefficients ( Cl) of 3.5 and 3.1 were achieved for a blown drooped (morphed) leading edge concept and a non-drooped leading edge blowing concept, respectively. The most effective AHLLE design yielded an estimated 94% lift improvement over the conventional high lift Krueger flap configurations while providing laminar flow capability on the cruise configuration.

  15. Numerical simulation of the flow field around a complete aircraft

    Science.gov (United States)

    Shang, J. S.; Scherr, S. J.

    1986-01-01

    The present effort represents a first attempt of numerical simulation of the flow field around a complete aircraft-like, lifting configuration utilizing the Reynolds averaged Navier-Stokes equations. The numerical solution generated for the experimental aircraft concept X24C-10D at a Mach number of 5.95 not only exhibited accurate prediction of detailed flow properties but also of the integrated aerodynamic coefficients. In addition, the present analysis demonstrated that a page structure of data collected into cyclic blocks is an efficient and viable means for processing the Navier-Stokes equations on the CRAY XMP-22 computer with external memory device.

  16. Guidance Systems of Fighter Aircraft

    Directory of Open Access Journals (Sweden)

    K.N. Rajanikanth

    2005-07-01

    Full Text Available Mission performance of a fighter aircraft is crucial for survival and strike capabilities in todays' aerial warfare scenario. The guidance functions of such an aircraft play a vital role inmeeting the requirements and accomplishing the mission success. This paper presents the requirements of precision guidance for various missions of a fighter aircraft. The concept ofguidance system as a pilot-in-loop system is pivotal in understanding and designing such a system. Methodologies of designing such a system are described.

  17. 牵引车吊具的设计与有限元分析%The Desi gn and Finite-element Analysis of Lifting Tool of Tractor

    Institute of Scientific and Technical Information of China (English)

    常喜庆

    2015-01-01

    In this paper , a lifting tool for a certain type of tractor was designed . The strength and stiffness of the lifting tool were analysed by using ANSYSWorkbench software . The lifting tool was optimized by using the analysis results . The design of lifting tool was effective and feasible by practical examination and application .%文章以某型号牵引车为例,进行整车吊具的设计,利用 ANSYSWorkbench 软件进行吊具的强刚度特性分析,并基于分析结果对吊具进行优化.通过实际的吊装试验及应用,结果表明该吊具的设计有效可行.

  18. Development of Bubble Lift-off Diameter Model for Subcooled Boiling Flows

    International Nuclear Information System (INIS)

    A lot of models and correlations for predicting the bubble departure/lift-off diameter are available in the literature. Most of them were developed based on a hydrodynamic principle, which balances forces acting on a bubble at the departure/lift-off point. One difficulty of these models is lack of essential information, such as bubble front velocity, liquid velocity, or relative velocity, to estimate the active force elements. Hence, the lift-off bubble diameter predicted by these hydrodynamic-controlled models may be suffered a large uncertainty. In contract to the hydrodynamic approach, there are few models developed based on the heat transfer aspect. By balancing the heat conducted through a microlayer underneath a bubble with the heat taken away by condensation at the upper part of the bubble, Unal derived a heat-controlled model of the bubble lift-off diameter. This model did not consider the role of superheat liquid layer surrounding the bubble as well as the effect of liquid properties on the heat transfer process. Beside these two approaches, several empirical correlations have been proposed based on dimensionless analyses for measured experimental databases. The application of these correlations to different experiments conditions is, of course, questionable because of the lack of physical bases. Regarding the heat transfer accompanied by a vapor bubble, four involved heat transfer regions surrounding this bubble can be defined as in Fig. 1. These are dry region, microlayer, superheated liquid layer (SpLL) and subcooled liquid layer (SbLL). The existing of the microlayer is confirmed by experiments, and it is considered to be very effective in the heat transfer. Sernas and Hoper defined five types of the microlayer and indicated that the microlayer acting as a very thick liquid layer gives a best prediction for the bubble growth. However, beside the microlayer, the SpLL might play an important role in the heat transfer if its effective heat transfer area

  19. Autoignited laminar lifted flames of methane, ethylene, ethane, and n-butane jets in coflow air with elevated temperature

    KAUST Repository

    Choi, Byungchul

    2010-12-01

    The autoignition characteristics of laminar lifted flames of methane, ethylene, ethane, and n-butane fuels have been investigated experimentally in coflow air with elevated temperature over 800. K. The lifted flames were categorized into three regimes depending on the initial temperature and fuel mole fraction: (1) non-autoignited lifted flame, (2) autoignited lifted flame with tribrachial (or triple) edge, and (3) autoignited lifted flame with mild combustion. For the non-autoignited lifted flames at relatively low temperature, the existence of lifted flame depended on the Schmidt number of fuel, such that only the fuels with Sc > 1 exhibited stationary lifted flames. The balance mechanism between the propagation speed of tribrachial flame and local flow velocity stabilized the lifted flames. At relatively high initial temperatures, either autoignited lifted flames having tribrachial edge or autoignited lifted flames with mild combustion existed regardless of the Schmidt number of fuel. The adiabatic ignition delay time played a crucial role for the stabilization of autoignited flames. Especially, heat loss during the ignition process should be accounted for, such that the characteristic convection time, defined by the autoignition height divided by jet velocity was correlated well with the square of the adiabatic ignition delay time for the critical autoignition conditions. The liftoff height was also correlated well with the square of the adiabatic ignition delay time. © 2010 The Combustion Institute.

  20. Reduction of aircraft noise in civil air transport by optimization of flight tracks and takeoff and approach procedures

    Science.gov (United States)

    Rottmann, Uwe

    1988-08-01

    Noise optimized design of operational flight procedures for effective noise pollution reduction is analyzed. Power cutback during certain stages of approach and takeoff, extension of distance between sound source and sound receiver, as well as diminution of sound impact time are optimized for specific flight procedures and routings. Five takeoff and three landing procedures are analyzed in acoustic effects. Sound immission is computed by NOISIMSIS (NOISe IMpact SImulation System), a simulation system especially created for this task, under consideration of aircraft type specified sound emission characteristics and performance data as well as different meteorological conditions. The investigations for the example of Frankfurt airport result in formulating a planning guideline with notes and impulses for activities in operational noise abatement.

  1. Study on Size Distributions of Airborne Particles by Aircraft Observation in Spring over Eastern Coastal Areas of China

    Institute of Scientific and Technical Information of China (English)

    WANG Wei; LIU Hongjie; YUE Xin; LI Hong; CHEN Jianhua; TANG Dagang

    2005-01-01

    The authors studied the size distributions of particles at an altitude of 2000 m by aircraft observation over eastern costal areas of China from Zhuhai, Guangdong to Dalian, Liaoning (0.47-30 μm, 57 channels,including number concentration distribution, surface area concentration distribution and mass concentration distribution). In these cities, the average daily concentrations of PM10 are very high. They are among the most heavily polluted cities in China. The main pollution sources are anthropogenic activities such as wood, coal and oil burning. The observed size distributions show a broad spectrum and unique multi-peak characteristics, indicating no significant impacts of individual sources from urban areas. These results are far different from the distribution type at ground level. It may reflect the comprehensive effect of the regional pollution characteristics. Monitoring results over big cities could to some extent reflect their pollution characteristics.

  2. LIFT AND POWER REQUIREMENTS OF HOVERING INSECT FLIGHT

    Institute of Scientific and Technical Information of China (English)

    孙茂; 杜刚

    2003-01-01

    Lift and power requirements for hovering flight of eight species of insects are studied by solving the Navier-Stokes equation numerically. The solution provides velocity and pressure fields,from which unsteady aerodynamic forces and moments are obtained. The inertial torque of wing mass are computed analytically. The wing length of the insects ranges from 2 mm (fruit fly) to 52 mm (hawkmoth); Reynolds numbers Re (based on mean flapping speed and mean chord length) ranges from 75 to 3 850. The primary findings are shown in the following: (1) Either small (R = 2 mm, Re = 75),medium (R ≈ 10 mm, Re ≈ 500) or large (R ≈ 50 mm, Re ≈ 4 000) insects mainly employ the same high-lift mechanism, delayed stall, to produce lift in hovering flight. The midstroke angle of attack needed to produce a mean lift equal to the insect weight is approximately in the range of 25° to 45°,which is approximately in agreement with observation. (2) For the small insect (fruit fly) and for the medium and large insects with relatively small wingbeat frequency (cranefly, ladybird and hawkmoth),the specific power ranges from 18 to 39W.kg-1 , the major part of the power is due to aerodynamic force, and the elastic storage of negative work does not change the specific power greatly. However for medium and large insects with relatively large wingbeat frequency (hoverfly, dronefly, honey bee and bumble bee), the specific power ranges from 39 to 61W.kg-1 , the major part of the power is due to wing inertia, and the elastic storage of negative work can decrease the specific power by approximately 33%. (3) For the case of power being mainly contributed by aerodynamic force (fruit fly, cranefly,ladybird and hawkmoth), the specific power is proportional to the product of the wingbeat frequency,the stroke amplitude, the wing length and the drag-to-lift ratio. For the case of power being mainly contributed by wing inertia (hoverfly, dronefly, honey bee and bumble bee), the specific power (without

  3. Aerodynamic Interference between Oscillating Lifting Surfaces and Fuselage Part 2: Some Applications of Oscillating Lifting Surface Theory

    Directory of Open Access Journals (Sweden)

    Valentin Adrian Jean BUTOESCU

    2014-03-01

    Full Text Available This is the second article of a series that deals with the calculation of the aerodynamic unsteady forces on lifting surfaces. It presents some new important details on the lifting surface theory that performs oscillations in subsonic flow. These features will be applied to the aerodynamic response to certain kind of gusts and to the flapping wing calculations.

  4. 喷射气举提升性能实验分析%Experimental research on lifting capability of jet air-lift

    Institute of Scientific and Technical Information of China (English)

    杜鹏; 卢义玉; 张磊; 周哲; 林晓东; 侯吉峰

    2015-01-01

    The lifting efficiency of traditional air-lift system is low,therefore a jet air-lift of annular jet pump structure is designed in this article,and an experimental device of air-lift system is established.In the experiment,riversand is chosen as the lifting object,and the influence laws of jet air-lift lifting water and solid capacity by air flow rate on submergence ration are researched.The flow pattern inside the riser is analyzed,and the lifting solid capacity of traditional air-lift and jet air-lift is compared.The efficiency model of air-lift is established by energy conservation law,and the lifting solid efficiency of traditional air-lift and jet air-lift is compared.The result show that there is a best air flow rate making the highest of water and solid flow rate.The water and solid flow rate increase as the submergence ration increases,and the system can lift water and solid effectively when the flow pattern is churn flow.The lifting solid efficiency of jet air-lift is higher than that of traditional one,especially in the condition of high air flow rate and low submergence ration.%由于传统气举提升效率较低,笔者设计出环形射流泵结构的喷射气举,建立了一套气举提升实验装置,选用精筛选的河沙作为提升对象,实验研究了进气量、浸入率等因素对喷射气举扬水量、扬固量的影响规律,对提升管内的流动形态进行了分析,并对传统气举和喷射气举的扬固能力进行对比;运用能量守恒定律建立了气举效率模型,对喷射气举和传统气举的扬固效率进行对比分析。结果表明:存在最优进气量,使喷射气举的扬固量和扬水量最高,浸入率越大,喷射气举的扬固量和扬水量越高,提升管内流动形态为团状流时能有效提升固液混合物;喷射气举扬固效率高于传统气举,在高进气量和低浸入率条件下尤为明显。

  5. Reduction in anisotropy of mechanical properties of coilable (α+β)-type titanium alloy thin sheet through simple heat treatment for use in next-generation aircraft applications

    International Nuclear Information System (INIS)

    In order to reduce the anisotropy of mechanical properties of a coilable thin sheet of (α+β)-type titanium alloy, Ti–4.5Al–2Mo–1.6V–0.5Fe–0.3Si–0.03C (Ti9), for use in aircraft applications, duplex heat treatments were examined. In each duplex heat treatment, the first heat treatment controls the volume fraction of the primary α phase and orientation of the acicular α phase in (α+β) two-phase area between the primary α grains, whereas the second heat treatment stabilizes the α and β phases. The microstructure of the Ti9 sheet after the duplex heat treatment was analyzed by optical microscopy, pole-figure measurement through X-ray diffraction, and electron backscatter diffraction. The mechanical properties of the duplex heat-treated Ti9 sheet were evaluated by tensile tests. The Ti9 sheet was heat treated to obtain two different types of microstructures. A microstructure consisting of acicular α phase in the β grains was obtained by a first heat treatment above the β transus (1273 K) followed by water quenching and a second heat treatment at 973 K. A microstructure consisting of equiaxed primary α grains and an (acicular α+β) two-phase area between the primary α grains was obtained by heating below the β transus (1123–1223 K) followed by water quenching and a second heat treatment at 973 K. The volume fraction of the primary α grains decreased and the volume fraction of the acicular α phase with 12 variants increased instead of increasing first heat-treatment temperature, suppressing the alignment of the c axis of the α lattice parallel to the transverse direction within the rolling plane (T-texture formation) as a result. Anisotropy of the tensile properties can be decreased by increasing the first heat-treatment temperature because the T texture was decreased

  6. A nitrogen doped low-dislocation density free-standing single crystal diamond plate fabricated by a lift-off process

    International Nuclear Information System (INIS)

    A nitrogen-doped single crystal diamond plate with a low dislocation density is fabricated by chemical vapor deposition (CVD) from a high pressure high temperature synthetic type IIa seed substrate by ion implantation and lift-off processes. To avoid sub-surface damage, the seed surface was subjected to deep ion beam etching. In addition, we introduced a nitrogen flow during the CVD step to grow low-strain diamond at a relatively high growth rate. This resulted in a plate with low birefringence and a dislocation density as low as 400 cm−2, which is the lowest reported value for a lift-off plate. Reproducing this lift-off process may allow mass-production of single crystal CVD diamond plates with low dislocation density and consistent quality.

  7. Demonstration results of fly-by-light flight control system architectures for tactical military aircraft

    Science.gov (United States)

    Corrigan, Jack; Shaw, Brad; Jones, Jack E.

    1996-10-01

    Requirements for future advanced tactical aircraft identify the need for flight control system architectures that provide a higher degree of performance with regard to electromagnetic interference immunity, communication bus data rate, propulsion/utility subsystem integration, and affordability. Evolution for highly centralized, digital, fly-by-light flight/propulsion/utility control system is achieved as modular functions are implemented and integrated by serial digital fiberoptic communication links. These adaptable architectures allow the user to configure the fly- by-light system to meet unique safety requirements, system performance, and design-to-cost targets. This paper presents results of the open and closed loop system demonstrations of Fly-By-Light Advanced System Hardware architecture building blocks integrated with SAE AS-1773 communication bus at MDA.

  8. Understanding Wing Lift

    Science.gov (United States)

    Silva, J.; Soares, A. A.

    2010-01-01

    The conventional explanation of aerodynamic lift based on Bernoulli's equation is one of the most common mistakes in presentations to school students and is found in children's science books. The fallacies in this explanation together with an alternative explanation for aerofoil lift have already been presented in an excellent article by Babinsky…

  9. Effect of electromagnetic interference by neonatal transport equipment on aircraft operation.

    Science.gov (United States)

    Nish, W A; Walsh, W F; Land, P; Swedenburg, M

    1989-06-01

    The number of civilian air ambulance services operating in the United States has been steadily increasing. The quantity and sophistication of electronic equipment used during neonatal transport have also increased. All medical equipment generates some electromagnetic interference (EMI). Excessive EMI can interfere with any of an aircraft's electrical systems, including navigation and communications. The United States military has strict standards for maximum EMI in transport equipment. Over the past 15 years, approximately 70% of neonatal transport monitors, ventilators, and incubators have failed testing due to excessive EMI. As neonatal transport equipment becomes more sophisticated, EMI is increased, and there is greater potential for aircraft malfunction. The Federal Aviation Administration should develop civilian standards for acceptable EMI, civilian aircraft operators must be aware of the possible dangers of excessive EMI, and equipment which does not meet future FAA standards should not be purchased. PMID:2751593

  10. Drag and lift coefficients evolution of a Savonius rotor

    Science.gov (United States)

    Chauvin, A.; Benghrib, D.

    1989-10-01

    The lift and drag coefficients of the rotating Savonius wind machine are determined from the pressure difference measured between the upper plane and the lower plane of a blade. Pressure measurements have been performed for two sets of experiments; the first one for U ∞ = 10 m/s and the second one for U ∞ = 12.5 m/s. In each case it is to be noted that a negative lift effect is present for low values of the tip speed ratio λ. The lift coefficient becomes positive when λ increases. The drag coefficient is of course always negative.

  11. The stable isotopic composition of molecular hydrogen in the tropopause region probed by the CARIBIC aircraft

    Science.gov (United States)

    Batenburg, A. M.; Schuck, T. J.; Baker, A. K.; Zahn, A.; Brenninkmeijer, C. A. M.; Röckmann, T.

    2012-05-01

    More than 450 air samples that were collected in the upper troposphere - lower stratosphere (UTLS) region by the CARIBIC aircraft (Civil Aircraft for the Regular Investigation of the atmosphere Based on an Instrument Container) have been analyzed for molecular hydrogen (H2) mixing ratios (χ(H2)) and H2 isotopic composition (deuterium content, δD). More than 120 of the analyzed samples contained air from the lowermost stratosphere (LMS). These show that χ(H2) does not vary appreciably with O3-derived height above the thermal tropopause (TP), whereas δD does increase with height. The isotope enrichment is caused by H2 production and destruction processes that enrich the stratospheric H2 reservoir in deuterium (D); the exact shapes of the profiles are mainly determined by mixing of stratospheric with tropospheric air. Tight negative correlations are found between δD and the mixing ratios of methane (χ(CH4)) and nitrous oxide (χ(N2O)), as a result of the relatively long lifetimes of these three species. The correlations are described by δD[‰]=-0.35 · χ(CH4)[ppb]+768 and δD[‰]=-1.90· χ(N2O)[ppb]+745. These correlations are similar to previously published results and likely hold globally for the LMS. Samples that were collected from the Indian subcontinent up to 40° N before, during and after the summer monsoon season show no significant seasonal change in χ(H2), but δD is up to 12.3‰ lower in the July, August and September monsoon samples. This δD decrease is correlated with the χ(CH4) increase in these samples. The significant correlation with χ(CH4) and the absence of a perceptible χ(H2) increase that accompanies the δD decrease indicates that microbial production of very D-depleted H2 in the wet season may contribute to this phenomenon. Some of the samples have very high χ(H2) and very low δD values, which indicates a pollution effect. Aircraft engine exhaust plumes are a suspected cause, since the effect mostly occurs in samples

  12. Intensive probing of clear air convective fields by radar and instrumented drone aircraft.

    Science.gov (United States)

    Rowland, J. R.

    1972-01-01

    Clear air convective fields were probed in three summer experiments (1969, 1970, and 1971) on an S-band monopulse tracking radar at Wallops Island, Virginia, and a drone aircraft with a takeoff weight of 5.2 kg, wingspan of 2.5 m, and cruising glide speed of 10.3 m/sec. The drone was flown 23.2 km north of the radar and carried temperature, pressure/altitude, humidity, and vertical and airspeed velocity sensors. Extensive time-space convective field data were obtained by taking a large number of RHI and PPI pictures at short intervals of time. The rapidly changing overall convective field data obtained from the radar could be related to the meteorological information telemetered from the drone at a reasonably low cost by this combined technique.

  13. Inverse lift: a signature of the elasticity of complex fluids?

    OpenAIRE

    Dollet, Benjamin; Aubouy, Miguel; Graner, Francois

    2004-01-01

    To understand the mechanics of a complex fluid such as a foam we propose a model experiment (a bidimensional flow around an obstacle) for which an external sollicitation is applied, and a local response is measured, simultaneously. We observe that an asymmetric obstacle (cambered airfoil profile) experiences a downards lift, opposite to the lift usually known (in a different context) in aerodynamics. Correlations of velocity, deformations and pressure fields yield a clear explanation of this ...

  14. Influences of the position of the head on posture while lifting.

    Science.gov (United States)

    Ishida, H; Watanabe, S; Eguchi, A; Kobara, K

    2008-01-01

    In clinical training of some lower back pain patients, teaching them to control their lumbar lordosis during lifting may be difficult. Therefore, another effective method for lifting technique is required. In standing, head cannot move without some compensating postural adjustment. The purpose of this study was to examine the influence of head position on lifting posture. Fourteen healthy male volunteers (22.6 +/- 4.4 years old) lifted a case while maintaining two different head positions; a downward position and an upright position. In the upright position, activities of the latissimus dorsi and vastus lateralis significantly increased, and these of the biceps femoris significantly decreased during the initial 100 msec phase of lifting. There were no differences in the activities of the upper trapezius, lumbar extensor muscles (L3, L5), and obliquus abdominis under the two conditions. There were also no differences in the lumbar angle when the case was lifted. The flexion angles of the hip, knee, and ankle significantly increased, and the lumbar spine moved closer to the case. Lifting posture was influenced by the head position. Advantages included being able to shift loads on the body from the lower back to the legs, to move the lumbar spine closer to the case, and to relatively increase the moment of lumbar extension. The weight of the head as it moved upward and back, and the weight of the rear part of the body as it moved downward and forward helped to maintain balance. PMID:18551836

  15. Differential conductometry biosensors prepared by lift-off technique by using of e-beam writer with shaped beam

    Czech Academy of Sciences Publication Activity Database

    Krátký, Stanislav; Kolařík, Vladimír; Urbánek, Michal; Matějka, Milan; Horáček, Miroslav; Chlumská, Jana; Neděla, Vilém; Jaffrezic-Renault, N.; Krejčí, J.; Kučerová, R.; Plička, R.; Krejčí, T.

    Cambridge: University of Cambridge, 2013. s. 387. [MNE2013. International Conference on Micro and Nano Engineering /39./. 16.09.2013-19.09.2013, London] Institutional support: RVO:68081731 Keywords : differential conductometry biosensor * electron-beam lithography * microorganism detection Subject RIV: JA - Electronics ; Optoelectronics, Electrical Engineering

  16. 76 FR 63167 - Airworthiness Directives; Diamond Aircraft Industries GmbH Airplanes With Supplemental Type...

    Science.gov (United States)

    2011-10-12

    ... compressor and reactivate the air conditioning system following Premier Aircraft Service Service Bulletin No... cabin air conditioning vapor cycle system (VCS) installed per STC SA03674AT held by Premier Aircraft... FR 37684). That NPRM proposed to require removal of the VCS mount, which could result in the...

  17. The Application of Surface Electromyography in the Assessment of Ergonomic Risk Factors Associated with Manual Lifting Tasks

    Institute of Scientific and Technical Information of China (English)

    陈静; 杨磊; 丁嘉顺; 王正伦

    2004-01-01

    The purpose of this study was to evaluate the ergonomic risk factors associated with manual lifting tasks using surface electromyography (EMG). 13 volunteers lifted loads of 6 and 13kg at two speeds and at two horizontal distances in 3 different postures and three boxes of different sizes, from floor to knuckle height, performing 72 lifting tasks. For each lift, the surface electromyography signals from the erector spinae muscles, bilaterally at T10 and L3, was recorded. The ergonomic risk factors associated with manual lifting tasks were evaluated by comparing the average amplitude of EMG signals from the erector spinae muscles. The EMG average amplitude for lifting the load of 13 kg was 14.3 % greater than that for lifting the load of 6kg (t= -10.93, P<0.01).The EMG average amplitude at the site of L3 was 10.3 % greater than that at the site of T10 (t= -7.98, P<0.01). The EMG average amplitude when performing "fast" lift was 5.9 %greater than the "slow" lift (t= -4.63, P<0.01 ). The posture of lifting affected the EMG average amplitude.It was lowest with semi-squat posture and greatest with squat posture (F= 27.76, P<0.01). The result of multiple stepwise regression analysis showed that the loads of lifting, the size of box, horizontal distance, posture of lifting, the site of the spine subjected to force, lifting speed were the factors affecting the EMG average amplitude. The most significant factor was the loads of lifting,followed by the site of the spine subjected to force and the lifting speed in terms of risk. The ergonomic risk factors associated with manual lifting tasks includes the loads, posture, lifting speed,horizontal distance, the site of the spine subjected to force etc. The results of signal amplitude of EMG from the erector spinae muscles showed that semi-squat posture is the best posture for lifting tasks.

  18. Perception of aircraft Deviation Cues

    Science.gov (United States)

    Martin, Lynne; Azuma, Ronald; Fox, Jason; Verma, Savita; Lozito, Sandra

    2005-01-01

    To begin to address the need for new displays, required by a future airspace concept to support new roles that will be assigned to flight crews, a study of potentially informative display cues was undertaken. Two cues were tested on a simple plan display - aircraft trajectory and flight corridor. Of particular interest was the speed and accuracy with which participants could detect an aircraft deviating outside its flight corridor. Presence of the trajectory cue significantly reduced participant reaction time to a deviation while the flight corridor cue did not. Although non-significant, the flight corridor cue seemed to have a relationship with the accuracy of participants judgments rather than their speed. As this is the second of a series of studies, these issues will be addressed further in future studies.

  19. Practical Ranges of Loudness Levels of Various Types of Environmental Noise, Including Traffic Noise, Aircraft Noise, and Industrial Noise

    Directory of Open Access Journals (Sweden)

    Sabine A. Janssen

    2011-05-01

    Full Text Available In environmental noise control one commonly employs the A-weighted sound level as an approximate measure of the effect of noise on people. A measure that is more closely related to direct human perception of noise is the loudness level. At constant A-weighted sound level, the loudness level of a noise signal varies considerably with the shape of the frequency spectrum of the noise signal. In particular the bandwidth of the spectrum has a large effect on the loudness level, due to the effect of critical bands in the human hearing system. The low-frequency content of the spectrum also has an effect on the loudness level. In this note the relation between loudness level and A-weighted sound level is analyzed for various environmental noise spectra, including spectra of traffic noise, aircraft noise, and industrial noise. From loudness levels calculated for these environmental noise spectra, diagrams are constructed that show the relation between loudness level, A‑weighted sound level, and shape of the spectrum. The diagrams show that the upper limits of the loudness level for broadband environmental noise spectra are about 20 to 40 phon higher than the lower limits for narrowband spectra, which correspond to the loudness levels of pure tones. The diagrams are useful for assessing limitations and potential improvements of environmental noise control methods and policy based on A-weighted sound levels.

  20. Practical ranges of loudness levels of various types of environmental noise, including traffic noise, aircraft noise, and industrial noise.

    Science.gov (United States)

    Salomons, Erik M; Janssen, Sabine A

    2011-06-01

    In environmental noise control one commonly employs the A-weighted sound level as an approximate measure of the effect of noise on people. A measure that is more closely related to direct human perception of noise is the loudness level. At constant A-weighted sound level, the loudness level of a noise signal varies considerably with the shape of the frequency spectrum of the noise signal. In particular the bandwidth of the spectrum has a large effect on the loudness level, due to the effect of critical bands in the human hearing system. The low-frequency content of the spectrum also has an effect on the loudness level. In this note the relation between loudness level and A-weighted sound level is analyzed for various environmental noise spectra, including spectra of traffic noise, aircraft noise, and industrial noise. From loudness levels calculated for these environmental noise spectra, diagrams are constructed that show the relation between loudness level, A-weighted sound level, and shape of the spectrum. The diagrams show that the upper limits of the loudness level for broadband environmental noise spectra are about 20 to 40 phon higher than the lower limits for narrowband spectra, which correspond to the loudness levels of pure tones. The diagrams are useful for assessing limitations and potential improvements of environmental noise control methods and policy based on A-weighted sound levels. PMID:21776205

  1. Laser lift-off technique for freestanding GaN substrate using an In droplet formed by thermal decomposition of GaInN and its application to light-emitting diodes

    International Nuclear Information System (INIS)

    We developed a laser lift-off technique for a freestanding GaN substrate using an In droplet formed by thermal decomposition of GaInN. A combination of an In droplet formed by thermal decomposition of GaInN during growth and a pulsed second-harmonic neodymium-doped yttrium aluminum garnet laser (λ = 532 nm) realized the lift-off GaN substrate. After laser lift-off of the GaN substrate, it was used to achieve 380 nm ultraviolet light-emitting diodes with light output enhanced 1.7-fold. In this way, the light extraction can be improved by removing the GaN substrate.

  2. Standard Test Method for Stress-Corrosion of Titanium Alloys by Aircraft Engine Cleaning Materials

    CERN Document Server

    American Society for Testing and Materials. Philadelphia

    2006-01-01

    1.1 This test method establishes a test procedure for determining the propensity of aircraft turbine engine cleaning and maintenance materials for causing stress corrosion cracking of titanium alloy parts. 1.2 The evaluation is conducted on representative titanium alloys by determining the effect of contact with cleaning and maintenance materials on tendency of prestressed titanium alloys to crack when subsequently heated to elevated temperatures. 1.3 Test conditions are based upon manufacturer's maximum recommended operating solution concentration. This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety and health practices and determine the applicability of regulatory limitations prior to use. For specific precautionary statements, see and .

  3. Abatement of an aircraft exhaust plume using aerodynamic baffles.

    Science.gov (United States)

    Bennett, Michael; Christie, Simon M; Graham, Angus; Garry, Kevin P; Velikov, Stefan; Poll, D Ian; Smith, Malcolm G; Mead, M Iqbal; Popoola, Olalekan A M; Stewart, Gregor B; Jones, Roderic L

    2013-03-01

    The exhaust jet from a departing commercial aircraft will eventually rise buoyantly away from the ground; given the high thrust/power (i.e., momentum/buoyancy) ratio of modern aero-engines, however, this is a slow process, perhaps requiring ∼ 1 min or more. Supported by theoretical and wind tunnel modeling, we have experimented with an array of aerodynamic baffles on the surface behind a set of turbofan engines of 124 kN thrust. Lidar and point sampler measurements show that, as long as the intervention takes place within the zone where the Coanda effect holds the jet to the surface (i.e., within about 70 m in this case), then quite modest surface-mounted baffles can rapidly lift the jet away from the ground. This is of potential benefit in abating both surface concentrations and jet blast downstream. There is also some modest acoustic benefit. By distributing the aerodynamic lift and drag across an array of baffles, each need only be a fraction of the height of a single blast fence. PMID:23343109

  4. Analysis of Aircraft Control Performance using a Fuzzy Rule Base Representation of the Cooper-Harper Aircraft Handling Quality Rating

    Science.gov (United States)

    Tseng, Chris; Gupta, Pramod; Schumann, Johann

    2006-01-01

    The Cooper-Harper rating of Aircraft Handling Qualities has been adopted as a standard for measuring the performance of aircraft since it was introduced in 1966. Aircraft performance, ability to control the aircraft, and the degree of pilot compensation needed are three major key factors used in deciding the aircraft handling qualities in the Cooper- Harper rating. We formulate the Cooper-Harper rating scheme as a fuzzy rule-based system and use it to analyze the effectiveness of the aircraft controller. The automatic estimate of the system-level handling quality provides valuable up-to-date information for diagnostics and vehicle health management. Analyzing the performance of a controller requires a set of concise design requirements and performance criteria. Ir, the case of control systems fm a piloted aircraft, generally applicable quantitative design criteria are difficult to obtain. The reason for this is that the ultimate evaluation of a human-operated control system is necessarily subjective and, with aircraft, the pilot evaluates the aircraft in different ways depending on the type of the aircraft and the phase of flight. In most aerospace applications (e.g., for flight control systems), performance assessment is carried out in terms of handling qualities. Handling qualities may be defined as those dynamic and static properties of a vehicle that permit the pilot to fully exploit its performance in a variety of missions and roles. Traditionally, handling quality is measured using the Cooper-Harper rating and done subjectively by the human pilot. In this work, we have formulated the rules of the Cooper-Harper rating scheme as fuzzy rules with performance, control, and compensation as the antecedents, and pilot rating as the consequent. Appropriate direct measurements on the controller are related to the fuzzy Cooper-Harper rating system: a stability measurement like the rate of change of the cost function can be used as an indicator if the aircraft is under

  5. Evaluation of an exhaust gas evacuation system during propane-fueled lift truck maintenance

    International Nuclear Information System (INIS)

    Exposure to carbon monoxide (CO) gas in the workplace can cause health problem. CO gas is colourless and odourless, and exposure to it can cause intoxication, particularly for mechanics working on internal combustion engines fed by propane-fueled lift trucks. Regular procedures for evacuating the gases emitted during routine mechanical repairs involve the use of rigid evacuating pipes attached to the building and hooked to a flexible pipe at the end of the exhaust pipe. With lift trucks, this procedure is limited because of the configuration of these vehicles, and also because this type of work is often done in places without access to permanent mechanical ventilation. The object of this study was to propose a new evacuation method for CO gas fumes that would lower the exposures of fumes for mechanics and for workstations. It identified the criteria that should be considered, such as the configuration of the existing exhaust system of lift trucks, and feasibility of using this system at a variety of on-site locations. The design of the device was described and evaluated. 7 refs., 6 tabs., 8 figs., 3 appendices

  6. 30 CFR 57.16016 - Lift trucks.

    Science.gov (United States)

    2010-07-01

    ... 30 Mineral Resources 1 2010-07-01 2010-07-01 false Lift trucks. 57.16016 Section 57.16016 Mineral Resources MINE SAFETY AND HEALTH ADMINISTRATION, DEPARTMENT OF LABOR METAL AND NONMETAL MINE SAFETY AND... § 57.16016 Lift trucks. Fork and other similar types of lift trucks shall be operated with the:...

  7. 30 CFR 56.16016 - Lift trucks.

    Science.gov (United States)

    2010-07-01

    ... 30 Mineral Resources 1 2010-07-01 2010-07-01 false Lift trucks. 56.16016 Section 56.16016 Mineral Resources MINE SAFETY AND HEALTH ADMINISTRATION, DEPARTMENT OF LABOR METAL AND NONMETAL MINE SAFETY AND....16016 Lift trucks. Fork and other similar types of lift trucks shall be operated with the— (a)...

  8. Human Factors Lessons Learned from Flight Testing Wingless Lifting Body Vehicles

    Science.gov (United States)

    Merlin, Peter William

    2014-01-01

    Since the 1960s, NASA, the Air Force, and now private industry have attempted to develop an operational human crewed reusable spacecraft with a wingless, lifting body configuration. This type of vehicle offers increased mission flexibility and greater reentry cross range than capsule type craft, and is particularly attractive due to the capability to land on a runway. That capability, however, adds complexity to the human factors engineering requirements of developing such aircraft.

  9. Liquid fallback and the performance of intermittent gas-lift

    Energy Technology Data Exchange (ETDEWEB)

    Santos, Odair G.; Alhanati, Francisco J.S.; Bordalo, Sergio N. [Universidade Estadual de Campinas, SP (Brazil). Faculdade de Engenharia Mecanica. Dept. de Petroleo

    1998-07-01

    The study of liquid fallback in intermittent gas-lift methods shows that the impact of the fallback is misinterpreted in the literature. An explanation of the dynamics of this phenomena is presented as a contribution to a better understanding of the process. The economic analysis of gas-lift plants demonstrates the sensitivity of the performance to the correct evaluation of the effect of the fallback, when ranking the best intermittent methods. (author)

  10. Design and implementation of an expert system for remote fault diagnosis in ship lift

    Institute of Scientific and Technical Information of China (English)

    2007-01-01

    In this paper an expert system for remote fault diagnosis in the ship lift was developed by analysis of the fault tree and combination with VPN. The fault tree was constructed based on the operation condition of the ship lift. The diagnosis model was constructed by hierarchical classification of the fault tree structure, and the inference mechanism was given. Logical structure of the fault diagnosis in the ship lift was proposed. The implementation of the expert system for remote fault diagnosis in the ship...

  11. Lifting of a sector block for YE-2 at Kawasaki.

    CERN Multimedia

    R. Loveless/U. of Wisconsin

    2000-01-01

    YE-2 is build from machined sector blocks. Trial assembly is carried out horizontally. This picture represents the lifting of a machined sector block destined to the trial assembly of a half disk YE-2 at Kawasaki (KHI) Kobe, Japan.

  12. Impact of Advanced Propeller Technology on Aircraft/Mission Characteristics of Several General Aviation Aircraft

    Science.gov (United States)

    Keiter, I. D.

    1982-01-01

    Studies of several General Aviation aircraft indicated that the application of advanced technologies to General Aviation propellers can reduce fuel consumption in future aircraft by a significant amount. Propeller blade weight reductions achieved through the use of composites, propeller efficiency and noise improvements achieved through the use of advanced concepts and improved propeller analytical design methods result in aircraft with lower operating cost, acquisition cost and gross weight.

  13. Lift Enhancement of a Vortex-Sink Attached to a Flat Plate

    CERN Document Server

    Xia, Xi; Mohseni, Kamran

    2012-01-01

    As observed in natural fliers, stabilized vortices on the surface of an airfoil or wing could provide lift enhancement. Similar concept can be applied in fixed lifting surfaces. Potential flow theory is employed to model lift enhancement by attaching a vortex-sink pair to the top surface of a flat plate in a pseudo-steady flow. Using this flow model, a parametric study on the location of the vortex-sink pair is performed in order to optimize lift enhancement. Lift coefficient calculations are presented for a range of vortex-sink positions, vortex-sink strengths, and flat-plate angles of attack. It is shown that beyond the lift contribution terms due to the vortex-sink strength, lift enhancement could be also achieved by a translating velocity of the vortex-sink in a non-equilibrium position. This vortex-sink velocity term is more pronounced when the vortex-sink is placed close to the top surface of the flat-plate near the leading or the trailing edges of the flat plate. It is concluded that increasing the vor...

  14. Noise simulation of aircraft engine fans by the boundary element method

    Science.gov (United States)

    Pyatunin, K. R.; Arkharova, N. V.; Remizov, A. E.

    2016-07-01

    Numerical simulation results of the civil aircraft engine fan stage noise in the far field are presented. Non-steady-state rotor-stator interaction is calculated the commercial software that solves the Navier-Stokes equations using differentturbulence models. Noise propagation to the far acoustic field is calculated by the boundary element method using acoustic Lighthill analogies without taking into account the mean current in the air inlet duct. The calculated sound pressure levels at points 50 m from the engine are presented, and the directional patterns of the acoustic radiation are shown. The use of the eddy resolving turbulence model to calculate rotor-stator interaction increases the accuracy in predicting fan stage noise.

  15. Damage assessment of nuclear containment against aircraft crash

    International Nuclear Information System (INIS)

    Highlights: • Damage assessment of nuclear containment is studied against aircraft crash. • Four impact locations have been identified at the outer containment shell. • The mid of the total height has been found to be most vulnerable location. • The crown of dome has been found to be the strongest location. • Phantom F4 caused more localized and severe damage compared to other aircrafts. - Abstract: The behavior of nuclear containment structure has been studied against aircraft crash with an emphasis on the influence of strike location. The impact locations identified on the BWR Mark III type nuclear containment structure are mid-height, junction of dome and cylinder, crown of dome and arc of dome. The containment at each of the above locations has been impacted normally by Phantom F-4, Boeing 707-320 and Airbus A320 aircrafts. The loading of the aircraft has been assigned through the corresponding reaction-time response curve. ABAQUS/Explicit finite element code has been used to carry out the three-dimensional numerical simulations. The concrete damaged plasticity model was used to simulate the behavior of concrete while the behavior of steel reinforcement was incorporated using the Johnson–Cook elasto-viscoplastic material model. The mid-height of containment has been found to experience most severe deformation against each aircraft. Phantom F4 has been found to be most disastrous at each location. The results have been compared with those of the available studies with respect to the containment deformation

  16. Damage assessment of nuclear containment against aircraft crash

    Energy Technology Data Exchange (ETDEWEB)

    Iqbal, Mohd Ashraf, E-mail: iqbal_ashraf@rediffmail.com; Sadique, Md. Rehan, E-mail: rehan.sadique@gmail.com; Bhargava, Pradeep, E-mail: bhpdpfce@iitr.ac.in; Bhandari, N.M., E-mail: nmbcefce@iitr.ac.in

    2014-10-15

    Highlights: • Damage assessment of nuclear containment is studied against aircraft crash. • Four impact locations have been identified at the outer containment shell. • The mid of the total height has been found to be most vulnerable location. • The crown of dome has been found to be the strongest location. • Phantom F4 caused more localized and severe damage compared to other aircrafts. - Abstract: The behavior of nuclear containment structure has been studied against aircraft crash with an emphasis on the influence of strike location. The impact locations identified on the BWR Mark III type nuclear containment structure are mid-height, junction of dome and cylinder, crown of dome and arc of dome. The containment at each of the above locations has been impacted normally by Phantom F-4, Boeing 707-320 and Airbus A320 aircrafts. The loading of the aircraft has been assigned through the corresponding reaction-time response curve. ABAQUS/Explicit finite element code has been used to carry out the three-dimensional numerical simulations. The concrete damaged plasticity model was used to simulate the behavior of concrete while the behavior of steel reinforcement was incorporated using the Johnson–Cook elasto-viscoplastic material model. The mid-height of containment has been found to experience most severe deformation against each aircraft. Phantom F4 has been found to be most disastrous at each location. The results have been compared with those of the available studies with respect to the containment deformation.

  17. Thrust and Lift generation of heaving and pitching oscillating foil propulsion in ground effect

    Science.gov (United States)

    Mivehchi, Amin; Dahl, Jason M.; Licht, Stephen

    2015-11-01

    Experimental results are presented for the thrust and lift generation on a NACA0012 airfoil undergoing heave and pitch oscillation near a solid boundary. For ground effect in the steady flow over a lifting surface, lift and drag forces are altered by an enhanced spanwise flow around the tip of the lifting surface, resulting in a strong low pressure region on the upper part of the wing and increased lift in the presence of a boundary. In the present study, this effect is investigated for an inherently unsteady flow, a propulsive flapping foil. It is found that ground effect has a significant effect on the instantaneous and average lift and thrust forces generated by the oscillating foil with heave and pitch motion. It is found that the forces on a flapping foil in the presence of the ground is not only dependent on the aspect ratio but shows high dependency on the kinematics of motion such as maximum angle of attack, frequency of flapping, and the distance from the ground. The relation between these parameters and their effect on the cycle averaged thrust, lift, propulsive efficiency, and instantaneous force over the airfoil is shown. It is hypothesized that ground effect may be used as a proxy sensor for identifying solid boundaries with biomimetic underwater vehicles. Keywords: Ground effect, Flapping foil propulsion, flow-structure interaction.

  18. Modelling and simulation of flexible aircraft : handling qualities with active load control

    OpenAIRE

    Andrews, Stuart P.

    2011-01-01

    The study of the motion of manoeuvring aircraft has traditionally considered the aircraft to be rigid. This simplifying assumption has been shown to give quite accurate results for the flight dynamics of many aircraft types. As modern transport aircraft have developed however, there has been a marked increase in the size and weight of these aircraft. This trend is likely to continue with the development of future blended-wing-body and supersonic transport aircraft. This increas...

  19. Software design to calculate and simulate the mechanical response of electromechanical lifts

    Science.gov (United States)

    Herrera, I.; Romero, E.

    2016-05-01

    Lift engineers and lift companies which are involved in the design process of new products or in the research and development of improved components demand a predictive tool of the lift slender system response before testing expensive prototypes. A method for solving the movement of any specified lift system by means of a computer program is presented. The mechanical response of the lift operating in a user defined installation and configuration, for a given excitation and other configuration parameters of real electric motors and its control system, is derived. A mechanical model with 6 degrees of freedom is used. The governing equations are integrated step by step through the Meden-Kutta algorithm in the MATLAB platform. Input data consists on the set point speed for a standard trip and the control parameters of a number of controllers and lift drive machines. The computer program computes and plots very accurately the vertical displacement, velocity, instantaneous acceleration and jerk time histories of the car, counterweight, frame, passengers/loads and lift drive in a standard trip between any two floors of the desired installation. The resulting torque, rope tension and deviation of the velocity plot with respect to the setpoint speed are shown. The software design is implemented in a demo release of the computer program called ElevaCAD. Further on, the program offers the possibility to select the configuration of the lift system and the performance parameters of each component. In addition to the overall system response, detailed information of transients, vibrations of the lift components, ride quality levels, modal analysis and frequency spectrum (FFT) are plotted.

  20. Modelling of the automatic stabilization system of the aircraft course by a fuzzy logic method

    Science.gov (United States)

    Mamonova, T.; Syryamkin, V.; Vasilyeva, T.

    2016-04-01

    The problem of the present paper concerns the development of a fuzzy model of the system of an aircraft course stabilization. In this work modelling of the aircraft course stabilization system with the application of fuzzy logic is specified. Thus the authors have used the data taken for an ordinary passenger plane. As a result of the study the stabilization system models were realised in the environment of Matlab package Simulink on the basis of the PID-regulator and fuzzy logic. The authors of the paper have shown that the use of the method of artificial intelligence allows reducing the time of regulation to 1, which is 50 times faster than the time when standard receptions of the management theory are used. This fact demonstrates a positive influence of the use of fuzzy regulation.

  1. Decontamination of radioactive P32 and I131 from aircraft and car surfaces by detergent compositions

    International Nuclear Information System (INIS)

    Sheets from aircrafts and cars having the same surfaces were contaminated with solutions of radioactive phosphorus salts and solutions of radioactive iodine salts. Different compositions from synthetic detergents and locally available complexing salts were prepared and their efficiencies in decontaminating the sheets were measured under the same conditions. The most effective compositions were those in which 'Berol Lanco' and 'Nestabon' were used. (orig.)

  2. Adaptive structures for fixed and rotary wing aircraft

    Science.gov (United States)

    Martin, Willi; Jänker, Peter; Siemetzki, Markus; Lorkowski, Thomas; Grohmann, Boris; Maier, Rudolf; Maucher, Christoph; Klöppel, Valentin; Enenkl, Bernhard; Roth, Dieter; Hansen, Heinz

    2007-07-01

    Since more than 10 years EADS Innovation Works, which is the corporate research centre of EADS (European Aeronautic Defence and Space Company), is investigating smart materials and adaptive structures for aircraft in cooperation with EADS business units. Focus of research efforts are adaptive systems for shape control, noise reduction and vibration control of both fixed and rotary wing aircraft as well as for lift optimisation of fixed wing aircraft. Two outstanding adaptive systems which have been pushed ahead in cooperation with Airbus Germany and Eurocopter Germany are adaptive servo flaps for helicopter rotor blades and innovative high lift devices for fixed wing aircraft which both were tested in flight for the first time representing world premieres. In this paper various examples of adaptive systems are presented which were developed and realized by EADS in recent years.

  3. Stereotype threat and lift effects in motor task performance: the mediating role of somatic and cognitive anxiety.

    Science.gov (United States)

    Laurin, Raphael

    2013-01-01

    The aim of this investigation was to replicate the stereotype threat and lift effects in a motor task in a neutral sex-typed activity, using somatic and cognitive anxiety as key mediators of these phenomena. It was hypothesized that an ingroup/outgroup social categorization based on gender would have distinctive effects for female and male participants. A total of 161 French physical education students were randomly assigned to three threat conditions--no threat, female threat, and male threat--thus leading to a 3 x 2 (threat by gender) design. The analyses revealed a stereotype lift effect on the performances for both male and female participants, as well as a stereotype threat effect only for female participants. They also indicated that somatic anxiety had a mediating effect on the performance of female participants targeted by a negative stereotype, but that it had a facilitating effect on their performance. The stereotype threat and lift effects on motor tasks were replicated in a neutral sex-typed activity and somatic anxiety seems to have a facilitating mediating effect of the relationships between the gender-conditions (control or female threat) interaction and free-throw performance. The model used to distinguish somatic and cognitive anxiety appeared to be a relevant means of explaining the stereotype threat and lift mechanisms. PMID:24236380

  4. Conceptual study of advanced VTOL transport aircraft engine; Kosoku VTOL kiyo engine no gainen kento

    Energy Technology Data Exchange (ETDEWEB)

    Saito, Y.; Endo, M.; Matsuda, Y.; Sugiyama, N.; Watanabe, M.; Sugahara, N.; Yamamoto, K. [National Aerospace Laboratory, Tokyo (Japan)

    1996-04-01

    This report proposes the concept of an ultra-low noise engine for advanced high subsonic VTOL transport aircraft, and discusses its technological feasibility. As one of the applications of the previously reported `separated core turbofan engine,` the conceptual engine is composed of 3 core engines, 2 cruise fan engines for high subsonic cruising and 6 lift fan engines producing thrust of 98kN (10000kgf)/engine. The core turbojet engine bleeds a large amount of air at the outlet of a compressor to supply driving high-pressure air for fans to other engines. The lift fan engine is composed of a lift fan, driving combustor, turbine and speed reduction gear, and is featured by not only high operation stability and thin fan engine like a separated core engine but also ultra-low noise operation. The cruise fan engine adopts the same configuration as the lift fan engine. Since this engine configuration has no technological problems difficult to be overcome, its high technological feasibility is expected. 6 refs., 7 figs., 5 tabs.

  5. Topological structures of vortex flow on a flying wing aircraft, controlled by a nanosecond pulse discharge plasma actuator

    Science.gov (United States)

    Du, Hai; Shi, Zhiwei; Cheng, Keming; Wei, Dechen; Li, Zheng; Zhou, Danjie; He, Haibo; Yao, Junkai; He, Chengjun

    2016-06-01

    Vortex control is a thriving research area, particularly in relation to flying wing or delta wing aircraft. This paper presents the topological structures of vortex flow on a flying wing aircraft controlled by a nanosecond plasma dielectric barrier discharge actuator. Experiments, including oil flow visualization and two-dimensional particle image velocimetry (PIV), were conducted in a wind tunnel with a Reynolds number of 0.5 × 106. Both oil and PIV results show that the vortex can be controlled. Oil topological structures on the aircraft surface coincide with spatial PIV flow structures. Both indicate vortex convergence and enhancement when the plasma discharge is switched on, leading to a reduced region of separated flow.

  6. Predictive Maintenance of Hydraulic Lifts through Lubricating Oil Analysis

    Directory of Open Access Journals (Sweden)

    Stamatios S. Kalligeros

    2013-12-01

    Full Text Available This article examines the possibility of measuring lift maintenance through analysis of used hydraulic oil. Hydraulic oils have proved to be a reliable indicator for the maintenance performed on elevators. It has also been proved that the end users or the maintenance personnel do not always conform to the instructions of the elevators’ hydraulic machine manufacturer. Furthermore, by examining the proportion of the metals, an estimation of the corrosion and the wear resistance of the joined moving parts can be observed. Additionally, the presence of chlorine and calcium in hydraulic oils demonstrates their function in a highly corrosive environment.

  7. Modeling and performance of conventional intermittent gas-lift

    Energy Technology Data Exchange (ETDEWEB)

    Santos, Odair G. dos; Alhanati, Francisco J.S.; Bordalo, Sergio N. [Universidade Estadual de Campinas, SP (Brazil). Faculdade de Engenharia Mecanica. Dept. de Engenharia de Petroleo]. E-mail: bordalo@dep.fem.unicamp.br

    1997-07-01

    Artificial lift is used in petroleum production when the energy of the reservoir is not enough to sustain the flow of oil in the well up the surface with satisfactory economic return. The gas-lift is a widely used method of artificial lift; in some cases, the continuous gas-lift (CGL) is not efficient, and one must implement the intermittent gas lift (IGL), for which there are different design options. There are some empirical and questionable rules of thumb to choose between the CGL, but almost no material exists in the literature for the selection among the different intermittent gas-lift designs; furthermore, there are no published models or studies of their dynamics to help in the selection and design of IGL systems. This work present a model to study the CONVENTIONAL IGL. The IGL works in cycles, and each cycle is made of stages that follow transient flow processes. Vertical two-phase flow occurs in the well. This paper presents sample results for typical conditions of the petroleum reservoir, and for variations of the operational parameters. This can aid the engineer in the determination of the optimum values of the operational parameters, and in the choice of the IGL design for particular field conditions. (author)

  8. Modeling and performance of intermittent gas-lift with chamber

    Energy Technology Data Exchange (ETDEWEB)

    Santos, Odair G. dos; Alhanati, Francisco J.S.; Bordalo, Sergio N. [Universidade Estadual de Campinas, SP (Brazil). Faculdade de Engenharia Mecanica. Dept. de Engenharia de Petroleo]. E-mail: bordalo@dep.fem.unicamp.br

    1997-07-01

    Artificial lift is used in petroleum production when the energy of the reservoir is not enough to sustain the flow of oil in the well up to surface with satisfactory economic return. The gas-lift is a widely used method of artificial lift; in some cases, the continuous gas-lift (CGL) is not efficient, and one must implement the intermittent gas-lift (IGL), for which there are different design options. There are some empirical and questionable rules of thumb to choose between the CGL and IGL, but almost no material exists in the literature for the selection among the different intermittent gas-lift designs; furthermore, there are no published models or behavior studies of their dynamics to help in the selection and design of IGL systems. This work presents a model to study the IGL WITH CHAMBER. In this system, a chamber is used to accumulate oil at the bottom of the well. This paper presents sample results for some conditions of the petroleum reservoir, and for variations of the operational parameters. This work can aid the engineer in the determination of the optimum values of the operational parameters, and in the choice of the IGL design for particular field conditions. (author)

  9. Breast lift

    Science.gov (United States)

    Mastopexy; Breast lift with reduction; Breast lift with augmentation ... enlargement with implants) when they have a breast lift. ... it for medical reasons. Women usually have breast lifts to lift sagging, loose breasts. Pregnancy, breastfeeding, and ...

  10. Automation of Workplace Lifting Hazard Assessment for Musculoskeletal Injury Prevention

    OpenAIRE

    Spector, June T.; Lieblich, Max; Bao, Stephen; McQuade, Kevin; Hughes, Margaret

    2014-01-01

    Objectives Existing methods for practically evaluating musculoskeletal exposures such as posture and repetition in workplace settings have limitations. We aimed to automate the estimation of parameters in the revised United States National Institute for Occupational Safety and Health (NIOSH) lifting equation, a standard manual observational tool used to evaluate back injury risk related to lifting in workplace settings, using depth camera (Microsoft Kinect) and skeleton algorithm technology. ...

  11. Key Topics for High-Lift Research: A Joint Wind Tunnel/Flight Test Approach

    Science.gov (United States)

    Fisher, David; Thomas, Flint O.; Nelson, Robert C.

    1996-01-01

    Future high-lift systems must achieve improved aerodynamic performance with simpler designs that involve fewer elements and reduced maintenance costs. To expeditiously achieve this, reliable CFD design tools are required. The development of useful CFD-based design tools for high lift systems requires increased attention to unresolved flow physics issues. The complex flow field over any multi-element airfoil may be broken down into certain generic component flows which are termed high-lift building block flows. In this report a broad spectrum of key flow field physics issues relevant to the design of improved high lift systems are considered. It is demonstrated that in-flight experiments utilizing the NASA Dryden Flight Test Fixture (which is essentially an instrumented ventral fin) carried on an F-15B support aircraft can provide a novel and cost effective method by which both Reynolds and Mach number effects associated with specific high lift building block flows can be investigated. These in-flight high lift building block flow experiments are most effective when performed in conjunction with coordinated ground based wind tunnel experiments in low speed facilities. For illustrative purposes three specific examples of in-flight high lift building block flow experiments capable of yielding a high payoff are described. The report concludes with a description of a joint wind tunnel/flight test approach to high lift aerodynamics research.

  12. Depreciation of aircraft

    Science.gov (United States)

    Warner, Edward P

    1922-01-01

    There is a widespread, and quite erroneous, impression to the effect that aircraft are essentially fragile and deteriorate with great rapidity when in service, so that the depreciation charges to be allowed on commercial or private operation are necessarily high.

  13. Thin lift dewatering of oil sand tailings: optimizing dewatering of fluid fine tailings by controlling polymer mixing

    Energy Technology Data Exchange (ETDEWEB)

    Demoz, A.; Munoz, V.; Mikula, R. [Natural Resources Canada, CanmetENERGY, Devon, Alberta (Canada)

    2011-07-01

    In the oil sands industry, dewatering of tailings is an important issue. Recent work has shown that the addition of polymer helps to enhance dewatering of fluid fine tailings. High molecular weight polymers are used to bind small solids which results in a higher floc strength with no significant effect on water chemistry. The problem of this technique is that polymers only achieve optimal performance within a narrow window. This paper aimed at assessing the effect of mixing on the dewatering performance of polymer treatment on mature fine tailings. Tests were performed with different impeller types, mixing speeds and durations. Results demonstrated that the flocculation process is critical in the dewatering process and that working at the optimal flocculation conditions presents considerable benefits. This paper investigated the importance of mixing on the dewatering process and highlighted that further work has to be undertaken to optimize this process.

  14. Effect of shear heat on hydrodynamic lift of brush seals in oil sealing

    OpenAIRE

    Duran, Ertuğrul Tolga; Duran, Ertugrul Tolga; Akşit, Mahmut Faruk; Aksit, Mahmut Faruk; Doğu, Yahya; Dogu, Yahya

    2006-01-01

    Due to their superior performance and stable leakage characteristics, brush seals are one of the dynamic seals used in oil and oil mist applications in aero-engines and turbines. The viscous medium between the high speed rotor surface and bearing surfaces formed by brush seal bristles generates a hydrodynamic lifting force that determines seal clearance and leakage rate in oil sealing applications. The analytical solution to bristle lifting force can be found by using Reynolds formulation. Fo...

  15. Power consumption of lifts and potential for energy savings; Elektrizitaetsverbrauch und Einspar-Potenziale bei Aufzuegen

    Energy Technology Data Exchange (ETDEWEB)

    Nipkow, J.

    2005-07-01

    This final report for the Swiss Federal Office of Energy (SFOE) reviews the results of a study made on the electricity consumption of lifts, which estimates that around 0.5% of Swiss power consumption is caused by lift installations. The results of measurements made on 33 various lift installations and their power consumption are presented. The SIA 380/4 model used to determine energy consumption on the basis of the number of movements is described. Stand-by and lighting consumption is examined, which, according to the authors' conclusions, offer considerable room for improvement, especially for lifts in residential buildings. A further significant potential for improvement is also noted which can be achieved when renewing older systems. The avoidance of inefficient concepts by the use of guidelines for architects, planners and customers is recommended.

  16. Optimal Sizing of a Photovoltaic-Hydrogen Power System for HALE Aircraft by means of Particle Swarm Optimization

    Directory of Open Access Journals (Sweden)

    Victor M. Sanchez

    2015-01-01

    Full Text Available Over the last decade there has been a growing interest in the research of feasibility to use high altitude long endurance (HALE aircrafts in order to provide mobile communications. The use of HALEs for telecommunication networks has the potential to deliver a wide range of communication services (from high-quality voice to high-definition videos, as well as high-data-rate wireless channels cost effectively. One of the main challenges of this technology is to design its power supply system, which must provide the enough energy for long time flights in a reliable way. In this paper a photovoltaic/hydrogen system is proposed as power system for a HALE aircraft due its high power density characteristic. In order to obtain the optimal sizing for photovoltaic/hydrogen system a particle swarm optimizer (PSO is used. As a case study, theoretical design of the photovoltaic/hydrogen power system for three different HALE aircrafts located at 18° latitude is presented. At this latitude, the range of solar radiation intensity was from 310 to 450 Wh/sq·m/day. The results obtained show that the photovoltaic/hydrogen systems calculated by PSO can operate during one year with efficacies ranging between 45.82% and 47.81%. The obtained sizing result ensures that the photovoltaic/hydrogen system supplies adequate energy for HALE aircrafts.

  17. Monitoring Aircraft Motion at Airports by LIDAR

    Science.gov (United States)

    Toth, C.; Jozkow, G.; Koppanyi, Z.; Young, S.; Grejner-Brzezinska, D.

    2016-06-01

    Improving sensor performance, combined with better affordability, provides better object space observability, resulting in new applications. Remote sensing systems are primarily concerned with acquiring data of the static components of our environment, such as the topographic surface of the earth, transportation infrastructure, city models, etc. Observing the dynamic component of the object space is still rather rare in the geospatial application field; vehicle extraction and traffic flow monitoring are a few examples of using remote sensing to detect and model moving objects. Deploying a network of inexpensive LiDAR sensors along taxiways and runways can provide both geometrically and temporally rich geospatial data that aircraft body can be extracted from the point cloud, and then, based on consecutive point clouds motion parameters can be estimated. Acquiring accurate aircraft trajectory data is essential to improve aviation safety at airports. This paper reports about the initial experiences obtained by using a network of four Velodyne VLP- 16 sensors to acquire data along a runway segment.

  18. Different levels of undermining in face lift - Experience of 141 consecutive cases

    Directory of Open Access Journals (Sweden)

    Panettiere Pietro

    2004-01-01

    Full Text Available CONTEXT: The most revolutionary concept in rhytidectomy is the role of Sub Muscular Aponeurotic System (SMAS, even if many alternative approaches have been proposed. The main aim of face lift is to bring back the time, preventing the "lifted-face" appearance. SETTINGS AND DESIGN: The authors present their personal experience with different levels of undermining, i.e. subperiosteal forehead lift, subcutaneous midface lift with SMAS plication and platysmal suspension, and discuss the anatomical and biomechanical elements of rhytidectomy. RESULTS: Optimal aesthetic results were achieved by repositioning the neck, face and forehead tissues in a global and harmonious fashion, without distorting face characteristics and disguising surgery trails as much as possible. CONCLUSIONS: Different levels of undermining can give good and stable aesthetic results minimizing the risks and preventing face distortion.

  19. Optimal trajectory and heat load analysis of different shape lifting reentry vehicles for medium range application

    OpenAIRE

    S. Tauqeer ul Islam Rizvi; Lin-shu He; Da-jun Xu

    2015-01-01

    The objective of the paper is to compute the optimal burn-out conditions and control requirements that would result in maximum down-range/cross-range performance of a waverider type hypersonic boost-glide (HBG) vehicle within the medium and intermediate ranges, and compare its performance with the performances of wing-body and lifting-body vehicles vis-à-vis the g-load and the integrated heat load experienced by vehicles for the medium-sized launch vehicle under study. Trajectory optimization...

  20. Processing infrared images of aircraft lapjoints

    Science.gov (United States)

    Syed, Hazari; Winfree, William P.; Cramer, K. E.

    1992-01-01

    Techniques for processing IR images of aging aircraft lapjoint data are discussed. Attention is given to a technique for detecting disbonds in aircraft lapjoints which clearly delineates the disbonded region from the bonded regions. The technique is weak on unpainted aircraft skin surfaces, but can be overridden by using a self-adhering contact sheet. Neural network analysis on raw temperature data has been shown to be an effective tool for visualization of images. Numerical simulation results show the above processing technique to be an effective tool in delineating the disbonds.

  1. Power Generation and Distribution System of Modern Civil Aircraft

    Directory of Open Access Journals (Sweden)

    Swapnil Srivastava

    2014-04-01

    Full Text Available As the aircraft industry is moving towards the all electric and More Electric Aircraft (MEA; is the future trend in adopting single power type for driving the non-propulsive aircraft systems; i.e. is the electrical power. The trend in the aircraft industry is to replace hydraulic and pneumatic systems with electrical systems achieving more comfort and monitoring features. The structure of MEA distribution system improves aircraft maintainability, reliability, flight safety and efficiency. Moreover, MEA reduces the emissions of air pollutant gases from aircrafts, which can contribute in significantly solving some of the problems of climate change. However, the MEA puts some challenges on the aircraft electrical system, both in the amount of the required power and the processing and management of this power. MEA electrical distribution systems are mainly in the form of multi-converter power electronic system.

  2. Investigation of relationship between drag and lift coefficients for a generic car model

    OpenAIRE

    Dobrev, Ivan; Massouh, Fawaz

    2014-01-01

    The paper presents a study of aerodynamic characteristics of a car, which has the simplified geometric shape, so called Ahmed body. Flow around the body and the influence of its rear slant angle on drag are widely studied by numerous researchers. However, small number of studies treats the relationship between drag and lift and this phenomenon is not fully understood. To clarify the relationship between lift and drag, experiments are conducted in the wind tunnel of ENSAM - Paris. The study is...

  3. Trust Control of VTOL Aircraft Part Deux

    Science.gov (United States)

    Dugan, Daniel C.

    2014-01-01

    Thrust control of Vertical Takeoff and Landing (VTOL) aircraft has always been a debatable issue. In most cases, it comes down to the fundamental question of throttle versus collective. Some aircraft used throttle(s), with a fore and aft longitudinal motion, some had collectives, some have used Thrust Levers where the protocol is still "Up is Up and Down is Down," and some have incorporated both throttles and collectives when designers did not want to deal with the Human Factors issues. There have even been combinations of throttles that incorporated an arc that have been met with varying degrees of success. A previous review was made of nineteen designs without attempting to judge the merits of the controller. Included in this paper are twelve designs entered in competition for the 1961 Tri-Service VTOL transport. Entries were from a Bell/Lockheed tiltduct, a North American tiltwing, a Vanguard liftfan, and even a Sikorsky tiltwing. Additional designs were submitted from Boeing Wichita (direct lift), Ling-Temco-Vought with its XC-142 tiltwing, Boeing Vertol's tiltwing, Mcdonnell's compound and tiltwing, and the Douglas turboduct and turboprop designs. A private party submitted a re-design of the Breguet 941 as a VTOL transport. It is important to document these 53 year-old designs to preserve a part of this country's aviation heritage.

  4. The stable isotopic composition of molecular hydrogen in the tropopause region probed by the CARIBIC aircraft

    Directory of Open Access Journals (Sweden)

    A. M. Batenburg

    2012-01-01

    Full Text Available More than 450 air samples that were collected in the upper troposphere – lower stratosphere (UTLS region around the tropopause (TP by the CARIBIC aircraft (Civil Aircraft for the Regular Investigation of the Atmosphere Based on an Instrument Container have been analyzed for molecular hydrogen (H2 mixing ratios (m(H2 and H2 isotopic composition (deuterium content, δD.

    More than 120 of the analysed samples consisted of air from the lowermost stratosphere (LMS. These show that m(H2 does not vary appreciably with O3-derived height above the thermal TP, whereas δD does increase with height. The isotope enrichment is caused by competing H2 production and destruction processes that enrich the stratospheric H2 reservoir in deuterium (D; the exact shapes of the profiles are mainly determined by mixing of stratospheric with tropospheric air. Tight negative correlations are found between δD and the mixing ratios of methane (CH4 and nitrous oxide (N2O, as a result of the relatively long lifetimes of these three species. The correlations are described by δ D [‰]=-0.35 · m(CH4[ppb]+768 and δD [‰]=-1.90 · m(N2O[ppb]+745. These correlations are similar to previously published results and likely hold globally.

    Samples that were collected from the Indian subcontinent up to 40° N before, during and after the summer monsoon season show no significant seasonal change in m(H2, but δD is up to 15‰ lower in the July, August and September monsoon samples. This δD lowering is correlated with m(CH4 increase. The significant correlation with m(CH4 and the absence of a perceptible m(H2 increase that accompanies the δD lowering indicates that microbial production

  5. Computer simulation of viscous fingering in a lifting Hele-Shaw cell with grooved plates

    Indian Academy of Sciences (India)

    Sujata Tarafdar; Soma Nag; Tapati Dutta; Suparna Sinha

    2009-10-01

    We simulate viscous fingering generated by separating two plates with a constant force, in a lifting Hele-Shaw cell. Variation in the patterns for different fluid viscosity and lifting force is studied. Viscous fingering is strongly affected by anisotropy. We report a computer simulation study of fingering patterns, where circular or square grooves are etched on to the lower plate. Results are compared with experiments.

  6. The stable isotopic composition of molecular hydrogen in the tropopause region probed by the CARIBIC aircraft

    Directory of Open Access Journals (Sweden)

    A. M. Batenburg

    2012-05-01

    Full Text Available More than 450 air samples that were collected in the upper troposphere – lower stratosphere (UTLS region by the CARIBIC aircraft (Civil Aircraft for the Regular Investigation of the atmosphere Based on an Instrument Container have been analyzed for molecular hydrogen (H2 mixing ratios (χ(H2 and H2 isotopic composition (deuterium content, δD.

    More than 120 of the analyzed samples contained air from the lowermost stratosphere (LMS. These show that χ(H2 does not vary appreciably with O3-derived height above the thermal tropopause (TP, whereas δD does increase with height. The isotope enrichment is caused by H2 production and destruction processes that enrich the stratospheric H2 reservoir in deuterium (D; the exact shapes of the profiles are mainly determined by mixing of stratospheric with tropospheric air. Tight negative correlations are found between δD and the mixing ratios of methane (χ(CH4 and nitrous oxide (χ(N2O, as a result of the relatively long lifetimes of these three species. The correlations are described by δD[‰]=−0.35 · χ(CH4[ppb]+768 and δD[‰]=−1.90· χ(N2O[ppb]+745. These correlations are similar to previously published results and likely hold globally for the LMS.

    Samples that were collected from the Indian subcontinent up to 40° N before, during and after the summer monsoon season show no significant seasonal change in χ(H2, but δD is up to 12.3‰ lower in the July, August and September monsoon samples. This δD decrease is correlated with the χ(CH4 increase in these samples. The significant correlation with χ(CH4 and the absence of a perceptible χ(H2 increase that accompanies the δD decrease indicates that microbial production of

  7. Wind tunnel tests of high-lift systems for advanced transports using high-aspect-ratio supercritical wings

    Science.gov (United States)

    Allen, J. B.; Oliver, W. R.; Spacht, L. A.

    1982-01-01

    The wind tunnel testing of an advanced technology high lift system for a wide body and a narrow body transport incorporating high aspect ratio supercritical wings is described. This testing has added to the very limited low speed high Reynolds number data base for this class or aircraft. The experimental results include the effects on low speed aerodynamic characteristics of various leading and trailing edge devices, nacelles and pylons, ailerons, and spoilers, and the effects of Mach and Reynolds numbers.

  8. "Dedicated To The Continued Education, Training and Demonstration of PEM Fuel Cell Powered Lift Trucks In Real-World Applications."

    Energy Technology Data Exchange (ETDEWEB)

    Dever, Thomas J.

    2011-11-29

    The project objective was to further assist in the commercialization of fuel cell and H2 technology by building further upon the successful fuel cell lift truck deployments that were executed by LiftOne in 2007, with longer deployments of this technology in real-world applications. We involved facilities management, operators, maintenance personnel, safety groups, and Authorities Having Jurisdiction. LiftOne strived to educate a broad group from many areas of industry and the community as to the benefits of this technology. Included were First Responders from the local areas. We conducted month long deployments with end-users to validate the value proposition and the market requirements for fuel cell powered lift trucks. Management, lift truck operators, Authorities Having Jurisdiction and the general public experienced 'hands on' fuel cell experience in the material handling applications. We partnered with Hydrogenics in the execution of the deployment segment of the program. Air Products supplied the compressed H2 gas and the mobile fueler. Data from the Fuel Cell Power Packs and the mobile fueler was sent to the DOE and NREL as required. Also, LiftOne conducted the H2 Education Seminars on a rotating basis at their locations for lift trucks users and for other selected segments of the community over the project's 36 month duration. Executive Summary The technology employed during the deployments program was not new, as the equipment had been used in several previous demos and early adoptions within the material handling industry. This was the case with the new HyPx Series PEM - Fuel Cell Power Packs used, which had been demo'd before during the 2007 Greater Columbia Fuel Cell Challenge. The Air Products HF-150 Fueler was used outdoors during the deployments and had similarly been used for many previous demo programs. The methods used centered on providing this technology as the power for electric sit-down lift trucks at high profile companies

  9. Evaluation of STOL approach and landing of the quiet STOL experimental aircraft `ASKA`; Teisoon STOL jikkenki `ASKA` no soju hyoka

    Energy Technology Data Exchange (ETDEWEB)

    Nakamura, M.; Terui, Y. [National Aerospace Laboratory, Tokyo (Japan)

    1997-12-01

    Quiet STOL experimental aircraft `ASKA` was developed to establish power lift techniques which allow aircraft to land at a lower speed and steeper angle, to reduce noise around airfields and required runway length. The flight tests were conducted in the 1986 to 1989 period at Gifu airfield. This paper describes STOL landing behavior, with special emphasis placed on its landing maneuverability. It lands at a 2 times steeper angle than the conventional aircraft, for which its power is controlled to secure more accurate landing path. A number of valuable data were collected for maneuverability of landing attitude control, landing accuracy, effects of wind on landing stability and visual fields by the landing tests repeated 121 times. 5 refs., 18 tabs.

  10. Using Fly-By-Wire Technology in Future Models of the UH-60 and Other Rotary Wing Aircraft

    Science.gov (United States)

    Solem, Courtney K.

    2011-01-01

    Several fixed-winged airplanes have successfully used fly-by-wire (FBW) technology for the last 40 years. This technology is now beginning to be incorporated into rotary wing aircraft. By using FBW technology, manufacturers are expecting to improve upon the weight, maintenance time and costs, handling and reliability of the aircraft. Before mass production of this new system begins in new models such as the UH-60MU, testing must be conducted to insure the safety of this technology as well as to reassure others it will be worth the time and money to make such a dramatic change to a perfectly functional machine. The RASCAL JUH-60A has been modified for these purposes. This Black Hawk helicopter has already been equipped with the FBW technology and can be configured as a near perfect representation of the UH-60MU. Because both machines have very similar qualities, the data collected from the RASCAL can be used to make future decisions about the UH-60MU. The U.S. Army AFDD Flight Project Office oversees all the design modifications for every hardware system used in the RASCAL aircraft. This project deals with specific designs and analyses of unique RASCAL aircraft subsystems and their modifications to conduct flight mechanics research.

  11. Time series and correlation of pulsations observed simultaneously by two aircraft

    International Nuclear Information System (INIS)

    Geomagnetic pulsations are an interesting and ubiquitous component of the geomagnetic field and they have been studied extensively for several decades. Numerous comparisons have been made of pulsations at a variety of sites for various objectives. However, conductivity anomalies introduce a number of complexities into the interpretations of pulsations at ground sites through the action of the primary fields on the electrical properties of the local geologic structure. To avoid the difficulties associated with conductivity irregularities, Ochadlick et al. [1985] described an aeromagnetic approach using two aircraft for studying the relationship between pulsations observed over a deep ocean area. Relative to land regions, a deep sea is presumably a more uniform conductor. Using the dual aeromagnetic results, Ochadlick found that the correlation coefficient of pulsations remained relatively constant for observation points spaced apart from a few to about 150 km. Beyond 150 km the correlation coefficient was found to decrease. This letter summarizes the time series records of pulsations, totaling about 9 h, acquired during several dual aircraft flights performed between 20 May and 15 Aug 1985 and presents the associated correlation coefficient between the dual aircraft data sets. Apparently, those measurements show for the first time that a strong similarity of pulsations weakens quickly at a distance of ∼150 km which is remarkably close to the ionospheric height and is thus suggestive of a strong ionospheric control on the spatial coherence of pulsations

  12. Development of Facial Rejuvenation Procedures: Thirty Years of Clinical Experience with Face Lifts.

    Science.gov (United States)

    Kim, Byung Jun; Choi, Jun Ho; Lee, Yoonho

    2015-09-01

    Facial rejuvenation procedures can be roughly divided into face lift surgery and nonoperative, less invasive procedures, such as fat grafts, fillers, botulinum toxin injections, thread lifts, or laserbrasion. Face lift surgery or rhytidectomy is the procedure most directly associated with rejuvenation, due to its fundamental ability to restore the anatomical changes caused by aging. Various methods of face lift surgery have been developed over the last hundred years, thanks to advances in the understanding of facial anatomy and the mechanisms of aging, as well as the dedication of innovative surgeons. However, no generally applicable standard method exists, because the condition of each patient is different, and each operative method has advantages and disadvantages. Specific characteristics of the skin of Asians and their skeletal anatomy should be considered when determining the operative method to be used on Asian patients. Plastic surgeons should improve their ability to analyze the original aesthetic properties and problem areas of each patient, drawing on scientific knowledge about the aging process, and they should develop the skills necessary to perform various rejuvenative techniques. In the present article, we reviewed various face lift procedures and the current methods of modified double plane face lift, based on our clinical experience of over 30 years. PMID:26430622

  13. Greenhouse effects of aircraft emissions as calculated by a radiative transfer model

    OpenAIRE

    Fortuin, J.P.F.; Dorland, R.; Wauben, W. M. F.; Kelder, H.

    1995-01-01

    With a radiative transfer model, assessments are made of the radiative forcing in northern mid-latitudes due to aircraft emissions up to 1990. Considered are the direct climate effects from the major combustion products carbon dioxide, nitrogen dioxide, water vapor and sulphur dioxide, as well as the indirect effect of ozone production from NOx emissions. Our study indicates a local radiative forcing at the tropopause which should be negative in summe...

  14. Development and testing of advanced redundancy management methods for the F-8 DFBW aircraft. [failure detection for Digital Fly By Wire systems

    Science.gov (United States)

    Deyst, J.; Deckert, J.; Desai, M.; Willsky, A.

    1977-01-01

    A reliable aircraft sensor failure detection and identification (FDI) technique is presented. The technique exploits the kinematic and dynamic relationships that exist between variables measured by dissimilar sensors to identify failures in the sensors. The method is applied to management of dual redundant sensors on the NASA F-8 digital fly-by-wire (DFBW) research aircraft.

  15. The design and development of electric vehicle-carried device for lifting submersible pump

    International Nuclear Information System (INIS)

    An electric vehicle-carried device for lifting submersible pump was designed and developed, and the electric vehicle-carried device consists of winch, power equipment, transmission system guide device, etc. The condition in which submersible pump was artificially lifted and put down during in-situ leaching operation has been fundamentally exchanged by using the electro vehicle-carried device, hence, reducing the labor intensity,and improving production efficiency and safety of operation process. (authors)

  16. The contribution of aircraft emissions to the atmospheric sulfur budget

    Energy Technology Data Exchange (ETDEWEB)

    Kjellstroem, E. [Stockholm Univ. (Sweden). Dept. of Meteorology; Feichter, J. [Max-Planck-Institut fuer Meteorologie, Hamburg (Germany); Sausen, R.; Hein, R. [Deutsches Zentrum fuer Luft- und Raumfahrt (DLR), Oberpfaffenhofen (Germany). Inst. fuer Physik der Atmosphaere

    1998-01-01

    An atmospheric general circulation model including the atmospheric sulfur cycle has been used to investigate the impact of aircraft sulfur emissions on the global sulfur budget of the atmosphere. The relative contribution from aircraft sulfur to the atmospheric sulfate burden is larger than the ratio between aircraft emissions and surface emissions due to the calculated long turn-over time of aircraft sulfate (about 12 days). However, in terms of the sulfate mass balance, aircraft emissions are small, contributing about 1% of the total sulfate mass north of 40 deg C where the aircraft emissions are largest. Despite this small contribution to sulfate mass, the aircraft emissions could potentially significantly enhance the background number concentration of aerosol particles. Based on the model calculations the increased stratospheric background aerosol mass observed during the last decades can not be explained by increased aircraft sulfur emissions 50 refs, 9 figs, 4 tabs

  17. Damage tolerance analysis of aircraft reinforced panels

    Directory of Open Access Journals (Sweden)

    A. Pirondi

    2011-04-01

    Full Text Available This work is aimed at reproducing numerically a campaign of experimental tests performed for the development of reinforced panels, typically found in aircraft fuselage. The bonded reinforcements can significantly reduce the rate of fatigue crack growth and increase the residual strength of the skin. The reinforcements are of two types: stringers and doublers. The former provides stiffening to the panel while the latter controls the crack growth between the stringers. The purpose of the study is to validate a numerical method of analysis that can predict the damage tolerance of these reinforced panels. Therefore, using a fracture mechanics approach, several models (different by the geometry and the types of reinforcement constraints were simulated with the finite element solver ABAQUS. The bonding between skin and stiffener was taken either rigid or flexible due to the presence of adhesive. The possible rupture of the reinforcements was also considered. The stress intensity factor trend obtained numerically as a function of crack growth was used to determine the fatigue crack growth rate, obtaining a good approximation of the experimental crack propagation rate in the skin. Therefore, different solutions for improving the damage tolerance of aircraft reinforced panels can be virtually tested in this way before performing experiments.

  18. Analysis of Aircraft Crash Accident for WETF

    International Nuclear Information System (INIS)

    This report applies the methodology of DOE-STD-3014-96, ''Accident Analysis for Aircraft Crash into Hazardous Facilities'', to the Weapons Engineering Tritium Facility (WETF) at LANL. Straightforward application of that methodology shows that including local helicopter flights with those of all other aircraft with potential to impact the facility poses a facility impact risk slightly in excess of the DOE standard's threshold--10-6 impacts per year. It is also shown that helicopters can penetrate the facility if their engines impact that facility's roof. However, a refinement of the helicopter impact analysis shows that penetration risk of the facility for all aircraft lies below the DOE standard's threshold. By that standard, therefore, the potential for release of hazardous material from the facility as a result of an aircraft crashing into the facility is negligible and need not be analyzed further

  19. Effect of hydrogen addition on autoignited methane lifted flames

    KAUST Repository

    Choin, Byung Chul

    2012-01-01

    Autoignited lifted flames in laminar jets with hydrogen-enriched methane fuels have been investigated experimentally in heated coflow air. The results showed that the autoignited lifted flame of the methane/hydrogen mixture, which had an initial temperature over 920 K, the threshold temperature for autoignition in methane jets, exhibited features typical of either a tribrachial edge or mild combustion depending on fuel mole fraction and the liftoff height increased with jet velocity. The liftoff height in the hydrogen-assisted autoignition regime was dependent on the square of the adiabatic ignition delay time for the addition of small amounts of hydrogen, as was the case for pure methane jets. When the initial temperature was below 920 K, where the methane fuel did not show autoignition behavior, the flame was autoignited by the addition of hydrogen, which is an ignition improver. The liftoff height demonstrated a unique feature in that it decreased nonlinearly as the jet velocity increased. The differential diffusion of hydrogen is expected to play a crucial role in the decrease in the liftoff height with increasing jet velocity.

  20. The simulation of the transport of aircraft emissions by a three-dimensional global model

    OpenAIRE

    Velders, G.J.M.; Heijboer, L. C.; Kelder, H.

    1994-01-01

    A three-dimensional off-line tracer transport model coupled to the ECMWF analyses has been used to study the transport of trace gases in the atmosphere. The model gives a reasonable description of their general transport in the atmosphere. The simulation of the transport of aircraft emissions (as NOx) has been studied as well as the transport of passive tracers injected at different altitudes in the North Atlantic flight corridor. A large zonal variation in the NO

  1. Comparative Kinematic Analysis of the Snatch Lifts in Elite Male Adolescent Weightlifters

    Directory of Open Access Journals (Sweden)

    Erbil Harbili

    2014-06-01

    Full Text Available The purpose of the study was to compare the linear kinematics of the barbell and the angular kinematics of the lower limb during the snatch lifts of two different barbell weights in elite male adolescent weightlifters. In the national team level, nine elite male adolescent weightlifters participated in the study. The snatch lifts were recorded by two video cameras under competitive conditions in preparation period before the European Junior Championship (Sony MiniDv PAL- 50 field/s and the two heaviest successful lifts were selected for kinematic analysis. The little toe, ankle, knee, hip, and shoulder on the body and one point on the barbell were digitized using Ariel Performance Analysis System (APAS, San Diego, CA, USA. Significant decreases were found in the maximum barbell height, the relative power output during the second pull, and the maximum vertical velocity of the barbell during the second pull of the heaviest lift (p < 0.05. Maximum extension velocity of the hip joint significantly increased during the first pull of the heaviest lift (p < 0.05. As the mass of the barbell increased, the maximum vertical velocity and the maximum height of the barbell and relative power output during the second pull decreased in the heaviest lift performed by adolescent weightlifters. Coaches should pay attention to assistant exercises to increase explosive strength during the second pull with maximum strength in male adolescent weightlifters.

  2. Modeling of Wall Effects on Drag and Lift Acting on Bubbles in Bubbly Flow

    International Nuclear Information System (INIS)

    The two-fluid model based on Eulerian-Eulerian approach has been widely used for simulating two-phase flows in many industrial applications. However, the two-fluid approach needs accurate modeling for interfacial momentum exchange such as drag, shear induced lift, and wall-induced lift. In particular, it is important to accurately model the wall effect in order to predict 'wall peaking' or 'core peaking' phenomena observed in bubbly pipe flow. Those phenomena characterized by the radial distribution of void fraction are mainly determined by the balance between shear induced lift and wall-induced lift usually called 'wall lubrication force'. However, the wall effect is not fully understood yet and the wall force coefficient in previous studies has a wide range of values, probably tuned to the experimental results. Therefore, we propose a new model considering the wall effect on drag and lift forces and evaluate its accuracy by simulating laminar bubbly flows with available data for comparison. In this study, we proposed a new model for interfacial momentum exchange for wall-bounded bubbly flow. In particular, to accurately consider the wall effects on drag and lift, separate simulations were performed for the flow around a moving sphere near the wall. The present model was verified by solving the laminar bubbly flow in a vertical pipe and comparing the results with previous ones. The present void fraction and water velocity profiles showed good results

  3. Man-eating and cattle-lifting by tigers and conservation implications in India

    OpenAIRE

    Chauhan, N. P. S.

    2011-01-01

    We investigated the incidences of human casualties and cattle-lifting by tigers and circumstances of attacks and suggested mitigation strategies. In India, tigers mostly survive in small numbers in protected areas which are isolated due to habitat fragmentation and disturbances. Man-killing behaviour and predation on cattle are the main issues of confrontation, and as a result, the conservation efforts are adversely affected. In the states of Uttar Pradesh, Uttarakhand, Rajasthan, Madhya Prad...

  4. The reproductive system function at women athletes are training by lifting and taekwondo

    Directory of Open Access Journals (Sweden)

    Nekhanevich O.B.

    2010-01-01

    Full Text Available The purpose of investigation is studying the character and leading mechanisms of reproductive system pathology at women athletes are training by lifting and taekwondo. The object of research was the medical control at women are training in lifting and taekwondo. The results of the research have shown that the physical and psychoemotional overexertion with restriction of eating lead to adrenocorticotropic horomon considerable quantity emission which stimulates suprarenal glands and cause the development of hyperanrogenemy and ovaries functions depression. The athletes have more frequent menstrual cycle disturbances such as opsomenorrhea, oligomenorrhea and algodysmenorrhea. Typically there are changes of indices of physical development, appearance the symptoms of psychological masculinithation, hirsutism and secondary ovaries disturbance.

  5. Greenhouse effects of aircraft emissions as calculated by a radiative transfer model

    Directory of Open Access Journals (Sweden)

    J. P. F. Fortuin

    Full Text Available With a radiative transfer model, assessments are made of the radiative forcing in northern mid-latitudes due to aircraft emissions up to 1990. Considered are the direct climate effects from the major combustion products carbon dioxide, nitrogen dioxide, water vapor and sulphur dioxide, as well as the indirect effect of ozone production from NOx emissions. Our study indicates a local radiative forcing at the tropopause which should be negative in summer (–0.5 to 0.0 W/m2 and either negative or positive in winter (–0.3 to 0.2 W/m2. To these values the indirect effect of contrails has to be added, which for the North Atlantic Flight Corridor covers the range –0.2 to 0.3 W/m2 in summer and 0.0 to 0.3 W/m2 in winter. Apart from optically dense non-aged contrails during summer, negative forcings are due to solar screening by sulphate aerosols. The major positive contributions come from contrails, stratospheric water vapor in winter and ozone in summer. The direct effect of NO2 is negligible and the contribution of CO2 is relatively small.

  6. A Chain-Type Price Index for New Business Jet Aircraft

    OpenAIRE

    Dong W. Cho

    2006-01-01

    This paper presents a price index constructed to measure the real price and real output of corporate business jet aircraft. It employs a chained price index methodology to properly account for the effect of changes in aircraft quality and product lines on the price index. The index indicates that the average price level of corporate jets has significantly outpaced the general price level measured by the GDP deflator, nearly doubling the real price of the product over a 35-year period from 196...

  7. Development and evaluation of an affordable lift device to reduce musculo-skeletal injuries among home support workers.

    Science.gov (United States)

    Heacock, Helen; Paris-Seeley, Nancy; Tokuno, Craig; Frederking, Sara; Keane, Brian; Mattie, Johanne; Kanigan, Ryan; Watzke, James

    2004-07-01

    Home support workers (HSWs) work in clients' homes assisting with rehabilitation and activities of daily living. Like all health-care professionals, HSWs are at an increased risk for developing back injuries. Lift devices have been shown to reduce injuries to the worker. Presently, there are few lifting devices for home use that cost under $4000 CDN. Our study involved designing a safe and affordable lift device (retail cost under $2000 CDN) to be used by HSWs in the home and evaluating it in a typical bathroom. Thirty-eight HSWs and three seniors evaluated the BCIT lift, a commercially available lift (BHM Medical Inc.) and the manual method of transfer and lift. Results indicated that the BCIT lift was an improvement over the manual method of transferring, and approximated the more expensive, automatic lift in terms of perceived exertion, ease of use and safety. Feedback provided to the researchers has been incorporated into a new, ergonomically sound and marketable lift device. PMID:15159204

  8. The lift-off velocity on the surface of an arbitrary body

    Science.gov (United States)

    Van wal, S.; Scheeres, D. J.

    2016-05-01

    An expression is developed for the velocity at which a particle, moving tangentially on the surface of a body with an arbitrary shape, rotation, and gravitational field, will lift off from that surface and enter orbit. The osculating departure plane in which this lift-off motion occurs is defined by the net particle acceleration and the desired lift-off direction. The body surface is approximated within this plane, at the departure point, with some radius and center of curvature, allowing for a universal, frame-independent lift-off velocity expression. Applying the geometry of plane-ellipsoid intersections, we perform a validation of the full lift-off velocity expression on a number of rotating ellipsoids. Finally, we derive a limit expression for the case of lift-off from a rotating plane, and compare this with the results on curved bodies. This theory has numerous applications to lander/rover surface mobility operations on asteroids, comets, and small moons, as well as to geophysical processes encountered on these bodies.

  9. Modal analysis by holographic interferometry of a turbine blade for aircraft engines

    Science.gov (United States)

    Caponero, Michele A.; De Angelis, Alberto; Filetti, V. R.; Gammella, S.

    1994-11-01

    Within the planning stage devoted to realize an innovative turbine for an aircraft engine, an experimental prototype has been made. Several measurements have been carried out to experimentally verify the expected structural and dynamic features of such a prototype. Expected properties were worked out by finite elements method, using the well-known Nastran software package. Natural frequencies and vibration modes of the designed prototype were computed assuming the turbine being in both `dynamic condition' (rotating turbine at running speed and temperature), and in `static condition' (still turbine at room temperature). We present the experimental modal analysis carried out by time average holographic interferometry, being the prototype in `static condition;' results show the modal behavior of the prototype. Experimental and computed modal features are compared to evaluate the reliability of the finite elements model of the turbine used for computation by the Nastran package; reliability of the finite elements model must be checked to validate results computed assuming the turbine blade is in hostile environments, such as `dynamic condition,' which could hardly be tested by experimental measurements. A piezoelectric transducer was used to excite the turbine blade by sine variable pressure. To better estimate the natural vibration modes, two holographic interferograms have been made for each identified natural frequency, being the sensitivity vector directions of the two interferograms perpendicular to each other. The first ten lower natural frequencies and vibration modes of the blade have been analyzed; experimental and computed results are compared and discussed. Experimental and computed values of natural frequencies are in good agrement between each other. Several differences are present between experimental and computed modal patterns; a possible cause of such discrepancies is identified in wrong structural constraints imposed at nodes of the finite elements

  10. Aeromechanical stability analysis of a multirotor vehicle model representing a hybrid heavy lift airship (HHLA)

    Science.gov (United States)

    Venkatesan, C.; Friedmann, P. P.

    1984-01-01

    Hybrid Heavy Lift Airship (HHLA) is a proposed candidate vehicle aimed at providing heavy lift capability at low cost. This vehicle consists of a buoyant envelope attached to a supporting structure to which four rotor systems, taken from existing helicopters are attached. Nonlinear equations of motion capable of modelling the dynamics of this coupled multi-rotor/support frame/vehicle system have been developed. Using these equations of motion the aeroelastic and aeromechanical stability analysis is performed aimed at identifying potential instabilities which could occur for this type of vehicle. The coupling between various blade, supporting structure and rigid body modes is identified. Furthermore, the effects of changes in buoyancy ratio (Buoyant lift/total weight) on the dynamic characteristics of the vehicle are studied. The dynamic effects found are of considerable importance for the design of such vehicles. The analytical model developed is also useful for studying the aeromechanical stability of single rotor and tandem rotor coupled rotor/fuselage systems.

  11. Integrating the Base of Aircraft Data (BADA) in CTAS Trajectory Synthesizer

    Science.gov (United States)

    Abramson, Michael; Ali, Kareem

    2012-01-01

    The Center-Terminal Radar Approach Control (TRACON) Automation System (CTAS), developed at NASA Ames Research Center for assisting controllers in the management and control of air traffic in the extended terminal area, supports the modeling of more than four hundred aircraft types. However, 90% of them are supported indirectly by mapping them to one of a relatively few aircraft types for which CTAS has detailed drag and engine thrust models. On the other hand, the Base of Aircraft Data (BADA), developed and maintained by Eurocontrol, supports more than 300 aircraft types, about one third of which are directly supported, i.e. they have validated performance data. All these data were made available for CTAS by integrating BADA version 3.8 into CTAS Trajectory Synthesizer (TS). Several validation tools were developed and used to validate the integrated code and to evaluate the accuracy of trajectory predictions generated using CTAS "native" and BADA Aircraft Performance Models (APM) comparing them with radar track data. Results of these comparisons indicate that the two models have different strengths and weaknesses. The BADA APM can improve the accuracy of CTAS predictions at least for some aircraft types, especially small aircraft, and for some flight phases, especially climb.

  12. Optimization of Wastewater Lift Stations for Reduction of Energy Usage and Greenhouse Gas Emissions (WERF Report INFR3R11)

    Science.gov (United States)

    One of the major contributions of Greenhouse Gas (GHG) emissions from water resource recovery facilities results from the energy used by the pumping regime of the lift stations. This project demonstrated an energy-efficient control method of lift station system operation that uti...

  13. GeoTrack: bio-inspired global video tracking by networks of unmanned aircraft systems

    Science.gov (United States)

    Barooah, Prabir; Collins, Gaemus E.; Hespanha, João P.

    2009-05-01

    Research from the Institute for Collaborative Biotechnologies (ICB) at the University of California at Santa Barbara (UCSB) has identified swarming algorithms used by flocks of birds and schools of fish that enable these animals to move in tight formation and cooperatively track prey with minimal estimation errors, while relying solely on local communication between the animals. This paper describes ongoing work by UCSB, the University of Florida (UF), and the Toyon Research Corporation on the utilization of these algorithms to dramatically improve the capabilities of small unmanned aircraft systems (UAS) to cooperatively locate and track ground targets. Our goal is to construct an electronic system, called GeoTrack, through which a network of hand-launched UAS use dedicated on-board processors to perform multi-sensor data fusion. The nominal sensors employed by the system will EO/IR video cameras on the UAS. When GMTI or other wide-area sensors are available, as in a layered sensing architecture, data from the standoff sensors will also be fused into the GeoTrack system. The output of the system will be position and orientation information on stationary or mobile targets in a global geo-stationary coordinate system. The design of the GeoTrack system requires significant advances beyond the current state-of-the-art in distributed control for a swarm of UAS to accomplish autonomous coordinated tracking; target geo-location using distributed sensor fusion by a network of UAS, communicating over an unreliable channel; and unsupervised real-time image-plane video tracking in low-powered computing platforms.

  14. New constructions of twistor lifts for harmonic maps

    DEFF Research Database (Denmark)

    Svensson, Martin; C. Wood, John

    We show that given a harmonic map \\varphi from a Riemann surface into a classical simply connected compact inner symmetric space, there is a J_2-holomorphic twistor lift of \\varphi (or its negative) if and only if it is nilconformal. In the case of harmonic maps of finite uniton number, we give...... algebraic formulae in terms of holomorphic data which describes their extended solutions. In particular, this gives explicit formulae for the twistor lifts of all harmonic maps of finite uniton number from a surface to the above symmetric spaces....

  15. Reduction environmental effects of civil aircraft through multi-objective flight plan optimisation

    International Nuclear Information System (INIS)

    With rising environmental alarm, the reduction of critical aircraft emissions including carbon dioxides (CO2) and nitrogen oxides (NOx) is one of most important aeronautical problems. There can be many possible attempts to solve such problem by designing new wing/aircraft shape, new efficient engine, etc. The paper rather provides a set of acceptable flight plans as a first step besides replacing current aircrafts. The paper investigates a green aircraft design optimisation in terms of aircraft range, mission fuel weight (CO2) and NOx using advanced Evolutionary Algorithms coupled to flight optimisation system software. Two multi-objective design optimisations are conducted to find the best set of flight plans for current aircrafts considering discretised altitude and Mach numbers without designing aircraft shape and engine types. The objectives of first optimisation are to maximise range of aircraft while minimising NOx with constant mission fuel weight. The second optimisation considers minimisation of mission fuel weight and NOx with fixed aircraft range. Numerical results show that the method is able to capture a set of useful trade-offs that reduce NOx and CO2 (minimum mission fuel weight).

  16. Investigation of cross flow fan propulsion for lightweight VTOL aircraft.

    OpenAIRE

    Gossett, Dean H.

    2000-01-01

    As world population increases, road and airport congestion will become increasingly prevalent. A small, cheap vTOL aircraft which can be flown from a driveway to the workplace parking lot would reduce traffic congestion and travel time. A lightweight, single seat commuter type VTOL aircraft is envisioned as the solution to this problem. To achieve a goal of minimum weight, the aircraft aerodynamic design should be optimized for forward flight. Vertical thrust augmentation from a propulsion un...

  17. Alternate method for gas measurement to offshore wells producing by plunger lift

    Energy Technology Data Exchange (ETDEWEB)

    Silva, Sergio Jose Goncalves e [PETROBRAS, Rio de Janeiro, RJ (Brazil). Exploracao e Producao; Mota, Francisco das Chagas [Universidade Federal do Rio Grande do Norte (UFRN), Natal, RN (Brazil)

    2008-07-01

    The purpose of this paper is to describe an alternate method for gas measurement to wells producing by conventional plunger lift to a two phase separator in offshore production systems. The principle of the plunger lift is basically the use of a free piston acting as a mechanical interface between the formation gas and the produced liquids, greatly increasing the well's lifting efficiency. However, when the piston reaches the surface a liquid slug is produced through the flowline and it propagates into the separator where the phases are measured. Usually, orifice meter is widely used in separators to measure steady-state gas flow rate, but when intermittent flow is present, the gas causes the signal saturation of the differential pressure element ({delta}P), resulting in measurement distortion. The solution proposed in this work to estimate the gas flow rate during the liquid slug it was obtained through the mathematical modeling of the separator and with the use of System Identification Theory. Applying the ARX model it was possible to get the best fit to the collected data. So, with this model and its recursive variant (RARX) it was possible to prove that, with reasonable forecast degree, the signal of the gas flow rate can be recovered by starting from the signal of the pressure control valve of the separator. (author)

  18. Analysis of aircraft maintenance models

    Directory of Open Access Journals (Sweden)

    Vlada S. Sokolović

    2011-10-01

    Full Text Available This paper addressed several organizational models of aircraft maintenance. All models presented so far have been in use in Air Forces, so that the advantages and disadvantages of different models are known. First it shows the current model of aircraft maintenance as well as its basic characteristics. Then the paper discusses two organizational models of aircraft maintenance with their advantages and disadvantages. The advantages and disadvantages of different models are analyzed based on the criteria of operational capabilities of military units. In addition to operational capabilities, the paper presents some other criteria which should be taken into account in the evaluation and selection of an optimal model of aircraft maintenance. Performing a qualitative analysis of some models may not be sufficient for evaluating the optimum choice for models of maintenance referring to the selected set of criteria from the scope of operational capabilities. In order to choose the optimum model, it is necessary to conduct a detailed economic and technical analysis of individual tactical model maintenance. A high-quality aircraft maintenance organization requires the highest state and army authorities to be involved. It is necessary to set clear objectives for all the elements of modern air force technical support programs based on the given evaluation criteria.

  19. A Survey of Jet Aircraft PM by TEM in APEX III

    Science.gov (United States)

    VanderWal, Randy L.; Bryg, Victoria M.

    2014-01-01

    Based upon field testing during the NASA led APEX III campaign conducted in November 2005 at the NASA Glenn Research Center in coordination with Continental Airlines and Cleveland Hopkins International Airport. This paper reports observations of particulate emissions collected from a suite of jet engine aircraft to assess differences and similarities in soot macro- micro- and nanostructure using transmission electron microscopy (TEM). Aggregates are compact, primary particle sizes varied and nanostructure mixed. Comparisons are made to more familiar laboratory flame-generated soot as a well-studied point of reference. Results are interpreted in terms of turbulence interacting with the different stages of particle formation and growth.

  20. Characteristics of autoignited laminar lifted flames in heated coflow jets of carbon monoxide/hydrogen mixtures

    KAUST Repository

    Choi, Byungchul

    2012-06-01

    The characteristics of autoignited lifted flames in laminar jets of carbon monoxide/hydrogen fuels have been investigated experimentally in heated coflow air. In result, as the jet velocity increased, the blowoff was directly occurred from the nozzle-attached flame without experiencing a stabilized lifted flame, in the non-autoignited regime. In the autoignited regime, the autoignited lifted flame of carbon monoxide diluted by nitrogen was affected by the water vapor content in the compressed air oxidizer, as evidenced by the variation of the ignition delay time estimated by numerical calculation. In particular, in the autoignition regime at low temperatures with added hydrogen, the liftoff height of the autoignited lifted flames decreased and then increased as the jet velocity increased. Based on the mechanism in which the autoignited laminar lifted flame is stabilized by ignition delay time, the liftoff height can be influenced not only by the heat loss, but also by the preferential diffusion between momentum and mass diffusion in fuel jets during the autoignition process. © 2012 The Korean Society of Mechanical Engineers.

  1. Characterization of non-methane hydrocarbons in Asian summer monsoon outflow observed by the CARIBIC aircraft

    Directory of Open Access Journals (Sweden)

    A. K. Baker

    2010-07-01

    Full Text Available Between April and December 2008 the CARIBIC commercial aircraft conducted monthly measurement flights between Frankfurt, Germany and Chennai, India. These flights covered the period of the Asian summer monsoon (June–September, during which enhancements in a number of atmospheric species were observed in monsoon outflow. In addition to in situ measurements of trace gases and aerosols, whole air samples were collected during the flights, and these were subsequently analyzed for a suite of trace gases that included the non-methane hydrocarbons. Non-methane hydrocarbons are relatively short-lived compounds and the large enhancements in their mixing ratios in the upper troposphere over Southwest Asia between June and September, sometimes more than double their spring and fall means, provides qualitative evidence for the influence of convectively uplifted boundary layer air. The particularly large enhancements of the combustion tracers benzene and ethyne, along with the similarity of their ratios to carbon monoxide and emission ratios from the burning of household biofuels, indicate a strong influence of biofuel burning to NMHC emissions in this region. Conversely, the ratios of ethane and propane to carbon monoxide, along with the ratio between i-butane and n-butane, indicate a significant source of these compounds from the use of LPG and natural gas, and comparison to previous campaigns suggests that this source could be increasing. Photochemical aging patterns of NMHCs showed that the CARIBIC samples were collected in two distinctly different regions of the monsoon circulation: a southern region where air masses had been recently influenced by low level contact and a northern region, where air parcels had spent substantial time in transit in the upper troposphere before being probed. Estimates of age using ratios of individual NMHCs have ranges of 3–6 d in the south and 9–12 d in the north.

  2. Characteristics of autoignited laminar lifted flames in heated coflow jets of carbon monoxide/hydrogen mixtures

    International Nuclear Information System (INIS)

    The characteristics of autoignited lifted flames in laminar jets of carbon monoxide/hydrogen fuels have been investigated experimentally in heated coflow air. In result, as the jet velocity increased, the blowoff was directly occurred from the nozzle attached flame without experiencing a stabilized lifted flame, in the non autoignited regime. In the autoignited regime, the autoignited lifted flame of carbon monoxide diluted by nitrogen was affected by the water vapor content in the compressed air oxidizer, as evidenced by the variation of the ignition delay time estimated by numerical calculation. In particular, in the autoignition regime at low temperatures with added hydrogen, the liftoff height of the autoignited lifted flames decreased and then increased as the jet velocity increased. Based on the mechanism in which the autoignited laminar lifted flame is stabilized by ignition delay time, the liftoff height can be influenced not only by the heat loss, but also by the preferential diffusion between momentum and mass diffusion in fuel jets during the autoignition process

  3. An accelerometer balance for the measurement of roll, lift and drag on a lifting model in a shock tunnel

    International Nuclear Information System (INIS)

    A force balance to measure roll, lift and drag on a lifting aerodynamic body in an ultrashort-duration hypersonic test facility, such as a shock tunnel, has been developed and tested on a flapped, blunt-nosed, triangular lifting body at a freestream Mach number of 8. The flow total enthalpy and the freestream unit Reynolds number were 0.83 MJ kg−1 and 0.98 million, respectively. The balance structure has a soft suspension that allows the model to have a free flight during the short-duration aerodynamic test. The balance was mounted inside the hollow model and was equipped with accelerometers to sense the aerodynamic moment and forces on the model. The measurements were carried out at different angles of incidence of the model and the acquired signals of the accelerometers were reduced to the aerodynamic moment and the force coefficients based on the theories of applied mechanics and aerodynamics. Also, the moment and force coefficients were theoretically calculated based on the Newtonian theory, which is an accepted analytical approach for hypersonic bodies. Good agreement has been observed between the experimental and the analytical results. The method of measurement of roll and lift, and the data on the rolling moment of a lifting body presented in this note are novel. (technical design note)

  4. Assessment of aircraft structural integrity by detecting disbonds through ultrasonic scanning

    Science.gov (United States)

    Abedin, M. N.; Prabhu, D. R.; Winfree, W. P.

    1992-01-01

    A study of nondestructive evaluation of aircraft bonded joints using the contact scanning technique is presented. Reflected signals acquired through the contacting transducer characterize the test region as being bonded or disbonded. Ultrasonic signals are attenuated more rapidly in the bonded regions when compared to disbonded regions. A peak amplitude based method and an artificial neural network are used to classify the signals. Results obtained using an artificial neural network exhibited significant insensitivity to signal variation when compared to the peak amplitude. Very good agreement is observed between results obtained using the present technique and those obtained using immersion scanning.

  5. A Collection of Nonlinear Aircraft Simulations in MATLAB

    Science.gov (United States)

    Garza, Frederico R.; Morelli, Eugene A.

    2003-01-01

    Nonlinear six degree-of-freedom simulations for a variety of aircraft were created using MATLAB. Data for aircraft geometry, aerodynamic characteristics, mass / inertia properties, and engine characteristics were obtained from open literature publications documenting wind tunnel experiments and flight tests. Each nonlinear simulation was implemented within a common framework in MATLAB, and includes an interface with another commercially-available program to read pilot inputs and produce a three-dimensional (3-D) display of the simulated airplane motion. Aircraft simulations include the General Dynamics F-16 Fighting Falcon, Convair F-106B Delta Dart, Grumman F-14 Tomcat, McDonnell Douglas F-4 Phantom, NASA Langley Free-Flying Aircraft for Sub-scale Experimental Research (FASER), NASA HL-20 Lifting Body, NASA / DARPA X-31 Enhanced Fighter Maneuverability Demonstrator, and the Vought A-7 Corsair II. All nonlinear simulations and 3-D displays run in real time in response to pilot inputs, using contemporary desktop personal computer hardware. The simulations can also be run in batch mode. Each nonlinear simulation includes the full nonlinear dynamics of the bare airframe, with a scaled direct connection from pilot inputs to control surface deflections to provide adequate pilot control. Since all the nonlinear simulations are implemented entirely in MATLAB, user-defined control laws can be added in a straightforward fashion, and the simulations are portable across various computing platforms. Routines for trim, linearization, and numerical integration are included. The general nonlinear simulation framework and the specifics for each particular aircraft are documented.

  6. Treatment of open tibial shaft fracture with soft tissue and bone defect caused by aircraft bomb: Case report

    Directory of Open Access Journals (Sweden)

    Golubović Zoran

    2010-01-01

    Full Text Available Introduction. Aircraft bombs can cause severe orthopaedic injuries. Tibia shaft fractures caused by aircraft bombs are mostly comminuted and followed by bone defects, which makes the healing process extremely difficult and prone to numerous complications. The goal of this paper is to present the method of treatment and the end results of treatment of a serious open tibial fracture with soft and bone tissue defects resulting from aircraft bomb shrapnel wounds. Case Outline. A 26-year-old patient presented with a tibial fracture as the result of a cluster bomb shrapnel wound. He was treated applying the method of external bone fixation done two days after wounding, as well as of early coverage of the lower leg soft tissue defects done on the tenth day after the external fixation of the fracture. The external fixator was removed after five months, whereas the treatment was continued by means of functional plaster cast for another two months. The final functional result was good. Conclusion. Radical wound debridement, external bone fixation of the fracture, and early reconstruction of any soft tissue and bone defects are the main elements of the treatment of serious fractures.

  7. Estimated Benefits of Variable-Geometry Wing Camber Control for Transport Aircraft

    Science.gov (United States)

    Bolonkin, Alexander; Gilyard, Glenn B.

    1999-01-01

    Analytical benefits of variable-camber capability on subsonic transport aircraft are explored. Using aerodynamic performance models, including drag as a function of deflection angle for control surfaces of interest, optimal performance benefits of variable camber are calculated. Results demonstrate that if all wing trailing-edge surfaces are available for optimization, drag can be significantly reduced at most points within the flight envelope. The optimization approach developed and illustrated for flight uses variable camber for optimization of aerodynamic efficiency (maximizing the lift-to-drag ratio). Most transport aircraft have significant latent capability in this area. Wing camber control that can affect performance optimization for transport aircraft includes symmetric use of ailerons and flaps. In this paper, drag characteristics for aileron and flap deflections are computed based on analytical and wind-tunnel data. All calculations based on predictions for the subject aircraft and the optimal surface deflection are obtained by simple interpolation for given conditions. An algorithm is also presented for computation of optimal surface deflection for given conditions. Benefits of variable camber for a transport configuration using a simple trailing-edge control surface system can approach more than 10 percent, especially for nonstandard flight conditions. In the cruise regime, the benefit is 1-3 percent.

  8. Does the effect of weight lifting on lymphedema following breast cancer differ by diagnostic method: results from a randomized controlled trial.

    Science.gov (United States)

    Hayes, Sandra C; Speck, Rebecca M; Reimet, Elizabeth; Stark, Azadeh; Schmitz, Kathryn H

    2011-11-01

    The lymphedema diagnostic method used in descriptive or intervention studies may influence results found. The purposes of this work were to compare baseline lymphedema prevalence in the physical activity and lymphedema (PAL) trial cohort and to subsequently compare the effect of the weight-lifting intervention on lymphedema, according to four standard diagnostic methods. The PAL trial was a randomized controlled intervention study, involving 295 women who had previously been treated for breast cancer, and evaluated the effect of 12 months of weight lifting on lymphedema status. Four diagnostic methods were used to evaluate lymphedema outcomes: (i) interlimb volume difference through water displacement, (ii) interlimb size difference through sum of arm circumferences, (iii) interlimb impedance ratio using bioimpedance spectroscopy, and (iv) a validated self-report survey. Of the 295 women who participated in the PAL trial, between 22 and 52% were considered to have lymphedema at baseline according to the four diagnostic criteria used. No between-group differences were noted in the proportion of women who had a change in interlimb volume, interlimb size, interlimb ratio, or survey score of ≥5, ≥5, ≥10%, and 1 unit, respectively (cumulative incidence ratio at study end for each measure ranged between 0.6 and 0.8, with confidence intervals spanning 1.0). The variation in proportions of women within the PAL trial considered to have lymphoedema at baseline highlights the potential impact of the diagnostic criteria on population surveillance regarding prevalence of this common morbidity of treatment. Importantly though, progressive weight lifting was shown to be safe for women following breast cancer, even for those at risk or with lymphedema, irrespective of the diagnostic criteria used. PMID:21562712

  9. Comparison of Response between RC and SC Containment Structures Subjected to Aircraft Impact

    International Nuclear Information System (INIS)

    Since the aircraft terror to the World Trade Center (WTC) on September 11, 2001, an aircraft impact problem has been increasingly interested. The possibilities of aircraft impacts against nuclear power plants are one of important category. To date, the impact load of the analysis on aircraft impacts has been applied to target structures in local areas by using the impact force-time history function of Riera. However, Riera forcing function is not recommended at the expectation of unreasonable damage or perforation to target structures. The numerical analysis of rc and sc containment structures subjected to aircraft impact is performed by using the AUTODYN-3D. It is carried out the four different types for RC and SC structures. Thus, in this study, the different behaviors of containment structures and the safety of SC structure are expected

  10. Lifted Region-Based Belief Propagation

    OpenAIRE

    Smith, David; Singla, Parag; Gogate, Vibhav

    2016-01-01

    Due to the intractable nature of exact lifted inference, research has recently focused on the discovery of accurate and efficient approximate inference algorithms in Statistical Relational Models (SRMs), such as Lifted First-Order Belief Propagation. FOBP simulates propositional factor graph belief propagation without constructing the ground factor graph by identifying and lifting over redundant message computations. In this work, we propose a generalization of FOBP called Lifted Generalized ...

  11. Effect of local pipe bends on pump performance of a small air-lift system in transporting solid particles

    International Nuclear Information System (INIS)

    The pump performance of a small air-lift system in transporting solid particles is investigated experimentally. Three types of riser pipe were used to examine the effect of local bends of riser pipes on the flow characteristics of a three-phase air-water-solid particles mixture. Two of them were locally S-shaped either below or above a gas injector. The other was vertically straight. Alumina particles of 3 or 5 mm diameter were used as solid particles. It is indicated that the pump performance is appreciably reduced when the pipe bend is above the gas injector. The critical condition under which solid particles are vertically lifted is discussed from a practical viewpoint. In addition, the particle motion in the region of a pipe bend is investigated by photographic observations

  12. Review of Aircraft Electric Power Systems and Architectures

    DEFF Research Database (Denmark)

    Zhao, Xin; Guerrero, Josep M.; Wu, Xiaohao

    2014-01-01

    In recent years, the electrical power capacity is increasing rapidly in more electric aircraft (MEA), since the conventional mechanical, hydraulic and pneumatic energy systems are partly replaced by electrical power system. As a consequence, capacity and complexity of aircraft electric power...... systems (EPS) will increase dramatically and more advanced aircraft EPSs need to be developed. This paper gives a brief description of the constant frequency (CF) EPS, variable frequency (VF) EPS and advanced high voltage (HV) EPS. Power electronics in the three EPS is overviewed. Keywords: Aircraft Power...... System, More Electric Aircraft, Constant Frequency, Variable Frequency, High Voltage....

  13. The simulation of the transport of aircraft emissions by a three-dimensional global model

    Directory of Open Access Journals (Sweden)

    G. J. M. Velders

    Full Text Available A three-dimensional off-line tracer transport model coupled to the ECMWF analyses has been used to study the transport of trace gases in the atmosphere. The model gives a reasonable description of their general transport in the atmosphere. The simulation of the transport of aircraft emissions (as NOx has been studied as well as the transport of passive tracers injected at different altitudes in the North Atlantic flight corridor. A large zonal variation in the NOx concentrations as well as large seasonal and yearly variations was found. The altitude of the flight corridor influences the amount of tracers transported into the troposphere and stratosphere to a great extent.

  14. Screening of external hazards for NPP with bank type reactor. Modeling of safety related systems and equipment for RBMK. Probabilistic assessment of NPP safety on aircraft impact. Progress report

    International Nuclear Information System (INIS)

    This progress report was produced within the frame of IAEA research project on screening the hazards for NPP with bank type reactor. It covers the following tasks; development of the model for the primary loop system of RBMK; developing the models for safety related equipment of RBMK; developing of models for safety related models of EGP-6 type reactor (Bilibinskaya Nuclear Co-generated heat and Power Plant); and probabilistic assessment of NPP safety on aircraft impact

  15. Hydraulic lift-off issues for application of high performance annular fuels in pressurized water reactors

    International Nuclear Information System (INIS)

    Highlights: • Pin and assembly lift-off forces are compared between solid and annular fuel. • Annular fuel experiences much stronger uplift forces. • Much stronger hold-down forces are required by annular fuel assembly. • Engineering modifications for hold-down mechanisms are required by annular fuel. - Abstract: In the PWR core, the fuel assembly is firmly seated on the lower core plate during operation. However, if the hydraulic force exerted on the fuel assembly by coolant flow is too large and the fuel assembly is lifted-off from the lower core plate, the excessive vibration will cause fuel failure. Therefore, the hydraulic lift-off issue needs to be addressed when the advanced fuel assembly is developed. It has been shown that the advanced annular fuel design with internal cooling allows power uprating up to 50% while the peak temperature of the fuel can be reduced and the MDNBR can be maintained. However, if the coolant condition in the core is kept unchanged, increasing the core power by 50% requires the core flow rate also increase proportionally, which will give rise to the hydraulic lift-off, an important issue to be addressed. In this paper, taking the 17 × 17 solid fuel design as the reference, the hydraulic lift-off issue is investigated for proposed 12 × 12 and 13 × 13 annular fuel designs. Both the steady-state and start-up operating conditions are evaluated. It is found that the hydraulic lift-off indeed is an issue for annular fuel design which requires careful analysis. By comparison, the lift-off forces and hold-down forces required for the externally and internally cooled annular fuels (13 × 13 and 12 × 12 arrays) are several times larger than that of the referenced solid fuel (17 × 17 array). Therefore, the hold-down mechanism for annular fuel needs to be carefully designed

  16. Non-intrusive measurement of emission indices. A new approach to the evaluation of infrared spectra emitted by aircraft engine exhaust gases

    Energy Technology Data Exchange (ETDEWEB)

    Lindermeir, E.; Haschberger, P.; Tank, V. [Deutsche Forschungsanstalt fuer Luft- und Raumfahrt e.V. (DLR), Wessling (Germany). Inst. fuer Optoelektronik

    1997-12-31

    A non-intrusive method is used to determine the emission indices of a research aircraft`s engine in-flight. The principle is based on the Fourier Transform Infrared Spectrometer MIROR which was specifically designed and built for operation aboard aircrafts. This device measures the spectrum of the infrared radiation emitted by the hot exhaust gas under cruise conditions. From these spectra mixing ratios and emission indices can be derived. An extension to previously applied evaluation schemes is proposed: Whereas formerly the plume was assumed a homogeneous layer of gas, temperature and concentration profiles are now introduced to the evaluation procedure. (author) 5 refs.

  17. Control of a Buoyancy-Based Pilot Underwater Lifting Body

    Directory of Open Access Journals (Sweden)

    Finn Haugen

    2010-04-01

    Full Text Available This paper is about position control of a specific small-scale pilot underwater lifting body where the lifting force stems from buoyancy adjusted with an air pocket in the lifting body. A mathematical model is developed to get a basis for a simulator which is used for testing and for designing the control system, including tuning controller parameters. A number of different position controller solutions were tried both on a simulator and on the physical system. Successful control on both the simulator and the physical system was obtained with cascade control based on feedback from measured position and height of the air pocket in the lifting body. The primary and the secondary controllers of the cascade control system were tuned using Skogestad's model-based PID tuning rules. Feedforward from estimated load force was implemented in combination with the cascade control system, giving a substantial improvement of the position control system, both with varying position reference and varying disturbance (load mass.

  18. Analysis of Asymmetric Aircraft Aerodynamics Due to an Experimental Wing Glove

    Science.gov (United States)

    Hartshorn, Fletcher

    2011-01-01

    Aerodynamic analysis on a business jet with a wing glove attached to one wing is presented and discussed. If a wing glove is placed over a portion of one wing, there will be asymmetries in the aircraft as well as overall changes in the forces and moments acting on the aircraft. These changes, referred to as deltas, need to be determined and quantified to make sure the wing glove does not have a drastic effect on the aircraft flight characteristics. TRANAIR, a non-linear full potential solver was used to analyze a full aircraft, with and without a glove, at a variety of flight conditions and angles of attack and sideslip. Changes in the aircraft lift, drag and side force, along with roll, pitch and yawing moment are presented. Span lift and moment distributions are also presented for a more detailed look at the effects of the glove on the aircraft. Aerodynamic flow phenomena due to the addition of the glove and its fairing are discussed. Results show that the glove used here does not present a drastic change in forces and moments on the aircraft, but an added torsional moment around the quarter-chord of the wing may be a cause for some structural concerns.

  19. Lift of a rotating circular cylinder in unsteady flows

    DEFF Research Database (Denmark)

    Carstensen, Stefan; Mandviwalla, Xerxes; Vita, Luca;

    2012-01-01

    A cylinder rotating in steady current experiences a lift known as the Magnus effect. In the present study the effect of waves on the Magnus effect has been investigated. This situation is experienced with the novel floating offshore vertical axis wind turbine (VAWT) concept called the DEEPWIND co...

  20. Evaluation of failure of high lift diesel No. 2

    International Nuclear Information System (INIS)

    At 6:30 a.m., September 21, 1976, the No. 2 Emergency High Lift Pump Diesel Engine was remotely started from the N Reactor Control Room to provide water for flushing the N Reactor Emergency Cooling System piping. The engine is a General Motors Diesel Engine Model 16-278A, 2 cycle V type, 16 cylinder, developing 1600 horsepower at 750 revolutions per minute. During the flush, water was observed to be overflowing the engine's jacket cooling water expansion tank. The N Reactor Control Room was notified, and the engine was shut down after having run for approximately 15 minutes. Examination of the engine found the No. 5 cylinder liner had ruptured, causing air to be forced into the cooling system. When the engine was stopped, cooling water was admitted to the engine air box and crankcase. All 16 cylinder heads were removed and the cylinder liners were examined using liquid penetrant to detect cracks. A cracked cylinder liner was found in cylinder No. 6, and the cylinder head of cylinder No. 1 was also found to be cracked. An adherent scale and light pitting were observed on the heads of the pistons in cylinders No. 1, 5, and 6, but not in any other cylinders. All damaged parts were replaced, and the engine was reassembled, tested, and declared serviceable

  1. Upper lifting performance of healthy young adults in functional capacity evaluations : A comparison of two protocols

    NARCIS (Netherlands)

    Gerrits, EHJ; Reneman, MF

    2003-01-01

    The objectives of this study were to explore the concurrent validity of test results of upper lifting tasks of the Ergo-Kit FCE and the Isernhagen Work Systems (IWS) FCE. Seventy-one healthy young adults performed 5 upper lifting tests with at least 5 min of rest in between. The lifting tests includ

  2. Sandwich design of a lift plate for tail lift platforms for cargo trucks

    OpenAIRE

    Bergwall, Robert

    2015-01-01

    This master thesis examines a sandwich lift plate for cargo trucks in order to propose an option for existing lift platforms in aluminium or steel. The wish is to make it lighter but not less stiff or weak. Two different cores in Divinycell with different density; H130 and H250 is examined. Calculations are made with respect to deflection and max stress in both core and faces for the whole plates. But also more local calculations are performed to see how the faces and core behaved on local po...

  3. Aerodynamic Analysis of the Truss-Braced Wing Aircraft Using Vortex-Lattice Superposition Approach

    Science.gov (United States)

    Ting, Eric Bi-Wen; Reynolds, Kevin Wayne; Nguyen, Nhan T.; Totah, Joseph J.

    2014-01-01

    The SUGAR Truss-BracedWing (TBW) aircraft concept is a Boeing-developed N+3 aircraft configuration funded by NASA ARMD FixedWing Project. This future generation transport aircraft concept is designed to be aerodynamically efficient by employing a high aspect ratio wing design. The aspect ratio of the TBW is on the order of 14 which is significantly greater than those of current generation transport aircraft. This paper presents a recent aerodynamic analysis of the TBW aircraft using a conceptual vortex-lattice aerodynamic tool VORLAX and an aerodynamic superposition approach. Based on the underlying linear potential flow theory, the principle of aerodynamic superposition is leveraged to deal with the complex aerodynamic configuration of the TBW. By decomposing the full configuration of the TBW into individual aerodynamic lifting components, the total aerodynamic characteristics of the full configuration can be estimated from the contributions of the individual components. The aerodynamic superposition approach shows excellent agreement with CFD results computed by FUN3D, USM3D, and STAR-CCM+. XXXXX Demand for green aviation is expected to increase with the need for reduced environmental impact. Most large transports today operate within the best cruise L/D range of 18-20 using the conventional tube-and-wing design. This configuration has led to marginal improvements in aerodynamic efficiency over this past century, as aerodynamic improvements tend to be incremental. A big opportunity has been shown in recent years to significantly reduce structural weight or trim drag, hence improved energy efficiency, with the use of lightweight materials such as composites. The Boeing 787 transport is an example of a modern airframe design that employs lightweight structures. High aspect ratio wing design can provide another opportunity for further improvements in energy efficiency. Historically, the study of high aspect ratio wings has been intimately tied to the study of

  4. Effect of rear-surface buffer layer on performance of lift-off Cu(In,Ga)Se2 solar cells

    Science.gov (United States)

    Aoyagi, Kenta; Tamura, Akihiro; Takakura, Hideyuki; Minemoto, Takashi

    2014-01-01

    The effect of an Au and MoOx rear-surface buffer layer inserted between Cu(In,Ga)Se2 (CIGS) and ZnO:Al on solar cell performances was examined. The lift-off CIGS solar cell without a rear-surface buffer layer showed particular characteristics of two series-connected diodes in the reverse direction, and its short-circuit current density was almost zero. In contrast, the Au or MoOx rear-surface buffer layer improved these characteristics. Although the lift-off CIGS solar cell with the Au rear-surface buffer layer showed shunt characteristics and low efficiency, the efficiency of the lift-off CIGS solar cell with the MoOx rear-surface buffer layer was approximately 50% of that of substrate-type CIGS solar cells. Diode parameters of lift-off CIGS solar cells were determined by fitting analysis of current density-voltage curves using a proposed new equivalent circuit model for lift-off CIGS solar cells.

  5. Nondestructive testing of aging aircraft

    International Nuclear Information System (INIS)

    Aircraft fleet in the US military is getting old, averaging over 40 years. These old planes are planned to be used for additional 20-30 years. Some commercial fleets are getting older as well, though not on the same level. Many NDT methods are in practice and new ones being developed. Corrosion and fatigue are the two main sources of damage to aircraft structures and require cost-effective NDT methods to detect and characterize the damage. Current approaches to this difficult task reviewed.

  6. Ear-body lift and a novel thrust generating mechanism revealed by the complex wake of brown long-eared bats (Plecotus auritus).

    Science.gov (United States)

    Johansson, L Christoffer; Håkansson, Jonas; Jakobsen, Lasse; Hedenström, Anders

    2016-01-01

    Large ears enhance perception of echolocation and prey generated sounds in bats. However, external ears likely impair aerodynamic performance of bats compared to birds. But large ears may generate lift on their own, mitigating the negative effects. We studied flying brown long-eared bats, using high resolution, time resolved particle image velocimetry, to determine the aerodynamics of flying with large ears. We show that the ears and body generate lift at medium to cruising speeds (3-5 m/s), but at the cost of an interaction with the wing root vortices, likely reducing inner wing performance. We also propose that the bats use a novel wing pitch mechanism at the end of the upstroke generating thrust at low speeds, which should provide effective pitch and yaw control. In addition, the wing tip vortices show a distinct spiraling pattern. The tip vortex of the previous wingbeat remains into the next wingbeat and rotates together with a newly formed tip vortex. Several smaller vortices, related to changes in circulation around the wing also spiral the tip vortex. Our results thus show a new level of complexity in bat wakes and suggest large eared bats are less aerodynamically limited than previous wake studies have suggested. PMID:27118083

  7. A new method of inhibiting pollutant release from source water reservoir sediment by adding chemical stabilization agents combined with water-lifting aerator

    Institute of Scientific and Technical Information of China (English)

    Beibei Chai; Tinglin Huang; Weihuang Zhu; Fengying Yang

    2011-01-01

    Source water reservoirs easily become thermally and dynamically stratified.Internal pollution released from reservoir sediments is the main cause of water quality problems.To mitigate the internal pollution more effectively,a new method,which combined chemical stabilization with water lifting aerator (WLA) technology,was proposed and its efficiency in inhibiting pollutant release was studied by controlled sediment-water interface experiments.The results showed that this new method can inhibit pollutant release from sediment effectively.The values of mean efficiency (E) in different reactors 2#-5# (1# with no agent,2# 10 mg/L polymeric aluminum chloride (PAC) was added,3# 20 mg/L PAC was added,4# 30 mg/L PAC was added,5# 20 mg/L PAC and 0.2 mg/L palyacrylamide (PAM)were added) for PO43- were 35.0%,43.9%,50.4% and 63.6%,respectively.This showed that the higher the PAC concentration was,the better the inhibiting efficiency was,and PAM addition strengthened the inhibiting efficiency significantly.For Fe2+,the corresponding values of E for the reactors 2#-5# were 22.9%,47.2%,34.3% and 46.2%,respectively.The inhibiting effect of PAC and PAM on Mn release remained positive for a relatively short time,about 10 days,and was not so effective as for PO43- and Fe2+.The average efliciencies in inhibiting the release of UV254 were 35.3%,25.9%,35.5%,38.9% and 39.5% for reactors 2#-5#,respectively.The inhibiting mechanisms of the agents for different pollutants varied among the conditions and should be studied further.

  8. Fish's Muscles Distortion and Pectoral Fins Propulsion of Lift-Based Mode

    Science.gov (United States)

    Yang, S. B.; Han, X. Y.; Qiu, J.

    As a sort of MPF(median and/or paired fin propulsion), pectoral fins propulsion makes fish easier to maneuver than other propulsion, according to the well-established classification scheme proposed by Webb in 1984. Pectoral fins propulsion is classified into oscillatory propulsion, undulatory propulsion and compound propulsion. Pectoral fins oscillatory propulsion, is further ascribable to two modes: drag-based mode and lift-based mode. And fish exhibits strong cruise ability by using lift-based mode. Therefore to robot fish design using pectoral fins lift-based mode will bring a new revolution to resources exploration in blue sea. On the basis of the wave plate theory, a kinematic model of fish’s pectoral fins lift-based mode is established associated with the behaviors of cownose ray (Rhinoptera bonasus) in the present work. In view of the power of fish’s locomotion from muscle distortion, it would be helpful benefit to reveal the mechanism of fish’s locomotion variation dependent on muscles distortion. So this study puts forward the pattern of muscles distortion of pectoral fins according to the character of skeletons and muscles of cownose ray in morphology and simulates the kinematics of lift-based mode using nonlinear analysis software. In the symmetrical fluid field, the model is simulated left-right symmetrically or asymmetrically. The results qualitatively show how muscles distortion determines the performance of fish locomotion. Finally the efficient muscles distortion associated with the preliminary dynamics is induced.

  9. Design of a spanloader cargo aircraft

    Science.gov (United States)

    1989-01-01

    With a growing demand for fast international freight service, the slow-moving cargo ships currently in use will soon find a substantial portion of their clients looking elsewhere. One candidate for filling this expected gap in the freight market is a span-loading aircraft (or 'flying wing') capable of long-range operation with extremely large payloads. This report summarizes the design features of an aircraft capable of fulfilling a long-haul, high-capacity cargo mission. The spanloader seeks to gain advantage over conventional aircraft by eliminating the aircraft fuselage and thus reducing empty weight. The primary disadvantage of this configuration is that the cargo-containing wing tends to be thick, thus posing a challenge to the airfoil designer. It also suffers from stability and control problems not encountered by conventional aircraft. The result is an interesting, challenging exercise in unconventional design. The report that follows is a student written synopsis of an effort judged to be the best of eight designs developed during the year 1988-1989.

  10. Modeling aircraft emmisions by flight [paper in Portuguese

    Directory of Open Access Journals (Sweden)

    Gabriel de Sá Meira de Araújo

    2008-07-01

    Full Text Available The following paper intends to develop a translog model of the pollutants emission in Brazilian air transportation according to the flight stages characteristics (flight distance, aircraft type, etc. The model will focus on the segment of passenger transportation in civil aviation and the statistical model of fuel consumption will be based in a historical Brazilian database from 1997 to 2004. The assessment is performed in two stages. In the first, the translog consumption model is defined and estiamted; in the second, the pollutants emission coefficients are calculated through FAA’s (Federal Aviation Administration spreadsheets. The developed model can be easily processed by computers and through the creation of an user interface can produce a brand new pollutants emission calculator.

  11. Fundamentals of aircraft and rocket propulsion

    CERN Document Server

    El-Sayed, Ahmed F

    2016-01-01

    This book provides a comprehensive basics-to-advanced course in an aero-thermal science vital to the design of engines for either type of craft. The text classifies engines powering aircraft and single/multi-stage rockets, and derives performance parameters for both from basic aerodynamics and thermodynamics laws. Each type of engine is analyzed for optimum performance goals, and mission-appropriate engines selection is explained. Fundamentals of Aircraft and Rocket Propulsion provides information about and analyses of: thermodynamic cycles of shaft engines (piston, turboprop, turboshaft and propfan); jet engines (pulsejet, pulse detonation engine, ramjet, scramjet, turbojet and turbofan); chemical and non-chemical rocket engines; conceptual design of modular rocket engines (combustor, nozzle and turbopumps); and conceptual design of different modules of aero-engines in their design and off-design state. Aimed at graduate and final-year undergraduate students, this textbook provides a thorough grounding in th...

  12. Simulated Nano scale Peeling Process of Monolayer Graphene Sheet: Effect of Edge Structure and Lifting Position

    International Nuclear Information System (INIS)

    The nanoscale peeling of the graphene sheet on the graphite surface is numerically studied by molecular mechanics simulation. For center-lifting case, the successive partial peelings of the graphene around the lifting center appear as discrete jumps in the force curve, which induce the arched deformation of the graphene sheet. For edge-lifting case, marked atomic-scale friction of the graphene sheet during the nanoscale peeling process is found. During the surface contact, the graphene sheet takes the atomic-scale sliding motion. The period of the peeling force curve during the surface contact decreases to the lattice period of the graphite. During the line contact, the graphene sheet also takes the stick-slip sliding motion. These findings indicate the possibility of not only the direct observation of the atomic-scale friction of the graphene sheet at the tip/surface interface but also the identification of the lattice orientation and the edge structure of the graphene sheet.

  13. Status of Advanced Stitched Unitized Composite Aircraft Structures

    Science.gov (United States)

    Jegley, Dawn C.; Velicki, Alex

    2013-01-01

    NASA has created the Environmentally Responsible Aviation (ERA) Project to explore and document the feasibility, benefits and technical risk of advanced vehicle configurations and enabling technologies that will reduce the impact of aviation on the environment. A critical aspect of this pursuit is the development of a lighter, more robust airframe that will enable the introduction of unconventional aircraft configurations that have higher lift-to-drag ratios, reduced drag, and lower community noise levels. The primary structural concept being developed under the ERA project in the Airframe Technology element is the Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) concept. This paper describes how researchers at NASA and The Boeing Company are working together to develop fundamental PRSEUS technologies that could someday be implemented on a transport size aircraft with high aspect ratio wings or unconventional shapes such as a hybrid wing body airplane design.

  14. Aerodynamic Measurements of a Gulfstream Aircraft Model With and Without Noise Reduction Concepts

    Science.gov (United States)

    Neuhart, Dan H.; Hannon, Judith A.; Khorrami, Mehdi R.

    2014-01-01

    Steady and unsteady aerodynamic measurements of a high-fidelity, semi-span 18% scale Gulfstream aircraft model are presented. The aerodynamic data were collected concurrently with acoustic measurements as part of a larger aeroacoustic study targeting airframe noise associated with main landing gear/flap components, gear-flap interaction noise, and the viability of related noise mitigation technologies. The aeroacoustic tests were conducted in the NASA Langley Research Center 14- by 22-Foot Subsonic Wind Tunnel with the facility in the acoustically treated open-wall (jet) mode. Most of the measurements were obtained with the model in landing configuration with the flap deflected at 39º and the main landing gear on and off. Data were acquired at Mach numbers of 0.16, 0.20, and 0.24. Global forces (lift and drag) and extensive steady and unsteady surface pressure measurements were obtained. Comparison of the present results with those acquired during a previous test shows a significant reduction in the lift experienced by the model. The underlying cause was traced to the likely presence of a much thicker boundary layer on the tunnel floor, which was acoustically treated for the present test. The steady and unsteady pressure fields on the flap, particularly in the regions of predominant noise sources such as the inboard and outboard tips, remained unaffected. It is shown that the changes in lift and drag coefficients for model configurations fitted with gear/flap noise abatement technologies fall within the repeatability of the baseline configuration. Therefore, the noise abatement technologies evaluated in this experiment have no detrimental impact on the aerodynamic performance of the aircraft model.

  15. Effects of aircraft noise on human sleep.

    Science.gov (United States)

    Lukas, J. S.

    1972-01-01

    Under controlled conditions in two test rooms, studies were made of the response of sleeping subjects to the stimuli of simulated sonic booms and subsonic jet aircraft noise. Children were relatively nonresponsive to the stimuli. In general, the older the subject, the more likely is behavioral awakening. The response rates to the two types of stimuli were essentially the same. The stimulus intensity had little, if any, effect on frequency of arousal, although other degrees of response did increase.

  16. Estimation of nuclear power plant aircraft hazards

    International Nuclear Information System (INIS)

    The standard procedures for estimating aircraft risk to nuclear power plants provide a conservative estimate, which is adequate for most sites, which are not close to airports or heavily traveled air corridors. For those sites which are close to facilities handling large numbers of aircraft movements (airports or corridors), a more precise estimate of aircraft impact frequency can be obtained as a function of aircraft size. In many instances the very large commercial aircraft can be shown to have an acceptably small impact frequency, while the very small general aviation aircraft will not produce sufficiently serious impact to impair the safety-related functions. This paper examines the in between aircraft: primarily twin-engine, used for business, pleasure, and air taxi operations. For this group of aircraft the total impact frequency was found to be approximately once in one million years, the threshold above which further consideration of specific safety-related consequences would be required

  17. [Growth and polysaccharide formation in Sinorhizobium meliloti strains in an air-lift-type fermentor. Effect on nodulation velocity in alfalfa plants].

    Science.gov (United States)

    Lorda, G S; Castaño, R C; Pordomingo, A B; Pastor, M D; Balatti, A P

    2003-01-01

    In this paper the influence of the exopolysaccharides produced by Sinorhizobium meliloti strains on the nodulation rates in alfalfa plants has been considered. The experiments were performed in a rotary shaker and in an air-lift type fermentor. Different Sinorhizobium meliloti strains were used. Bacterial growth rates were determined by viable cell counts. Exopolysaccharide concentration was determined by precipitation with ethanol. It was observed that maximum cell concentration was in the order of 1 x 10(10) cell/ml and exopolysaccharide content was approximately 11 g/l. The experiments performed with alfalfa plants in a controlled environment chamber showed that, when inoculation was carried out with diluted suspensions (1/10), nodulation time was reduced from 10 to 4 days, while the strains retained their symbiotic properties. PMID:12920984

  18. Failure analysis of axle shaft of a fork lift

    OpenAIRE

    Souvik Das; Goutam Mukhopadhyay; Sandip Bhattacharyya

    2015-01-01

    An axle shaft of fork lift failed at operation within 296 h of service. The shaft transmits torque from discrepancy to wheel through planetary gear arrangement. A section of fractured axle shaft made of induction-hardened steel was analyzed to determine the root cause of the failure. Optical microscopies as well as field emission gun scanning electron microscopy (FEG-SEM) along with energy dispersive spectroscopy (EDS) were carried out to characterize the microstructure. Hardness profile thro...

  19. Special analysis of community annoyance with aircraft noise reported by residents in the vicinity of JFK Airport, 1972

    Science.gov (United States)

    Borsky, P. N.

    1975-01-01

    During the summer of 1972, about 1500 residents were interviewed twice in 11 communities near JFK airport. Detailed aircraft operations reports were also collected for this period, and an effort has been made to analyze recorded human response data in relation to a number of physical exposure parameters. A series of exposure indexes, based on an arithmetic integration of aircraft operations, were correlated with summated aircraft noise annoyance responses. None of these correlations were as good as the CNR index which assumes a logrithmetic integration of numbers of aircraft exposures and includes a day-night differential weighting of 10:1. There were substantial variations in average annoyance responses among communities with similar CNR exposures, substantiating previous findings that attitudinal and other personal variables also play an important role in determining annoyance differences.

  20. Advanced flow measurement and active flow control of aircraft with MEMS

    Institute of Scientific and Technical Information of China (English)

    Jiang Chengyu; Deng Jinjun; Ma Binghe; Yuan Weizheng

    2012-01-01

    Advanced flow measurement and active flow control need the development of new type devices and systems. Micro-electro-mechanical systems (MEMS) technologies become the important and feasible approach for micro transducers fabrication. This paper introduces research works of MEMS/NEMS Lab in flow measurement sensors and active flow control actuators. Micro sensors include the flexible thermal sensor array, capacitive shear stress sensor and high sensitivity pressure sensor. Micro actuators are the balloon actuator and synthetic jet actuator respectively. Through wind tunnel test, these micro transducers achieve the goals of shear stress and pressure distribution measurement, boundary layer separation control, lift enhancement, etc. And unmanned aerial vehicle (UAV) flight test verifies the ability of maneuver control of micro actuator. In the future work, micro sensor and actuator can be combined into a closed-loop control system to construct aerodynamic smart skin system for aircraft.

  1. Numerical Prediction of Induced Pressure and Lift of the Planing Surfaces

    Institute of Scientific and Technical Information of China (English)

    Hassan GHASSEMI; Ahmad Reza KOHANSAL; Mahmoud GHIASSI

    2009-01-01

    This paper discusses the numerical prediction of the induced pressure and lift of the planing surfaces in a steady motion based on the potential flow solver as well as the spray drag by use of the practical method.The numerical method for computation of the induced pressure and lift is potential-based boundary element method.Special technique is identified to present upwash geometry and to determine the spray drag.Numerical results of a planing flat plate and planing craft model 4666 are presented.It is shown that the method is robust and efficient and the results agree well with the experimental measurements with various Froude humors.

  2. Determining the number of fingers in the lifting Hele-Shaw problem

    Science.gov (United States)

    Miranda, Jose; Dias, Eduardo

    2013-11-01

    The lifting Hele-Shaw cell flow is a variation of the celebrated radial viscous fingering problem for which the upper cell plate is lifted uniformly at a specified rate. This procedure causes the formation of intricate interfacial patterns. Most theoretical studies determine the total number of emerging fingers by maximizing the linear growth rate, but this generates discrepancies between theory and experiments. In this work, we tackle the number of fingers selection problem in the lifting Hele-Shaw cell by employing the recently proposed maximum-amplitude criterion. Our linear stability analysis accounts for the action of capillary, viscous normal stresses, and wetting effects, as well as the cell confinement. The comparison of our results with very precise laboratory measurements for the total number of fingers shows a significantly improved agreement between theoretical predictions and experimental data. We thank CNPq (Brazilian Sponsor) for financial support.

  3. A comparison of two lifting assessment approaches in patients with chronic low back pain

    NARCIS (Netherlands)

    Soer, Remko; Poels, Bas J. J.; Geertzen, Jan H. B.; Reneman, Michiel F.

    2006-01-01

    The Progressive Isoinertial Lifting Evaluation (PILE) and the lifting test of the WorkWell Systems Functional Capacity Evaluation (WWS) are well known as lifting performance tests. The objective of this study was to study whether the PILE and the WWS can be used interchangeably in patients with Chro

  4. Analysis of a Lifting Fixture to Hold a Steel Mandrel Horizontally from one End Support

    International Nuclear Information System (INIS)

    A lifting fixture (drawing number 3823.113-MD-372382) that lifts large steel mandrels from one end through the mandrel's end support web is described. The mandrels are used as a mold to form carbon fiber cylinders. The mandrels are held from one end to allow the carbon cylinder to be pulled horizontally off the mandrel. Only mandrels as described in drawing numbers 3823.113-MD-358992 and 3823.1 13-MD-358994 are lifted by the fixture. The largest mandrel is 41 inches in diameter, 120 inches long, and weighs approximately 3,000 lbs. A detailed procedure for removing the carbon cylinder from the steel mandrel is given in the Appendix. The fixture is to be supported only using Fermilab Forklift 10207 or equivalent. The forklift has a nameplate capacity of 12,000 lbs 24 inches from the mast at an elevation of 130 inches from the floor. The forklift forks must be removed from the truck prior to using the fixture. The forklift is to be used to support the mandrels only during the lifting operation and is not to be used to transport the mandrels. Stresses at the lifting fixture are shear stresses on the support brackets due to the overall weight of the mandrel and moment loads due to the cantilever style suppOrt. The moment on the forklift due to the overhanging weight of the mandrel is calculated. Stresses in the mandrel due to the method of support are also described.

  5. Lifting devices with minimum effort for testing, maintenance and repair at the example of a lifting rig for core internals

    Energy Technology Data Exchange (ETDEWEB)

    Pache, Martin [Westinghouse Electric Germany GmbH (Germany); Wiesendanger, Robert [Kernkraftwerk Beznau, NOK (Switzerland)

    2008-07-01

    Beznau is a Westinghouse built nuclear power plant in the Aargau area Switzerland. It consists of two PWR units, each providing 365 MWe net capacity. The units were set into operation in 1969 and 1972, respectively, and hold an unlimited license for operation, provided they continue to fulfill current legal and security requirements. Beznau's previous lifting rigs for core internals required a high effort in testing and maintenance. Moreover, a damage to one of the rigs nearly resulted in the inoperability of the rig. However, no element of the load chain was affected, so there was no danger of a crash, but it could have caused an extended outage. Hence, it was decided to replace the lifting rigs with a state-of-the-art functional design that reflects modern requirements on maintenance and testing. Although the plant was built to ASME standards and codes, the new lifting rigs have been designed to German KTA code for lifting devices (KTA 3902 / 3903 for equipment with increased requirements, as per section 4.3 of KTA 3902). Given KTA's demands on periodic testing, one main requirement on the new design was to minimize the testing effort for the new rigs. (orig.)

  6. Lifting devices with minimum effort for testing, maintenance and repair at the example of a lifting rig for core internals

    International Nuclear Information System (INIS)

    Beznau is a Westinghouse built nuclear power plant in the Aargau area Switzerland. It consists of two PWR units, each providing 365 MWe net capacity. The units were set into operation in 1969 and 1972, respectively, and hold an unlimited license for operation, provided they continue to fulfill current legal and security requirements. Beznau's previous lifting rigs for core internals required a high effort in testing and maintenance. Moreover, a damage to one of the rigs nearly resulted in the inoperability of the rig. However, no element of the load chain was affected, so there was no danger of a crash, but it could have caused an extended outage. Hence, it was decided to replace the lifting rigs with a state-of-the-art functional design that reflects modern requirements on maintenance and testing. Although the plant was built to ASME standards and codes, the new lifting rigs have been designed to German KTA code for lifting devices (KTA 3902 / 3903 for equipment with increased requirements, as per section 4.3 of KTA 3902). Given KTA's demands on periodic testing, one main requirement on the new design was to minimize the testing effort for the new rigs. (orig.)

  7. LES-CMS simulations of a turbulent lifted hydrogen flame in vitiated co-flow

    Directory of Open Access Journals (Sweden)

    Stanković Ivana

    2013-01-01

    Full Text Available Results from a study of turbulent lifted jet flame with Conditional Moment Closure (CMC turbulent combustion model are reported. First, a qualitative description of the simulation results is given, by examining the instantaneous resolved species mass fraction fields. The structure of the lifted flame is also assessed by comparing the measured temperature and species mass fraction profiles and the simulation results. The model is able to capture the axial and radial profiles of mixture fraction, temperature and major species. The sensitivity of prediction to boundary conditions is also explored and the lift-off height is found to be very sensitive to the co-flow temperature. Finally, the stabilisation mechanisms, auto-ignition or premixed flame propagation, are addressed. No evidence of premixed flame propagation is found: the diffusion in physical space is negligible for all studied conditions.

  8. High-Lift Propeller System Configuration Selection for NASA's SCEPTOR Distributed Electric Propulsion Flight Demonstrator

    Science.gov (United States)

    Patterson, Michael D.; Derlaga, Joseph M.; Borer, Nicholas K.

    2016-01-01

    Although the primary function of propellers is typically to produce thrust, aircraft equipped with distributed electric propulsion (DEP) may utilize propellers whose main purpose is to act as a form of high-lift device. These \\high-lift propellers" can be placed upstream of wing such that, when the higher-velocity ow in the propellers' slipstreams interacts with the wing, the lift is increased. This technique is a main design feature of a new NASA advanced design project called Scalable Convergent Electric Propulsion Technology Operations Research (SCEPTOR). The goal of the SCEPTOR project is design, build, and y a DEP aircraft to demonstrate that such an aircraft can be much more ecient than conventional designs. This paper provides details into the high-lift propeller system con guration selection for the SCEPTOR ight demonstrator. The methods used in the high-lift propeller system conceptual design and the tradeo s considered in selecting the number of propellers are discussed.

  9. Effect of operating conditions and particle properties on performance of vertical air-lift

    OpenAIRE

    Chladek, Jana; Enstad, Gisle; Melaaen, Morten Christian

    2011-01-01

    The effect of the fluidization air flow rate and the transport air velocity on the solids mass flow rate and the pressure drop along the transport pipe was investigated in a vertical air-lift. The use of two different materials, glass (150 μm) and zirconium oxide (260 μm) particles (Geldart’s B class), enabled to estimate the effect of particle properties on the air-lift performance. Different levels of the solids mass flow rate were obtained by varying the fluidization air flow rate while ke...

  10. Effect of Groundboard Height on the Aerodynamic Characteristics of a Lifting Circular Cylinder Using Tangential Blowing from Surface Slots for Lift Generation

    Science.gov (United States)

    Lockwood, Vernard E.

    1961-01-01

    A wind-tunnel investigation has been made to determine the ground effect on the aerodynamic characteristics of a lifting circular cylinder using tangential blowing from surface slots to generate high lift coefficients. The tests were made on a semispan model having a length 4 times the cylinder diameter and an end plate of 2.5 diameters. The tests were made at low speeds at a Reynolds number of approximately 290,000, over a range of momentum coefficients from 0.14 to 4.60, and over a range of groundboard heights from 1.5 to 10 cylinder diameters. The investigation showed an earlier stall angle and a large loss of lift coefficient as the groundboard was brought close to the cylinder when large lift coefficients were being generated. For example, at a momentum coefficient of 4.60 the maximum lift coefficient was reduced from a value of 20.3 at a groundboard height of 10 cylinder diameters to a value of 8.7 at a groundboard height of 1.5 cylinder diameters. In contrast to this there was little effect on the lift characteristics of changes in groundboard height when lift coefficients of about 4.5 were being generated. At a height of 1.5 cylinder diameters the drag coefficients generally increased rapidly when the slot position angle for maximum lift was exceeded. Slightly below the slot position angle for maximum lift, the groundboard had a beneficial effect, that is, the drag for a given lift was less near the groundboard than away from the groundboard. The variation of maximum circulation lift coefficient (maximum lift coefficient minus momentum coefficient) obtained in this investigation is in general agreement with a theory developed for a jet-flap wing which assumes that the loss in circulation is the result of blockage of the main stream beneath the wing.

  11. The Role of Aircraft Motion in Airborne Gravity Data Quality

    Science.gov (United States)

    Childers, V. A.; Damiani, T.; Weil, C.; Preaux, S. A.

    2015-12-01

    Many factors contribute to the quality of airborne gravity data measured with LaCoste and Romberg-type sensors, such as the Micro-g LaCoste Turnkey Airborne Gravity System used by the National Geodetic Survey's GRAV-D (Gravity for the Redefinition of the American Vertical Datum) Project. For example, it is well documented that turbulence is a big factor in the overall noise level of the measurement. Turbulence is best controlled by avoidance; thus flights in the GRAV-D Project are only undertaken when the predicted wind speeds at flight level are ≤ 40 kts. Tail winds are known to be particularly problematic. The GRAV-D survey operates on a number of aircraft in a variety of wind conditions and geographic locations, and an obvious conclusion from our work to date is that the aircraft itself plays an enormous role in the quality of the airborne gravity measurement. We have identified a number of features of the various aircraft which can be determined to play a role: the autopilot, the size and speed of the aircraft, inherent motion characteristics of the airframe, tip tanks and other modifications to the airframe to reduce motion, to name the most important. This study evaluates the motion of a number of the GRAV-D aircraft and looks at the correlation between this motion and the noise characteristics of the gravity data. The GRAV-D Project spans 7 years and 42 surveys, so we have a significant body of data for this evaluation. Throughout the project, the sensor suite has included an inertial measurement unit (IMU), first the Applanix POSAv, and then later the Honeywell MicroIRS IMU as a part of a NovAtel SPAN GPS/IMU system. We compare the noise characteristics of the data with measures of aircraft motion (via pitch, roll, and yaw captured by the IMU) using a variety of statistical tools. It is expected that this comparison will support the conclusion that certain aircraft tend to work well with this type of gravity sensor while others tend to be problematic in

  12. 49 CFR 178.975 - Top lift test.

    Science.gov (United States)

    2010-10-01

    ...) Flexible Large Packaging design types must be filled to six times the maximum permissible gross mass, the... minutes. (2) Rigid plastic Large Packaging design types must be: (i) Lifted by each pair of diagonally... indicated in paragraph (c)(1) of this section, a flexible Large Packaging design type must be tested...

  13. The lifting factorization and construction of wavelet bi-frames with arbitrary generators and scaling.

    Science.gov (United States)

    Shi, Yan; Yang, Xiaoyuan

    2011-09-01

    In this paper, we present the lifting factorization and construction of wavelet bi-frames with arbitrary generators and scaling. We show that an arbitrary polyphase matrix of a wavelet bi-frame can be factorized into a series of lifting steps. Based on the proposed factorization, we present a general construction of bi-frames. Especially, we give an explicit formula to construct the bi-frames of two scaling and two generators with symmetry and one vanishing moment. This paper does not involve many theories of wavelet frames in mathematics, but focuses on the algebraic issues related to Laurent polynomials, which are efficient expressions in redundant filter banks associated with wavelet frames. As an extension of the classical two-channel filter bank, the redundant filter bank is more complicated but also more flexible. Furthermore, we present an algorithm to increase the number of vanishing moments to arbitrary order by lifting, which is iterated and is straightforward in implementation. PMID:21356617

  14. Lift truck safety review

    International Nuclear Information System (INIS)

    This report presents safety information about powered industrial trucks. The basic lift truck, the counterbalanced sit down rider truck, is the primary focus of the report. Lift truck engineering is briefly described, then a hazard analysis is performed on the lift truck. Case histories and accident statistics are also given. Rules and regulations about lift trucks, such as the US Occupational Safety an Health Administration laws and the Underwriter's Laboratories standards, are discussed. Safety issues with lift trucks are reviewed, and lift truck safety and reliability are discussed. Some quantitative reliability values are given

  15. Lift truck safety review

    Energy Technology Data Exchange (ETDEWEB)

    Cadwallader, L.C.

    1997-03-01

    This report presents safety information about powered industrial trucks. The basic lift truck, the counterbalanced sit down rider truck, is the primary focus of the report. Lift truck engineering is briefly described, then a hazard analysis is performed on the lift truck. Case histories and accident statistics are also given. Rules and regulations about lift trucks, such as the US Occupational Safety an Health Administration laws and the Underwriter`s Laboratories standards, are discussed. Safety issues with lift trucks are reviewed, and lift truck safety and reliability are discussed. Some quantitative reliability values are given.

  16. Next Generation Civil Transport Aircraft Design Considerations for Improving Vehicle and System-Level Efficiency

    Science.gov (United States)

    Acosta, Diana M.; Guynn, Mark D.; Wahls, Richard A.; DelRosario, Ruben,

    2013-01-01

    The future of aviation will benefit from research in aircraft design and air transportation management aimed at improving efficiency and reducing environmental impacts. This paper presents civil transport aircraft design trends and opportunities for improving vehicle and system-level efficiency. Aircraft design concepts and the emerging technologies critical to reducing thrust specific fuel consumption, reducing weight, and increasing lift to drag ratio currently being developed by NASA are discussed. Advancements in the air transportation system aimed towards system-level efficiency are discussed as well. Finally, the paper describes the relationship between the air transportation system, aircraft, and efficiency. This relationship is characterized by operational constraints imposed by the air transportation system that influence aircraft design, and operational capabilities inherent to an aircraft design that impact the air transportation system.

  17. Prediction of UHPFRC panels thickness subjected to aircraft engine impact

    Directory of Open Access Journals (Sweden)

    Duc-Kien Thai

    2016-06-01

    Full Text Available In the practical design of nuclear building structures subjected to an aircraft crash, the structures are required to prevent scabbing and perforation. NEI 07-13 provided the formulas to predict the minimum reinforced concrete (RC wall thickness to prevent the local damage caused by aircraft engine impact. However, these formulas may not be suitable for predicting the thickness of the ultra-high performance fiber reinforced concrete (UHPFRC wall. In this study, the local damage of a UHPFRC wall caused by the impact of aircraft engine missile is investigated using a finite element program LS-DYNA. The structural components of the UHPFRC panel, aircraft engine model, and their contacts are fully modeled. The analysis results are verified with the test results. A parametric study with varying panel thickness, fiber type and content, and impact velocity is performed to investigate the local damage of the UHPFRC panel. Based on a comparison with the given formulas, the modified equations of Chang and Degen are proposed to predict the minimum wall thickness to prevent scabbing and perforation in the case in which the UHPFRC structure is used.

  18.  Heavy Lift Methods in Decommissioning of Installations

    OpenAIRE

    Breidablikk, Line Småge

    2010-01-01

     In this report decommissioning of offshore petroleum platforms have been investigated. It treats decommissioning in general, the process of a typical project. A variety of suitable lifting vessels have been presented, and some concepts of removal have been evaluated.Decommissioning is important to go through with because of the environment and the use of the area after the petroleum activities ceases. Other ocean users benefit from the decommissioning because the area can be utilized when it...

  19. Models of Lift and Drag Coefficients of Stalled and Unstalled Airfoils in Wind Turbines and Wind Tunnels

    Science.gov (United States)

    Spera, David A.

    2008-01-01

    Equations are developed with which to calculate lift and drag coefficients along the spans of torsionally-stiff rotating airfoils of the type used in wind turbine rotors and wind tunnel fans, at angles of attack in both the unstalled and stalled aerodynamic regimes. Explicit adjustments are made for the effects of aspect ratio (length to chord width) and airfoil thickness ratio. Calculated lift and drag parameters are compared to measured parameters for 55 airfoil data sets including 585 test points. Mean deviation was found to be -0.4 percent and standard deviation was 4.8 percent. When the proposed equations were applied to the calculation of power from a stall-controlled wind turbine tested in a NASA wind tunnel, mean deviation from 54 data points was -1.3 percent and standard deviation was 4.0 percent. Pressure-rise calculations for a large wind tunnel fan deviated by 2.7 percent (mean) and 4.4 percent (standard). The assumption that a single set of lift and drag coefficient equations can represent the stalled aerodynamic behavior of a wide variety of airfoils was found to be satisfactory.

  20. Application of air-lifting pump in standard spray-sieve-plates pulsed extraction column

    International Nuclear Information System (INIS)

    The present research aims to determine the application of air-lifting pump in 100 mm diameter standard spray-sieve-plates pulsed extraction column for 30%TRPO/ kerosene solution-1 mol/L HNO3 solution. The liquid flow rate of air-lifting pump, designed for aqueous phase feeding, organic phase feeding and aqueous phase discharging, increases linearly with air flow rate within experimental range, and the submerged ratio of the air-lifting pump for aqueous phase discharging is linear with the holdup of the pulsed extraction column. By combining above results with the online measurement of air-purge method, the steady state of pulsed extraction column is easily controlled. (authors)

  1. The Concept and Security Analysis of Wireless Sensor Network for Gas Lift in Oilwells

    Directory of Open Access Journals (Sweden)

    Bielecki Bartlomiej

    2014-06-01

    Full Text Available Pipelines, wellbores and ground installations are permanently controlled by sensors spread across the crucial points in the whole area. One of the most popular techniques to support proper oil drive in a wellbore is a Gas Lift. In this paper we present the concept of using wireless sensor network (WSN in the oil and gas industry installations. Assuming that Gas Lift Valves (GLVs in a wellbore annulus are sensor controlled, the proper amount of injected gas should be provided. In a ground installation, the optimized amount of loaded gas is a key factor in the effcient oil production. This paper considers the basic foundations and security requirements of WSN dedicated to Gas Lift Installations. Possible attack scenarios and their influence on the production results are shown as well.

  2. Experimental Study of Air-Lift Pumps Characteristics

    Directory of Open Access Journals (Sweden)

    Naji F. Al-Saqer

    2014-03-01

    Full Text Available The mean aim of this work is to study the Air-lift pumps characteristics according to design parameters such as the percentage of the distance between throat section and nozzle and the driving air pressure, suction head and also study the effect of each parameter on the air lift pump characteristics in order to have a better performance of such pump under various conditions. A certain geometry for air-lift pump designed and manufactured. The experiments show that there must be careful in increasing the suction head, and a balance must be considered between the suction head and the driving air volumetric flow rate. While the effect of increasing air pressure will stop at certain maximum of the ratio of the volumetric flow rate of water and air that is any increase in air pressure will meet no change ratio of the volumetric flow rate of water and air, While Increasing S/Dth will leads to decrease in the percentage of ratio of the volumetric flow rate of water and air because the optimum S/Dth so that at this value we will have the best performance and any other values for S/Dth the percentage of ratio of the volumetric flow rate of water and air will decreases , but this effect is not so clear and it could be neglected. The pump performance is not so sensitive with the change of S/Dth after a certain value, this information will help in the use of the air-lift pump in several applications using the predetermined operating conditions.

  3. THE CLINICAL APPLICATION OF ENDOSCOPE IN FRONTO-TEMPORAL LIFTING

    Institute of Scientific and Technical Information of China (English)

    2001-01-01

    Objective To introduce and discuss the usage and effects of endoscopic technique in the frontal-temporal lifting. Methods 15 endoscopic forehead-lift cases were treated from 1996 to 1999. The frontal and deep temporal fascia dissection were performed to produce a visualization pocket. The resection of the procerus and corrugator muscles were performed under direct vision to correct the imbalance of the muscles. The periosteum was also released along the supraobital rim. Results The results were satisfactory. The pro- cedure was usually performed to rejuvenate the ptosis of the eyebrow, to eliminate the temporal and glabellar wrinkles as well. Conclusion Small incision, less bleeding, mild numbness and less alopecia are the advan- tages of endoscopic operation.

  4. Validated Design and Analysis Tool for Small Vertical-Lift Unmanned Air Vehicle Noise Prediction Project

    Data.gov (United States)

    National Aeronautics and Space Administration — A procedure and supporting computer code for the prediction of noise that radiates from small, vertical lift UAV aircraft is proposed. The resulting building block...

  5. The European Research Infrastructure IAGOS - From dedicated field studies to routine observations of the atmosphere by instrumented passenger aircraft

    Science.gov (United States)

    Petzold, Andreas; Volz-Thomas, Andreas; Gerbig, Christoph; Thouret, Valerie; Cammas, Jean-Pierre; Brenninkmeijer, Carl A. M.; Iagos Team

    2013-04-01

    The global distribution of trace species is controlled by a complex interplay between natural and anthropogenic sources and sinks, atmospheric short- to long-range transport, and in future by diverse, largely not yet quantified feedback mechanisms such as enhanced evaporation of water vapour in a warming climate or possibly the release of methane from melting marine clathrates. Improving global trace gas budgets and reducing the uncertainty of climate predictions crucially requires representative data from routine long-term observations as independent constraint for the evaluation and improvement of model parameterizations. IAGOS (In-service Aircraft for a Global Observing System; www.iagos.org) is a new European Research Infrastructure which operates a unique global observing system by deploying autonomous instruments aboard a fleet of passenger aircraft. IAGOS consists of two complementary building blocks: IAGOS-CORE deploys newly developed high-tech instrumentation for regular in-situ measurements of atmospheric chemical species (O3, CO, CO2, NOx, NOy, H2O, CH4), aerosols and cloud particles. Involved airlines ensure global operation of the network. In IAGOS-CARIBIC a cargo container is operated as a flying laboratory aboard one passenger aircraft. IAGOS aims at the provision of long-term, frequent, regular, accurate, and spatially resolved in-situ observations of the atmospheric chemical composition in the UTLS and the extra tropical troposphere and on vertical profiles of greenhouse gases, reactive trace gases and aerosols throughout the troposphere. It builds on almost 20 years of scientific and technological expertise gained in the research projects MOZAIC (Measurement of Ozone and Water Vapour on Airbus In-service Aircraft) and CARIBIC (Civil Aircraft for the Regular Investigation of the Atmosphere Based on an Instrument Container). The European consortium includes research centres, universities, national weather services, airline operators and aviation

  6. Conceptual study of an advanced VTOL transport aircraft; Kosoku VTOL ki no gainen kento

    Energy Technology Data Exchange (ETDEWEB)

    Saito, Y.; Endo, M.; Matsuda, Y.; Sugiyama, N.; Watanabe, M.; Sugahara, N.; Yamamoto, K. [National Aerospace Laboratory, Tokyo (Japan)

    1996-05-01

    The concept of the advanced 100-passenger class VTOL aircraft equipped with new lift fan engines was clarified as domestic passenger aircraft for the 21st century. Under the assumption of a total weight of 40 tons, a seat fuselage diameter of 3.3m as small as possible and a short seat pitch, the airframe shape satisfying a target performance was obtained without any problems about aerodynamic stability, operability and control capability, and noise lower than that of small helicopters was also estimated. In the case of 10 tons in airframe payload and 8 tons in fuel, even if light-weight composite materials were used for most of parts including fuselage structure, a total weight summed to 42.3 tons exceeding a target by 2.3 tons. As this VTOL aircraft was limited to domestic flight use only, the total weight could be reduced without any change in airframe shape and number of passengers by reducing the payload (baggage weight can be probably reduced by 2 tons/100 passengers in the future domestic flight) and fuel (cruising range around 2500km can be secured even if fuel is reduced by 0.3 tons). In conclusion, this concept was thus technologically reasonable. 6 refs., 15 figs., 6 tabs.

  7. [Performance of internal-loop air-lift nitrifying bioreactor].

    Science.gov (United States)

    Lin, Feng-Mei; Zheng, Ping; Zhao, Yang-Yang; Hu, Bao-Lan; Chen, Jian-Song

    2002-07-01

    The performance of internal-loop air-lift nitrifying bioreactor was good with strong tolerance to influent ammonia concentration (78.49 mmol/L), high volume converting rate (163.18 mmol/L.d) and obvious working stability (ammonia removal > 94.42%). During operation of internal-loop air-lift bioreactor, the nitrifying activated sludge was granulated. The nitrifying granular activated sludge began to appear on day 45. Its average diameter was 0.83 mm, settling velocity was 55.53 m/h and specific ammonia removal rate was 0.95 mmol (NH4(+)-N)/g (VS).d. The nitrifying granular activated sludge had the activity for anaerobic ammonia oxidation with ammonia oxidation rate of 0.23 mmol (NH4(+)-N)/g(VS).d and nitrite reduction rate of 0.24 mmol (NO2(-)-N)/g(VS).d. PMID:12385250

  8. Extent of inspections for lifting appliances in nuclear installations

    International Nuclear Information System (INIS)

    During in-service inspections of lifting appliances, the test specifications, principles, and guidelines included in the technical rules are to be applied for the inspection of elevators and cranes. In annex 1 these specifications, principles, and guidelines are compiled. For lifting appliances in nuclear installations, which according to KTA rule 3902, edition 11/75, have to meet additional and more rigorous requirements, no. 10.3 is relevant. In nos. 2 and 3 of this direction, those in-service inspections are listed in detail which go beyond the general requirements according to no. 10.3.3 rule KTA 3902, edition 11/75. The extent of the inspections has to be set up between licensee and inspecting expert in a program for in-service inspections. (orig./HP)

  9. Advanced aircraft analysis of an F-4 Phantom on a reinforced concrete building

    International Nuclear Information System (INIS)

    Highlights: • Aircraft impact analyses are performed using the missile-target interaction method. • Three types of FE models of a F4-Phantom aircraft considering the fuel mass effect are considered with erosion effect. • The aircraft impact models are verified through the comparative studies with experimental data. • The parametric studies on the fictitious nuclear concrete containment wall are investigated. • The SPH or Hybrid models show severe damage to the deformable constrained concrete wall than does Lagrangian based model. - Abstract: The nonlinear dynamic fracture and collapse characteristics of an F-4 Phantom aircraft under an extreme load caused by the impact of an F-4 Phantom are investigated. Three types of FE models considering the fuel mass effect are developed to investigate the superiority of the developed model. A rigid wall impact test is conducted to determine the material properties and the eroding failure criteria. The impact forces exerted by the aircraft against mounted thick concrete walls are then verified by comparing the results here with earlier experimental data obtained from an actual-scale F-4 Phantom aircraft impact test conducted by Sandia National Laboratory. Validation of the methodology is further investigated by extending the comparative studies to a constrained thin concrete wall similar to the type used in nuclear power plant containment buildings. The experimental and simulation results are also analyzed and discussed

  10. Dedicated Solutions for Structural Health Monitoring of Aircraft Components

    OpenAIRE

    Pitropakis, Ioannis

    2015-01-01

    Aircraft structures, like any other mechanical structure, are subjected to various external factors that influence their lifetime. Mechanicalnbsp;and the environment are only some of the factors that can degrade the structure of aircraft components. Monitoring of these degradations by regular inspections or automated data recording is vital for the structural health of the critical components of an aircraft. This research proposes a number of dedicated solutions for structural health monitori...

  11. Purpose Tailored Design of Gas-Lift Reactor

    Czech Academy of Sciences Publication Activity Database

    Gogová, Zuzana; Hanika, Jiří

    Bratislava: Slovak Society of Chemical Engineering, 2008 - (Markoš, J.), s. 271 ISBN 978-80-227-2903-1. [35th International Conference of Slovak Society of Chemical Engineering. Tatranské Matliare (SK), 26.05.2008-30.05.2008] R&D Projects: GA ČR(CZ) GD203/08/H032 Institutional research plan: CEZ:AV0Z40720504 Keywords : gas- lift reactor * model * glucose Subject RIV: CI - Industrial Chemistry, Chemical Engineering

  12. MATHEMATICAL SIMULATION OF HOVERCRAFT LIFT SYSTEM AERODYNAMICS

    OpenAIRE

    Kalyasov, P.; Lyubimov, A.

    2008-01-01

    A procedure to calculate numerically the pressure-discharge characteristic of the hovercraft blowing system has been presented. The procedure has been realized on a multiprocessor cluster using the ANSYS CFX fluid dynamics software system. By the calculation results, some recommendations have been given to change the geometry of the air duct and fan wheel blades.

  13. Measurement of ozone and water vapor by Airbus in-service aircraft: The MOZAIC airborne program, An overview

    Science.gov (United States)

    Marenco, Alain; Thouret, ValéRie; NéDéLec, Philippe; Smit, Herman; Helten, Manfred; Kley, Dieter; Karcher, Fernand; Simon, Pascal; Law, Kathy; Pyle, John; Poschmann, Georg; von Wrede, Rainer; Hume, Chris; Cook, Tim

    1998-10-01

    Tentative estimates, using three-dimensional chemistry and transport models, have suggested small ozone increases in the upper troposphere resulting from current aircraft emissions, but have also concluded to significant deficiencies in today's models and to the need to improve them through comparison with extended data sets. The Measurement of Ozone and Water Vapor by Airbus In-Service Aircraft (MOZAIC) program was initiated in 1993 by European scientists, aircraft manufacturers, and airlines to collect experimental data. Its goal is to help understand the atmosphere and how it is changing under the influence of human activity, with particular interest in the effects of aircraft. MOZAIC consists of automatic and regular measurements of ozone and water vapor by five long range passenger airliners flying all over the world. The aim is not to detect direct effects of aircraft emissions on the ozone budget inside the air traffic corridors but to build a large database of measurements to allow studies of chemical and physical processes in the atmosphere, and hence to validate global chemistry transport models. MOZAIC data provide, in particular, detailed ozone and water vapor climatologies at 9-12 km where subsonic aircraft emit most of their exhaust and which is a very critical domain (e.g., radiatively and stratosphere/troposphere exchanges) still imperfectly described in existing models. This will be valuable to improve knowledge about the processes occuring in the upper troposphere and the lowermost stratosphere, and the model treatment of near tropopause chemistry and transport. During MOZAIC I (January 1993-September 1996), fully automatic devices were developed, installed aboard five commercial Airbus A340s, and flown in normal airline service. A second phase, MOZAIC II, started in October 1996 with the aim of continuing the O3 and H2O measurements and doing a feasibility study of new airborne devices (CO, NOy). Between September 1994 and December 1997, 7500

  14. Airborne aldehydes in cabin-air of commercial aircraft: Measurement by HPLC with UV absorbance detection of 2,4-dinitrophenylhydrazones.

    Science.gov (United States)

    Rosenberger, Wolfgang; Beckmann, Bibiana; Wrbitzky, Renate

    2016-04-15

    This paper presents the strategy and results of in-flight measurements of airborne aldehydes during normal operation and reported "smell events" on commercial aircraft. The aldehyde-measurement is a part of a large-scale study on cabin-air quality. The aims of this study were to describe cabin-air quality in general and to detect chemical abnormalities during the so-called "smell-events". Adsorption and derivatization of airborne aldehydes on 2,4-dinitrophenylhydrazine coated silica gel (DNPH-cartridge) was applied using tailor-made sampling kits. Samples were collected with battery supplied personal air sampling pumps during different flight phases. Furthermore, the influence of ozone was investigated by simultaneous sampling with and without ozone absorption unit (ozone converter) assembled to the DNPH-cartridges and found to be negligible. The method was validated for 14 aldehydes and found to be precise (RSD, 5.5-10.6%) and accurate (recovery, 98-103 %), with LOD levels being 0.3-0.6 μg/m(3). According to occupational exposure limits (OEL) or indoor air guidelines no unusual or noticeable aldehyde pollution was observed. In total, 353 aldehyde samples were taken from two types of aircraft. Formaldehyde (overall average 5.7 μg/m(3), overall median 4.9 μg/m(3), range 0.4-44 μg/m(3)), acetaldehyde (overall average 6.5 μg/m(3), overall median 4.6, range 0.3-90 μg/m(3)) and mostly very low concentrations of other aldehydes were measured on 108 flights. Simultaneous adsorption and derivatization of airborne aldehydes on DNPH-cartridges to the Schiff bases and their HPLC analysis with UV absorbance detection is a useful method to measure aldehydes in cabin-air of commercial aircraft. PMID:26376451

  15. Failure analysis of axle shaft of a fork lift

    Directory of Open Access Journals (Sweden)

    Souvik Das

    2015-04-01

    Full Text Available An axle shaft of fork lift failed at operation within 296 h of service. The shaft transmits torque from discrepancy to wheel through planetary gear arrangement. A section of fractured axle shaft made of induction-hardened steel was analyzed to determine the root cause of the failure. Optical microscopies as well as field emission gun scanning electron microscopy (FEG-SEM along with energy dispersive spectroscopy (EDS were carried out to characterize the microstructure. Hardness profile throughout the cross-section was evaluated by micro-hardness measurements. Chemical analysis indicated that the shaft was made of 42CrMo4 steel grade as per specification. Microstructural analysis and micro-hardness profile revealed that the shaft was improperly heat treated resulting in a brittle case, where crack was found to initiate from the case in a brittle mode in contrast to ductile mode within the core. This behaviour was related to differences in microstructure, which was observed to be martensitic within the case with a micro-hardness equivalent to 735 HV, and a mixture of non-homogeneous structure of pearlite and ferrite within the core with a hardness of 210 HV. The analysis suggests that the fracture initiated from the martensitic case as brittle mode due to improper heat treatment process (high hardness. Moreover the inclusions along the hot working direction i.e. in the longitudinal axis made the component more susceptible to failure.

  16. Flying and handling qualities of a fly-by-wire blended-wing-body civil transport aircraft

    OpenAIRE

    de Castro, Helena V.

    2003-01-01

    The blended-wing-body (BWB) configuration appears as a promising contender for the next generation of large transport aircraft. The idea of blending the wing with the fuselage and eliminating the tail is not new, it has long been known that tailless aircraft can suffer from stability and control problems that must be addressed early in the design. This thesis is concerned with identifying and then evaluating the flight dynamics, stability, flight controls and handling qualities of a generic B...

  17. Lift-Off Performance of Ferrite Enhanced Generation Emats

    Science.gov (United States)

    Fan, Yichao; Dixon, Steve; Jian, Xiaoming

    2008-02-01

    Electromagnetic Acoustic Transducers (EMATs) are non-contact ultrasonic transducers capable of generating wide-band ultrasonic waves on electrically conductive and magnetostrictive samples. The lack of physical contact makes EMATs particularly suitable for online inspection applications, or situations where samples may be moving or hot. The generation efficiency of a given EMAT on a given sample is dependent on the "lift-off", which is the distance between the EMAT and the sample surface. Efficiency dramatically reducing with increased lift-off. This requirement to be in close proximity to the sample imposes a practical limit of operation and changes in lift-off due to phenomena such as sample vibration can have practical implications in certain NDE applications. This paper describes some results from experiments comparing the performance of a ferrite enhanced EMAT design to one of our `standard' EMATs, where we have substituted the permanent magnet from the standard EMAT with a suitable ferrite material. When the EMAT coil is placed in proximity to the ferrite, but not wrapped around the ferrite, the increase in the generated eddy current amplitude is significant, whilst the inductance or bandwidth of the EMAT is not significantly affected. Using a ferrite material eliminated eddy current losses in the permanent magnet, and also enhances the self-field generation mechanism, which generates a repulsive normal force on the sample surface. Direct experimental results show the ferrite enhanced EMAT generation efficiency can be higher at large stand-offs and is also less sensitive to lift-off variations. Although the example we describe here only applies to EMAT generation, there are situations where ferrite could be used to enhance detector efficiencies.

  18. Practical Ranges of Loudness Levels of Various Types of Environmental Noise, Including Traffic Noise, Aircraft Noise, and Industrial Noise

    OpenAIRE

    Sabine A. Janssen; Salomons, Erik M.

    2011-01-01

    In environmental noise control one commonly employs the A-weighted sound level as an approximate measure of the effect of noise on people. A measure that is more closely related to direct human perception of noise is the loudness level. At constant A-weighted sound level, the loudness level of a noise signal varies considerably with the shape of the frequency spectrum of the noise signal. In particular the bandwidth of the spectrum has a large effect on the loudness level, due to the effect o...

  19. Hidden symmetries of Eisenhart-Duval lift metrics and the Dirac equation with flux

    OpenAIRE

    Cariglia, Marco

    2012-01-01

    The Eisenhart-Duval lift allows embedding non-relativistic theories into a Lorentzian geometrical setting. In this paper we study the lift from the point of view of the Dirac equation and its hidden symmetries. We show that dimensional reduction of the Dirac equation for the Eisenhart-Duval metric in general gives rise to the non-relativistic Levy-Leblond equation in lower dimension. We study in detail in which specific cases the lower dimensional limit is given by the Dirac equation, with sc...

  20. Computational Fluid Dynamics (CFD) Simulations of a Humvee Airdropped from Aircraft

    Science.gov (United States)

    Reyes, Phillip M.

    Military airdrop is a means of transporting and delivering cargo to inaccessible locales faster and more efficiently. The Humvee, an all-terrain truck, is one such payload that the U.S. Army drops routinely. Here, interesting physics occurs both structurally and aerodynamically. From a fluid dynamics and trajectory standpoint, determining the aerodynamic forces and moments acting on the parachute and payload is crucial particularly for trajectory prediction. This study primarily used Computational Fluid Dynamics (CFD) to simulate the aerodynamics of an airdrop Humvee model in two regimes of fall, namely, right after clearing the aircraft ramp, and during descent under parachute. This study was performed at a Reynolds number of 3.07x10. 6 and at an airspeedof 9.144m/s (30ft/s). The first humvee part of the study analyzed the aerodynamic coefficients drag, lift, and pitching moment over a 360 degree range of pitch angles for the Humvee configured for extraction. The second set of humvee simulations focused on the aerodynamic coefficients at pitch angles of -40 degrees to +40 degrees with the platform and vehicle configured for descent under parachute. The Humvee after ramp tip-off has a parachute pack on its hood, but lacks one during the descent phase. The numerical data was compared with the results of geometries from previous studies. These geometries include: the flat plate, Type-V LVADS and 10K-JPADS containers, and a cargo-carrying platform outfitted with a bumper. Our results clearly show the effects of the many angular features that characterize the shape of a Humvee in comparison to those of a simple cuboid, particularly with regards to the loss of lift in a sub-range of pitch angle (-45 degrees to -180 degrees). First, the aerodynamic coefficients were calculated over one full-revolution of the humvee (-180 degrees to +180 degrees static pitch angles with respect to the humvee's platform) best matched in lift, drag, and moment those of the type V LVADS

  1. Design of Gas-Lift Reactor for Catalytic Oxidation

    Czech Academy of Sciences Publication Activity Database

    Gogová, Zuzana; Hanika, Jiří

    Praha: Process Engineering Publisher, 2008, s. 248. ISBN 978-80-02-02048-6. [18th International Congress of Chemical and Process Engineering CHISA 2008. Praha (CZ), 24.08.2008-28.08.2008] R&D Projects: GA ČR GD203/08/H032 Institutional research plan: CEZ:AV0Z40720504 Keywords : gas- lift reactor * model * glucose Subject RIV: CI - Industrial Chemistry, Chemical Engineering

  2. Role of convective transport on tropospheric ozone chemistry revealed by aircraft observations during the wet season of the AMMA campaign

    Directory of Open Access Journals (Sweden)

    G. Ancellet

    2008-08-01

    Full Text Available During the wet season of the African Monsoon Multidisciplinary Analyses (AMMA campaign, airborne measurements of several chemical species were made onboard the French Falcon-20 (FF20 aircraft. The scientific flights were planned in order to document, on one hand the regional distribution of trace gas species related to the oxidizing capacity of the troposphere, and on the other hand their spatial variability in the outflow of mesoscale convective systems (MCSs. The main objectives of this paper are the analysis of the main transport processes responsible for the observed variability, and the discussion of differences and similarities related to the convective transport by 4 different MCSs. This work is needed before using this data set for future studies of the convective transport of chemical species or for modeling work in the frame of the AMMA project. Regarding the regional distribution, five air masses types have been identified using the Lagrangian particle dispersion model FLEXPART, and by considering relationship between the measured trace gas concentrations (O3, CO, NOx, H2O, and hydroperoxides. This paper specifically discusses the advantage of hydroperoxide measurements in order to document the impact of recent or aged convection. The highest values of O3 are found to be related to transport from the subtropical tropopause region into the mid-troposphere at latitudes as low as 10° N. The lowest ozone values have been always explained by recent uplifting from the monsoon layer where O3 is photochemically destroyed. Regarding the analysis of the MCS outflow, the CO and H2O2 enhancements are related to the age and the southernmost position of the MCS. The analysis of the long range transport of the air masses where convection occurred, shows a connection with the Persian Gulf emissions for the largest CO concentrations in MCS outflow. However for our

  3. Large-scale static investigation of circulation-control-wing concepts applied to upper surface-blowing aircraft

    Science.gov (United States)

    Shovlin, M. D.; Englar, R. J.; Eppel, J. C.; Nichols, J. H., Jr.

    1987-01-01

    The use of a circulation control to deflect turbofan engine thrust beyond 90 deg. has been proven in full-scale static ground tests of the circulation-control-wing/upper-surface-blowing (CCW/USB) concept. This powered high-lift system employs a circular, blown trailing edge to replace the USB mechanical flaps to entrain engine-exhaust flow, and to obtain both a vertical-thrust component and an augmented circulation lift for short takeoff and landing (STOL) applications. Previous tests (Phase 1), done in 1982, of a basic configuration installed on the Quiet Short Haul Research Aircraft confirmed these CCW/USB systems capabilities. A second phase (Phase 2) of full-scale, static, thrust-deflection investigations has reconfirmed the ability to deflect engine thrust from 40 to 102 deg., depending on thrust level. Five new configurations were evaluated and performance improvements noted for those configurations with larger blown span, fences or favorable engine interactions, smaller slot height, and larger radii with less than 180 deg. of CCW surface arc. In general, a 90 deg. circular arc with a smaller slot height provided the best performance, demonstrating that adequate thrust turning can be produced by a trailing-edge shape which may have minimal cruise-performance penalty. Thrust deflections were achieved at considerably lower blowing momentum than was required for the baseline case of Phase 1. Improved performance and versatility were thus confirmed for the CCW/USB system applied to STOL aircraft, where the potential for developing a non-moving-parts pneumatic thrust deflector to rapidly vary horizontal force from thrust to drag, while maintaining constant vertical force, appears quite promising. The conversion from high-lift to lower-drag cruise mode by merely terminating the blowing provides an effective STOL aircraft system.

  4. An Experimntal Investigation of the 30P30N Multi-Element High-Lift Airfoil

    Science.gov (United States)

    Pascioni, Kyle A.; Cattafesta, Louis N.; Choudhari, Meelan M.

    2014-01-01

    High-lift devices often generate an unsteady flow field producing both broadband and tonal noise which radiates from the aircraft. In particular, the leading edge slat is often a dominant contributor to the noise signature. An experimental study of a simplified unswept high-lift configuration, the 30P30N, has been conducted to understand and identify the various flow-induced noise sources around the slat. Closed-wall wind tunnel tests are performed in the Florida State Aeroacoustic Tunnel (FSAT) to characterize the slat cove flow field using a combination of surface and off-body measurements. Mean surface pressures compare well with numerical predictions for the free-air configuration. Consistent with previous measurements and computations for 2D high-lift configurations, the frequency spectra of unsteady surface pressures on the slat surface display several narrowband peaks that decrease in strength as the angle of attack is increased. At positive angles of attack, there are four prominent peaks. The three higher frequency peaks correspond, approximately, to a harmonic sequence related to a feedback resonance involving unstable disturbances in the slat cove shear layer. The Strouhal numbers associated with these three peaks are nearly insensitive to the range of flow speeds (41-58 m/s) and the angles of attack tested (3-8.5 degrees). The first narrow-band peak has an order of magnitude lower frequency than the remaining peaks and displays noticeable sensitivity to the angle of attack. Stereoscopic particle image velocimetry (SPIV) measurements provide supplementary information about the shear layer characteristics and turbulence statistics that may be used for validating numerical simulations.

  5. Aircraft noise: Changes of biochemical parameters

    Energy Technology Data Exchange (ETDEWEB)

    Marth, E.; Moese, J.R.; Gallasch, E.; Fueger, G.F.

    1988-01-01

    The effect of stress caused by aircraft noise was studied on 14 female and 11 male volunteers, who were of a age ranging from 21 to 42 years and of a mean age of 25 years. The volunteers were exposed to an aircraft simulator the simulated the lowlevel flight of an airforce plane and produced a maximum noise level of 105 dB(A) for 3 sec. in a short time. Before and immediately after the exposure, the concentration of ACTH was measured by means of a radioimmunoassay. The ACTH is a hormone, responsible for initiating a chain-reaction that is characteristic for a stress reaction. In 100% of the cases the concentration of this hormone increased. It reached a pathological level in 28% of the cases. The effect on the lipid metabolism was expressed by an increase of total cholesterol and a decrease of the triglycerides in the serum. A slight increase in blood sugar which, together with the free fatty acids, is relatively quickly reduced to energy, could determined. The aircraft noise did not influence the activity of the liver transaminases in any way. A short-term exposure to aircraft noise is able to stimulate a stress reaction, whereby, the determination of the ACTH offers valuable informations.

  6. An Analysis of Ball Lightning-Aircraft Incidents

    Science.gov (United States)

    Doe, R. K.; Keul, A. G.; Bychkov, V.

    2009-12-01

    Lightning is a rare but regular phenomenon for air traffic. Research and design have created aircraft that withstand average lightning strikes. Ball lightning (BL), a metastable, rare lightning type, is also observed from (and within) aircraft. Science and the media focused on individual BL incidents and did not analyze general patterns. Lacking established incident reporting channels, most BL observations are still passed on as “aviation lore”. To overcome this unsatisfactory condition, the authors collected and analyzed an international data bank of 87 BL-aircraft case histories from 1938 to 2007. 37 Russian military and civil BL reports were provided by the third author. Of the whole sample, 36 (41%) cases occurred over Russia/RF/SU, 24 (28%) over USA/Canada, 23 (26%) over Europe, and 4 (5%) over Asia/Pacific. Various types of military (US: C-54/141, B-52, KC-97/135 Stratotankers, C130, P-3 Orion, RF/SU: PO-2, IL, SU, TU, MIG; Nimrod, Saab-105) and civilian aircraft (US: DC-3/6, Metroliner, B-727/737/757/777, RF/SU: AN, TU; VC-10, Fokker F-28, CRJ-200), as well as general aviation (C-172, Falcon-20), were involved. BL reports show a flat annual April to August maximum. At BL impact, 15 aircraft were climbing, 7 descending; most were at cruising altitude. 42 (48%) reported BL outside the aircraft, 37 (43%) inside, 7 (8%) both in-and outside. No damage was reported in 34 (39%) cases, 39 objects (45%) caused minor damage, 11 major damage (13%), 3 even resulted in military aircraft losses. 3 objects caused minor, 1 major crew injury. 23 damage cases were associated with BL inside the fuselage; all 4 crew injury cases were of that BL type. Mean size is described as 25 cm, sometimes over 1 m, color 30% in the yellow-red, 10% in the blue-green spectral region, 8% white, duration around 10 seconds, sometimes over 1 minute. 33 (38%) incidents ended with an explosion of the object. Thunderstorm conditions were reported by 25 (29%) of the observers, 9 (10%) said there

  7. Optimal trajectory and heat load analysis of different shape lifting reentry vehicles for medium range application

    Directory of Open Access Journals (Sweden)

    S. Tauqeer ul Islam Rizvi

    2015-12-01

    Full Text Available The objective of the paper is to compute the optimal burn-out conditions and control requirements that would result in maximum down-range/cross-range performance of a waverider type hypersonic boost-glide (HBG vehicle within the medium and intermediate ranges, and compare its performance with the performances of wing-body and lifting-body vehicles vis-à-vis the g-load and the integrated heat load experienced by vehicles for the medium-sized launch vehicle under study. Trajectory optimization studies were carried out by considering the heat rate and dynamic pressure constraints. The trajectory optimization problem is modeled as a nonlinear, multiphase, constraint optimal control problem and is solved using a hp-adaptive pseudospectral method. Detail modeling aspects of mass, aerodynamics and aerothermodynamics for the launch and glide vehicles have been discussed. It was found that the optimal burn-out angles for waverider and wing-body configurations are approximately 5° and 14.8°, respectively, for maximum down-range performance under the constraint heat rate environment. The down-range and cross-range performance of HBG waverider configuration is nearly 1.3 and 2 times that of wing-body configuration respectively. The integrated heat load experienced by the HBG waverider was found to be approximately an order of magnitude higher than that of a lifting-body configuration and 5 times that of a wing-body configuration. The footprints and corresponding heat loads and control requirements for the three types of glide vehicles are discussed for the medium range launch vehicle under consideration.

  8. Enabling Use of Unmanned Aircraft Systems for Arctic Environmental Monitoring

    DEFF Research Database (Denmark)

    Storvold, Rune; la Cour-Harbo, Anders; Mulac, Brenda;

    , satellites and manned aircraft are the traditional platforms on which scientists gather data of the atmosphere, sea ice, glaciers, fauna and vegetation. However, significant data gaps still exist over much of the Arctic because there are few research stations, satellites are often hindered by cloud cover......, poor resolution, and the complicated surface of snow and ice. Measurements made from manned aircraft are also limited because of range and endurance, as well as the danger and costs presented by operating manned aircraft in harsh and remote environments like the Arctic. Unmanned aircraft systems (UAS...

  9. Review of Aircraft Electric Power Systems and Architectures

    OpenAIRE

    Zhao, Xin; Guerrero, Josep M.; Wu, Xiaohao

    2014-01-01

    In recent years, the electrical power capacity is increasing rapidly in more electric aircraft (MEA), since the conventional mechanical, hydraulic and pneumatic energy systems are partly replaced by electrical power system. As a consequence, capacity and complexity of aircraft electric power systems (EPS) will increase dramatically and more advanced aircraft EPSs need to be developed. This paper gives a brief description of the constant frequency (CF) EPS, variable frequency (VF) EPS and adva...

  10. City of Hesperia Lift Station Design

    OpenAIRE

    Reichmuth , Karl; Bhatia, Gurleen; Bondar , Tatsiana; Cruikshank, Tyler; Moral, Juan; Paneto , Vanessa; Whittington, Chad; Wilson , Heidi

    2013-01-01

    Project Description:  Anteater and Associates has been contracted by HDR Engineering Inc. to construct a two-phase wastewater pump station for a residential community in Hesperia, California.  Project Goal: The project goal is to develop a pump station that will accommodate for an increase in wastewater production from a new residential track of homes that will some be built in the area.  The pump station will be implemented in tow-phases to ensure that as the residential communities grow the...

  11. Neutron radiography of aircraft composite flight control surfaces

    International Nuclear Information System (INIS)

    A small (20 kWth), safe, pool-type nuclear research reactor called the SLOWPOKE-2 is located at the Royal Military College of Canada (RMC). The reactor was originally installed for teaching, training, research and semi-routine analysis, specifically, neutron activation analysis. It was envisioned that the neutrons from the SLOWPOKE-2 could also be used for neutron radiography, and so a research program was initiated to develop this technology. Over a period of approximately 15 years, and through a series of successive modifications, a neutron radiography system (NRS) was developed. Once completed, several applications of the technology have been demonstrated, including the nondestructive examination of the composite flight control surfaces from the Canadian Air Force's primary jet fighter, the CF18 Hornet aircraft. An initial trial was setup to investigate the flight control surfaces of 3 aircraft, to determine the parameters for a final licensed system, and to compare the results to other nondestructive methods. Over 500 neutron radiographs were made for these first 3 aircraft, and moisture and corrosion were discovered in the honeycomb structure and hydration was found in the composite and adhesive layers. In comparison with other NDT methods, neutron radiography was the only method that could detect the small areas of corrosion and moisture entrapment. However, before examining an additional 7 aircraft, the recommended modifications to the NRS were undertaken. These modifications were necessary to accommodate the larger flight control surfaces safely by incorporating flexible conformable shielding. As well, to expedite inspections so that all flight control surfaces from one aircraft could be completed in less than two weeks, there was a need to decrease the exposure time by both faster film/conversion screen combinations and by incorporating the capability of near realtime, digital radioscopy. Finally, as there are no inspection specific image quality

  12. Static mechanical properties of 30 x 11.5-14.5, type VII, aircraft tires of bias-ply and radial-belted design

    Science.gov (United States)

    Davis, Pamela A.; Lopez, Mercedes C.

    1987-01-01

    An investigation was conducted to determine the static mechanical characteristics of 30 x 115-14.5 bias-ply and radial aircraft tires. The tires were subjected to vertical and lateral loads and mass moment of inertia tests were conducted. Static load deflection curves, spring rates, hysteresis losses, and inertia data are presented along with a discussion of the advantages and disadvantages of one tire over the other.

  13. Challenges of aircraft design integration

    OpenAIRE

    Kafyeke, F.; Abdo, M.; Pepin, F; Piperni, P.; Laurendeau, E.

    2007-01-01

    The design of a modern airplane brings together many disciplines: structures, aerodynamics, controls, systems, propulsion with complex interdependencies and many variables. Recent aircraft programs, such as Bombardier's Continental Jet program use participants located around the world and selected for their cost, quality and delivery capability. These participants share the risk on the program and must therefore be fully implicated in the design. A big challenge is to provide information on c...

  14. The coupled nonlinear dynamics of a lift system

    International Nuclear Information System (INIS)

    Coupled lateral and longitudinal vibrations of suspension and compensating ropes in a high-rise lift system are often induced by the building motions due to wind or seismic excitations. When the frequencies of the building become near the natural frequencies of the ropes, large resonance motions of the system may result. This leads to adverse coupled dynamic phenomena involving nonplanar motions of the ropes, impact loads between the ropes and the shaft walls, as well as vertical vibrations of the car, counterweight and compensating sheave. Such an adverse dynamic behaviour of the system endangers the safety of the installation. This paper presents two mathematical models describing the nonlinear responses of a suspension/ compensating rope system coupled with the elevator car / compensating sheave motions. The models accommodate the nonlinear couplings between the lateral and longitudinal modes, with and without longitudinal inertia of the ropes. The partial differential nonlinear equations of motion are derived using Hamilton Principle. Then, the Galerkin method is used to discretise the equations of motion and to develop a nonlinear ordinary differential equation model. Approximate numerical solutions are determined and the behaviour of the system is analysed

  15. The coupled nonlinear dynamics of a lift system

    Science.gov (United States)

    Crespo, Rafael Sánchez; Kaczmarczyk, Stefan; Picton, Phil; Su, Huijuan

    2014-12-01

    Coupled lateral and longitudinal vibrations of suspension and compensating ropes in a high-rise lift system are often induced by the building motions due to wind or seismic excitations. When the frequencies of the building become near the natural frequencies of the ropes, large resonance motions of the system may result. This leads to adverse coupled dynamic phenomena involving nonplanar motions of the ropes, impact loads between the ropes and the shaft walls, as well as vertical vibrations of the car, counterweight and compensating sheave. Such an adverse dynamic behaviour of the system endangers the safety of the installation. This paper presents two mathematical models describing the nonlinear responses of a suspension/ compensating rope system coupled with the elevator car / compensating sheave motions. The models accommodate the nonlinear couplings between the lateral and longitudinal modes, with and without longitudinal inertia of the ropes. The partial differential nonlinear equations of motion are derived using Hamilton Principle. Then, the Galerkin method is used to discretise the equations of motion and to develop a nonlinear ordinary differential equation model. Approximate numerical solutions are determined and the behaviour of the system is analysed.

  16. The coupled nonlinear dynamics of a lift system

    Energy Technology Data Exchange (ETDEWEB)

    Crespo, Rafael Sánchez, E-mail: rafael.sanchezcrespo@northampton.ac.uk, E-mail: stefan.kaczmarczyk@northampton.ac.uk, E-mail: phil.picton@northampton.ac.uk, E-mail: huijuan.su@northampton.ac.uk; Kaczmarczyk, Stefan, E-mail: rafael.sanchezcrespo@northampton.ac.uk, E-mail: stefan.kaczmarczyk@northampton.ac.uk, E-mail: phil.picton@northampton.ac.uk, E-mail: huijuan.su@northampton.ac.uk; Picton, Phil, E-mail: rafael.sanchezcrespo@northampton.ac.uk, E-mail: stefan.kaczmarczyk@northampton.ac.uk, E-mail: phil.picton@northampton.ac.uk, E-mail: huijuan.su@northampton.ac.uk; Su, Huijuan, E-mail: rafael.sanchezcrespo@northampton.ac.uk, E-mail: stefan.kaczmarczyk@northampton.ac.uk, E-mail: phil.picton@northampton.ac.uk, E-mail: huijuan.su@northampton.ac.uk [The University of Northampton, School of Science and Technology, Avenue Campus, St George' s Avenue, Northampton (United Kingdom)

    2014-12-10

    Coupled lateral and longitudinal vibrations of suspension and compensating ropes in a high-rise lift system are often induced by the building motions due to wind or seismic excitations. When the frequencies of the building become near the natural frequencies of the ropes, large resonance motions of the system may result. This leads to adverse coupled dynamic phenomena involving nonplanar motions of the ropes, impact loads between the ropes and the shaft walls, as well as vertical vibrations of the car, counterweight and compensating sheave. Such an adverse dynamic behaviour of the system endangers the safety of the installation. This paper presents two mathematical models describing the nonlinear responses of a suspension/ compensating rope system coupled with the elevator car / compensating sheave motions. The models accommodate the nonlinear couplings between the lateral and longitudinal modes, with and without longitudinal inertia of the ropes. The partial differential nonlinear equations of motion are derived using Hamilton Principle. Then, the Galerkin method is used to discretise the equations of motion and to develop a nonlinear ordinary differential equation model. Approximate numerical solutions are determined and the behaviour of the system is analysed.

  17. Additional Development and Systems Analyses of Pneumatic Technology for High Speed Civil Transport Aircraft

    Science.gov (United States)

    Englar, Robert J.; Willie, F. Scott; Lee, Warren J.

    1999-01-01

    In the Task I portion of this NASA research grant, configuration development and experimental investigations have been conducted on a series of pneumatic high-lift and control surface devices applied to a generic High Speed Civil Transport (HSCT) model configuration to determine their potential for improved aerodynamic performance, plus stability and control of higher performance aircraft. These investigations were intended to optimize pneumatic lift and drag performance; provide adequate control and longitudinal stability; reduce separation flowfields at high angle of attack; increase takeoff/climbout lift-to-drag ratios; and reduce system complexity and weight. Experimental aerodynamic evaluations were performed on a semi-span HSCT generic model with improved fuselage fineness ratio and with interchangeable plain flaps, blown flaps, pneumatic Circulation Control Wing (CCW) high-lift configurations, plain and blown canards, a novel Circulation Control (CC) cylinder blown canard, and a clean cruise wing for reference. Conventional tail power was also investigated for longitudinal trim capability. Also evaluated was unsteady pulsed blowing of the wing high-lift system to determine if reduced pulsed mass flow rates and blowing requirements could be made to yield the same lift as that resulting from steady-state blowing. Depending on the pulsing frequency applied, reduced mass flow rates were indeed found able to provide lift augmentation at lesser blowing values than for the steady conditions. Significant improvements in the aerodynamic characteristics leading to improved performance and stability/control were identified, and the various components were compared to evaluate the pneumatic potential of each. Aerodynamic results were provided to the Georgia Tech Aerospace System Design Lab. to conduct the companion system analyses and feasibility study (Task 2) of theses concepts applied to an operational advanced HSCT aircraft. Results and conclusions from these

  18. Benign prostatic hyperplasia and new treatment options – a critical appraisal of the UroLift system

    Directory of Open Access Journals (Sweden)

    McNicholas TA

    2016-05-01

    Full Text Available Thomas Anthony McNicholas1–3 1Section of Urology, Royal Society of Medicine, London, UK; 2Urology Department, Lister Hospital, East and North Herts NHS Trust, Stevenage, UK; 3Faculty of Health and Human Sciences, University of Hertfordshire, Hatfield, Herts, UK Abstract: The prostatic urethral lift procedure, more commonly known as UroLift, has been designed to improve male lower urinary tract symptoms while avoiding the complications and disadvantages of existing drug and surgical therapies. In particular, UroLift does not damage ejaculatory function or affect orgasmic sensation. It appears an option for men who wish to avoid long-term drug therapy, the side effects of drugs or surgery and who do not need or will not accept traditional surgical treatments. UroLift was introduced following a series of planned studies that led to US Food and Drug Administration approval in September 2013. UroLift has recently been approved by the UK National Institute for Clinical and Health Excellence (September 2015 as effective and safe and cost-effective for use in the UK health system. This review describes the device and the procedure and the evidence base that has led to those approvals. Keywords: UroLift, prostatic urethral lift, LUTS prostatic hyperplasia, minimally invasive, BPH

  19. Computer Aided Visual Inspection of Aircraft Surfaces

    Directory of Open Access Journals (Sweden)

    Rafia Mumtaz

    2012-02-01

    Full Text Available Non Destructive Inspections (NDI plays a vital role in aircraft industry as it determines the structural integrity of aircraft surface and material characterization. The existing NDI methods are time consuming, we propose a new NDI approach using Digital Image Processing that has the potential to substantially decrease the inspection time. Automatic Marking of cracks have been achieved through application of Thresholding, Gabor Filter and Non Subsampled Contourlet transform. For a novel method of NDI, the aircraft imagery is analyzed by three methods i.e Neural Networks, Contourlet Transform (CT and Discrete Cosine Transform (DCT. With the help of Contourlet Transform the two dimensional (2-D spectrum is divided into fine slices, using iterated directional filterbanks. Next, directional energy components for each block of the decomposed subband outputs are computed. These energy values are used to distinguish between the crack and scratch images using the Dot Product classifier. In next approach, the aircraft imagery is decomposed into high and low frequency components using DCT and the first order moment is determined to form feature vectors.A correlation based approach is then used for distinction between crack and scratch surfaces. A comparative examination between the two techniques on a database of crack and scratch images revealed that texture analysis using the combined transform based approach gave the best results by giving an accuracy of 96.6% for the identification of crack surfaces and 98.3% for scratch surfaces.

  20. Computed tomography evaluation of autogenous graft in sinus lift surgery

    International Nuclear Information System (INIS)

    The objective was to quantify bone formation within autogenous bone grafts and autogenous bone grafts in combination with platelet-rich plasma obtained either from apheresis or centrifugation using computed tomography. This prospective, double-blind study was conducted in 34 male and female adult patients (mean age of 28 years and 8 months), with either unilateral or bilateral pneumatization of the maxillary sinuses, requiring bone graft for dental implant. All patients were submitted to computed tomography examinations prior and six months after sinus lift surgery. Fifty-three maxillary sinuses were operated and divided into three distinct groups: autogenous bone graft, autogenous bone graft in combination with platelet-rich plasma obtained by centrifugation, and autogenous bone graft in combination with platelet-rich plasma obtained by apheresis. The results showed that computed tomography demonstrated bone growth in height and width between the initial and the follow-up computed tomography scans in all three groups. However, no statistical difference was found either for bone height or width. It was concluded that clinical evidence demonstrates the effectiveness of autogenous bone grafts, particularly when used in combination with bone growth factors such as platelet-rich plasma, which allow prosthetic and functional restoration of maxillofacial structures through fixation of dental implants. (author)