Tactical missile aerodynamics

Science.gov (United States)

Hemsch, Michael J. (Editor); Nielsen, Jack N. (Editor)

1986-01-01

The present conference on tactical missile aerodynamics discusses autopilot-related aerodynamic design considerations, flow visualization methods' role in the study of high angle-of-attack aerodynamics, low aspect ratio wing behavior at high angle-of-attack, supersonic airbreathing propulsion system inlet design, missile bodies with noncircular cross section and bank-to-turn maneuvering capabilities, 'waverider' supersonic cruise missile concepts and design methods, asymmetric vortex sheding phenomena from bodies-of-revolution, and swept shock wave/boundary layer interaction phenomena. Also discussed are the assessment of aerodynamic drag in tactical missiles, the analysis of supersonic missile aerodynamic heating, the 'equivalent angle-of-attack' concept for engineering analysis, the vortex cloud model for body vortex shedding and tracking, paneling methods with vorticity effects and corrections for nonlinear compressibility, the application of supersonic full potential method to missile bodies, Euler space marching methods for missiles, three-dimensional missile boundary layers, and an analysis of exhaust plumes and their interaction with missile airframes.

Aircraft engine pollution reduction.

Science.gov (United States)

Rudey, R. A.

1972-01-01

The effect of engine operation on the types and levels of the major aircraft engine pollutants is described and the major factors governing the formation of these pollutants during the burning of hydrocarbon fuel are discussed. Methods which are being explored to reduce these pollutants are discussed and their application to several experimental research programs are pointed out. Results showing significant reductions in the levels of carbon monoxide, unburned hydrocarbons, and oxides of nitrogen obtained from experimental combustion research programs are presented and discussed to point out potential application to aircraft engines. An experimental program designed to develop and demonstrate these and other advanced, low pollution combustor design methods is described. Results that have been obtained to date indicate considerable promise for reducing advanced engine exhaust pollutants to levels significantly below current engines.

Evaluation of sealing performance of metal cask subjected to vertical impact load due to aircraft engine

International Nuclear Information System (INIS)

Namba, Kosuke; Shirai, Koji; Saegusa, Toshiari

2010-01-01

To confirm the sealing performance of a metal cask subjected to impact force due to commercial aircraft crash against a spent fuel storage facility, a vertical impact test was carried out. In this test, a simplified deformable missile was used by considering the rigidity of the actual aircraft engine and accelerated to the specified impact velocity (60 m/s) to hit the full-scale lid structure with the primary and secondary lids. Then, the leak rate, the inner pressure between the lids, and the displacement of the lids were measured. The leak rate of the secondary lid exceeded 1.0x10 -3 Pa·m 3 /s upon impact. However, because no residual lid opening displacement occurred after loading, the leak rate recovered to less than 1.0x10 -6 Pa·m 3 /s after 3 h from the impact test. In addition, to clarify the impact behaviour of the lid structure, the impact analysis using the LS-DYNA code was executed. It was found that the lid bolts maintained the good tightening force after impact loading, and the sealing performance of the full-scale metal cask would not be affected immediately by the vertical impact of the aircraft engine with a speed of 60 m/s. (author)

Controlling ballistic missiles: How important? How to do it?

International Nuclear Information System (INIS)

Harvey, J.R.; Rubin, U.

1992-01-01

Missiles themselves are not weapons of mass destruction; they do not give states the ability to wreak unimaginable destruction, or to radically shift the balance of power, as nuclear weapons do. Hence, the primary focus of nonproliferation efforts should remain on weapons of mass destruction, particularly nuclear weapons, rather than on one of the many possible means of delivering them. Moreover, as discussed in more detail below, advanced strike aircraft can also be effective in delivering nuclear weapons, and are generally more effective than ballistic missiles for delivering conventional or chemical ordnance. Ultimately, if the industrialized nations seriously desire to control the spread of delivery means for weapons of mass destruction, they need to consider bringing controls over ballistic missiles and advanced strike aircraft more into balance. At the same time, while efforts to control ballistic missile proliferation - centered on the Missile Technology Control Regime (MTCR) - have had some successes and could be strengthened, US policy will be most effective if it recognizes two key realities: the spread of ballistic missiles cannot be as comprehensively controlled as the spread of nuclear weapons, nor need it be as comprehensively controlled

How to optimize joint theater ballistic missile defense

OpenAIRE

Diehl, Douglas D.

2004-01-01

Approved for public release, distribution is unlimited Many potential adversaries seek, or already have theater ballistic missiles capable of threatening targets of interest to the United States. The U.S. Missile Defense Agency and armed forces are developing and fielding missile interceptors carried by many different platforms, including ships, aircraft, and ground units. Given some exigent threat, the U.S. must decide where to position defensive platforms and how they should engage poten...

Impact load time histories for viscoelastic missiles

International Nuclear Information System (INIS)

Stoykovich, M.

1977-01-01

Generation of the impact load time history at the contact point between a viscoelastic missile and its targets is presented. In the past, in the case of aircraft striking containment shell structure, the impact load history was determined on the basis of actual measurements by subjecting a rigid wall to aircraft crash. The effects of elastic deformation of the target upon the impact load time history is formulated in this paper. The missile is idealized by a linear mass-spring-dashpot combination using viscoelastic models. These models can readily be processed taking into account the elastic as well as inelastic deformations of the missiles. The target is assumed to be either linearly elastic or rigid. In the case of the linearly elastic target, the normal mode theory is used to express the time-dependent displacements of the target which is simulated by lumped masses, elastic properties and dashpots in discrete parts. In the case of Maxwell viscoelastic model, the time-dependent displacements of the missile and the target are given in terms of the unknown impact load time history. This leads to an integral equation which may be solved by Laplace transformation. The normal mode theory is provided. Examples are given for bricks with viscoelastic materials as missiles against a rigid target. (Auth.)

IR sensor design insight from missile-plume prediction models

Science.gov (United States)

Rapanotti, John L.; Gilbert, Bruno; Richer, Guy; Stowe, Robert

2002-08-01

Modern anti-tank missiles and the requirement of rapid deployment have significantly reduced the use of passive armour in protecting land vehicles. Vehicle survivability is becoming more dependent on sensors, computers and countermeasures to detect and avoid threats. An analysis of missile propellants suggests that missile detection based on plume characteristics alone may be more difficult than anticipated. Currently, the passive detection of missiles depends on signatures with a significant ultraviolet component. This approach is effective in detecting anti-aircraft missiles that rely on powerful motors to pursue high-speed aircraft. The high temperature exhaust from these missiles contains significant levels of carbon dioxide, water and, often, metal oxides such as alumina. The plumes emits strongest in the infrared, 1 to 5micrometers , regions with a significant component of the signature extending into the ultraviolet domain. Many anti-tank missiles do not need the same level of propulsion and radiate significantly less. These low velocity missiles, relying on the destructive force of shaped-charge warhead, are more difficult to detect. There is virtually no ultraviolet component and detection based on UV sensors is impractical. The transition in missile detection from UV to IR is reasonable, based on trends in imaging technology, but from the analysis presented in this paper even IR imagers may have difficulty in detecting missile plumes. This suggests that the emphasis should be placed in the detection of the missile hard body in the longer wavelengths of 8 to 12micrometers . The analysis described in this paper is based on solution of the governing equations of plume physics and chemistry. These models will be used to develop better sensors and threat detection algorithms.

Nanotechnology for missiles

Science.gov (United States)

Ruffin, Paul B.

2004-07-01

Nanotechnology development is progressing very rapidly. Several billions of dollars have been invested in nanoscience research since 2000. Pioneering nanotechnology research efforts have been primarily conducted at research institutions and centers. This paper identifies developments in nanoscience and technology that could provide significant advances in missile systems applications. Nanotechnology offers opportunities in the areas of advanced materials for coatings, including thin-film optical coatings, light-weight, strong armor and missile structural components, embedded computing, and "smart" structures; nano-particles for explosives, warheads, turbine engine systems, and propellants to enhance missile propulsion; nano-sensors for autonomous chemical detection; and nano-tube arrays for fuel storage and power generation. The Aviation and Missile Research, Development, and Engineering Center (AMRDEC) is actively collaborating with academia, industry, and other Government agencies to accelerate the development and transition of nanotechnology to favorably impact Army Transformation. Currently, we are identifying near-term applications and quantifying requirements for nanotechnology use in Army missile systems, as well as monitoring and screening research and developmental efforts in the industrial community for military applications. Combining MicroElectroMechanical Systems (MEMS) and nanotechnology is the next step toward providing technical solutions for the Army"s transformation. Several research and development projects that are currently underway at AMRDEC in this technology area are discussed. A top-level roadmap of MEMS/nanotechnology development projects for aviation and missile applications is presented at the end.

A Study on External Fire Damage of Structures subjected to Aircraft Impact

International Nuclear Information System (INIS)

Shin, Sang Shup; Hahm, Daegi; Kim, Min Kyu

2015-01-01

A large commercial aircraft consists of various components as fuselage, wings, fuel tank, engine etc. During a collision of the aircraft, the fuel tank with a large amount of jet fuel have a significant effect on the total load of the aircraft as well as causing explosive fire and smoke which affect the safety of the structure and equipment. US Sandia National Laboratories and Finland VTT etc. performed the test and simulation studies to evaluate the dispersion range of the fluid after the crash of liquid filled cylinder missiles. The test condition and results have been referred in this paper. The fluid modeling approach using SPH is applied to evaluate the dispersing range of the fluid, and is compared with the Brown's results. The jet fuel is idealized as particles contained in an aluminum cylinder missile, where those particles can be dispersed to the surrounding area after the missile crashes into a rigid target. The fluid model using the SPH method is briefly verified through comparison with test results, and then the modelling method is applied to a jet fuel model in an aircraft model. The dispersion analysis of jet fuel caused by aircraft impact is performed using an aircraft model for the determination of fire duration and fire affected zone in a nuclear power plant. Finally, the structural integrity of the roof of the structure during a jet fuel fire is evaluated. In this study, the filled jet fuel was modeled by using smooth particle hydrodynamics technique; jet fuel spread area following an aircraft crash was analyzed

A Study on External Fire Damage of Structures subjected to Aircraft Impact

Energy Technology Data Exchange (ETDEWEB)

Shin, Sang Shup [Hanyang University, Seoul (Korea, Republic of); Hahm, Daegi; Kim, Min Kyu [Korea Atomic Energy Research Institute, Daejeon (Korea, Republic of)

2015-10-15

A large commercial aircraft consists of various components as fuselage, wings, fuel tank, engine etc. During a collision of the aircraft, the fuel tank with a large amount of jet fuel have a significant effect on the total load of the aircraft as well as causing explosive fire and smoke which affect the safety of the structure and equipment. US Sandia National Laboratories and Finland VTT etc. performed the test and simulation studies to evaluate the dispersion range of the fluid after the crash of liquid filled cylinder missiles. The test condition and results have been referred in this paper. The fluid modeling approach using SPH is applied to evaluate the dispersing range of the fluid, and is compared with the Brown's results. The jet fuel is idealized as particles contained in an aluminum cylinder missile, where those particles can be dispersed to the surrounding area after the missile crashes into a rigid target. The fluid model using the SPH method is briefly verified through comparison with test results, and then the modelling method is applied to a jet fuel model in an aircraft model. The dispersion analysis of jet fuel caused by aircraft impact is performed using an aircraft model for the determination of fire duration and fire affected zone in a nuclear power plant. Finally, the structural integrity of the roof of the structure during a jet fuel fire is evaluated. In this study, the filled jet fuel was modeled by using smooth particle hydrodynamics technique; jet fuel spread area following an aircraft crash was analyzed.

Key considerations in infrared simulations of the missile-aircraft engagement

CSIR Research Space (South Africa)

Willers, MS

2012-09-01

Full Text Available is required to steer the missile towards the target, using the seeker-provided target sight-line for missile guidance.These requirements are satisfied by detailed models for aerodynamics, flight control servos, the auto-pilot and guidance and navigation...

Design and Testing of a Combustor for a Turbo-Ramjet Engine for UAV and Missile Applications

Science.gov (United States)

2003-03-01

CA, September 1999. 6. Al- Namani , S . M., Development of Shrouded Turbojet to Form a Turboramjet for Future Missile Applications, Master’s Thesis...Turbo- ramjet Engine for UAV and Missile Applications 6. AUTHOR( S ) Ross H. Piper III 5. FUNDING NUMBERS 7. PERFORMING ORGANIZATION NAME( S ) AND...ADDRESS(ES) Naval Postgraduate School Monterey, CA 93943-5000 8. PERFORMING ORGANIZATION REPORT NUMBER 9. SPONSORING / MONITORING AGENCY NAME( S

Increased Range/Mini-Cruise Missile

National Research Council Canada - National Science Library

2006-01-01

Technical Directions Inc. (TDI), Ortonville, Michigan, was asked by the U.S. Army and the U.S. Air Force to improve the efficiency of their J-45 missile engine for the NLOS-LS LAM Loitering Attack Missile...

The Study of Foreign Object Damage Caused by Aircraft Operations on Unconventional and Bomb-Damaged Airfield Surfaces.

Science.gov (United States)

1981-06-01

missile IR seeker heads and EO missiles such as MAVERICK should not be a problem for limited exposure of takeoff and landing. (3) Aircraft engines are...no rocks are thrown ahead of the tire. b. A trampoline effect exists directly behind the tire wherein the rebound of the soil tosses the surface...the fuselage skin as 138 scratches in the paint. One possible explanation is that the stones were raised by the trampoline effect and then received an

Elimination of the Roll Bias Caused by Wrap Around Fins for the FMTI Missile

National Research Council Canada - National Science Library

McKerley, C

1998-01-01

The Future Missile Technology Integration (FMTI) Missile System is an attempt to design an Army tactical weapon that can effectively attack both fixed and rotary wing aircraft and armor of all types...

20th Annual Systems Engineering Conference. Volume 2, Wednesday

Science.gov (United States)

2017-10-26

Roadmap Key Capability Areas C yber M odeling, Sim ulation, and Experim entation (M SE) Em bedded, M obile, and Tactical System s ( EM T) (MSE & EMT) cross...Space Weapons Missile Bomb Sensors WS Characteristics WS Quality Properties Defining Themes WS Engineering Methods WS Types | 10 | This technical data...aircraft 10 Aircraft depart initial point (IP) 11 JTAC controls CAS aircraft 12 Bombs on target 13 Assessment < 3min < 2 min > 95% Acrcy ASOC/ DASC CAS

Calculation of odour emissions from aircraft engines at Copenhagen Airport

Energy Technology Data Exchange (ETDEWEB)

Winther, Morten; Kousgaard, Uffe [National Environmental Research Institute, Frederiksborgvej 399, 4000 Roskilde (Denmark); Oxboel, Arne [FORCE Technology, Park Alle 345, 2605 Broendby (Denmark)

2006-07-31

In a new approach the odour emissions from aircraft engines at Copenhagen Airport are calculated using actual fuel flow and emission measurements (one main engine and one APU: Auxiliary Power Unit), odour panel results, engine specific data and aircraft operational data for seven busy days. The calculation principle assumes a linear relation between odour and HC emissions. Using a digitalisation of the aircraft movements in the airport area, the results are depicted on grid maps, clearly reflecting aircraft operational statistics as single flights or total activity during a whole day. The results clearly reflect the short-term temporal fluctuations of the emissions of odour (and exhaust gases). Aircraft operating at low engine thrust (taxiing, queuing and landing) have a total odour emission share of almost 98%, whereas the shares for the take off/climb out phases (2%) and APU usage (0.5%) are only marginal. In most hours of the day, the largest odour emissions occur, when the total amount of fuel burned during idle is high. However, significantly higher HC emissions for one specific engine cause considerable amounts of odour emissions during limited time periods. The experimentally derived odour emission factor of 57 OU/mg HC is within the range of 23 and 110 OU/mg HC used in other airport odour studies. The distribution of odour emission results between aircraft operational phases also correspond very well with the results for these other studies. The present study uses measurement data for a representative engine. However, the uncertainties become large when the experimental data is used to estimate the odour emissions for all aircraft engines. More experimental data is needed to increase inventory accuracy, and in terms of completeness it is recommended to make odour emission estimates also for engine start and the fuelling of aircraft at Copenhagen Airport in the future. (author)

Calculation of odour emissions from aircraft engines at Copenhagen Airport.

Science.gov (United States)

Winther, Morten; Kousgaard, Uffe; Oxbøl, Arne

2006-07-31

In a new approach the odour emissions from aircraft engines at Copenhagen Airport are calculated using actual fuel flow and emission measurements (one main engine and one APU: Auxiliary Power Unit), odour panel results, engine specific data and aircraft operational data for seven busy days. The calculation principle assumes a linear relation between odour and HC emissions. Using a digitalisation of the aircraft movements in the airport area, the results are depicted on grid maps, clearly reflecting aircraft operational statistics as single flights or total activity during a whole day. The results clearly reflect the short-term temporal fluctuations of the emissions of odour (and exhaust gases). Aircraft operating at low engine thrust (taxiing, queuing and landing) have a total odour emission share of almost 98%, whereas the shares for the take off/climb out phases (2%) and APU usage (0.5%) are only marginal. In most hours of the day, the largest odour emissions occur, when the total amount of fuel burned during idle is high. However, significantly higher HC emissions for one specific engine cause considerable amounts of odour emissions during limited time periods. The experimentally derived odour emission factor of 57 OU/mg HC is within the range of 23 and 110 OU/mg HC used in other airport odour studies. The distribution of odour emission results between aircraft operational phases also correspond very well with the results for these other studies. The present study uses measurement data for a representative engine. However, the uncertainties become large when the experimental data is used to estimate the odour emissions for all aircraft engines. More experimental data is needed to increase inventory accuracy, and in terms of completeness it is recommended to make odour emission estimates also for engine start and the fuelling of aircraft at Copenhagen Airport in the future.

Ship Anti Ballistic Missile Response (SABR)

OpenAIRE

Johnson, Allen P.; Breeden, Bryan; Duff, Willard Earl; Fishcer, Paul F.; Hornback, Nathan; Leiker, David C.; Carlisle, Parker; Diersing, Michael; Devlin, Ryan; Glenn, Christopher; Hoffmeister, Chris; Chong, Tay Boon; Sing, Phang Nyit; Meng, Low Wee; Meng, Fann Chee

2006-01-01

Includes supplementary material. Based on public law and Presidential mandate, ballistic missile defense development is a front-burner issue for homeland defense and the defense of U.S. and coalition forces abroad. Spearheaded by the Missile Defense Agency, an integrated ballistic missile defense system was initiated to create a layered defense composed of land-, air-, sea-, and space-based assets. The Ship Anti-Ballistic Response (SABR) Project is a systems engineering approach t...

Aircraft vulnerability analysis by modelling and simulation

CSIR Research Space (South Africa)

Willers, CJ

2014-09-01

Full Text Available attributable to misuse of the weapon or to missile performance restrictions. This paper analyses some of the factors affecting aircraft vulnerability and demonstrates a structured analysis of the risk and aircraft vulnerability problem. The aircraft...

Final Rule for Control of Air Pollution From Aircraft and Aircraft Engines; Emission Standards and Test Procedures

Science.gov (United States)

EPA adopted emission standards and related provisions for aircraft gas turbine engines with rated thrusts greater than 26.7 kilonewtons. These engines are used primarily on commercial passenger and freight aircraft.

Control Design for a Generic Commercial Aircraft Engine

Science.gov (United States)

Csank, Jeffrey; May, Ryan D.

2010-01-01

This paper describes the control algorithms and control design process for a generic commercial aircraft engine simulation of a 40,000 lb thrust class, two spool, high bypass ratio turbofan engine. The aircraft engine is a complex nonlinear system designed to operate over an extreme range of environmental conditions, at temperatures from approximately -60 to 120+ F, and at altitudes from below sea level to 40,000 ft, posing multiple control design constraints. The objective of this paper is to provide the reader an overview of the control design process, design considerations, and justifications as to why the particular architecture and limits have been chosen. The controller architecture contains a gain-scheduled Proportional Integral controller along with logic to protect the aircraft engine from exceeding any limits. Simulation results illustrate that the closed loop system meets the Federal Aviation Administration s thrust response requirements

Research of Short-range Missile Motion in Terms of Different Wind Loads

Directory of Open Access Journals (Sweden)

A. N. Klishin

2015-01-01

Full Text Available When modeling the aircraft motion it is advisable to choose a particular model of the Earth, depending both on the task and on the required accuracy of calculation. The article describes various models of the Earth, such as the flat Earth with a plane-parallel field of gravity, spherical and non-rotating Earth with a plane-parallel field of gravity, spherical and non-rotating Earth with a central gravitational field, spherical and non-rotating Earth, taking into account the polar flattening of the Earth, spherical Earth based compression and polar daily rotation. The article also considers the influence of these models on the motion of the selected aircraft.To date, there is technical equipment to provide highly accurate description of the Earthshape, gravitational field, etc. The improved accuracy of the Earth model description results in more correct description of the trajectory and motion parameters of a ballistic missile. However, for short ranges (10-20 km this accuracy is not essential, and, furthermore, it increases time of calculation. Therefore, there is a problem of choosing the optimal description of the Earth parameters.The motion in the model of the Earth, which takes into account a daily rotation of the planet and polar flattening, is discussed in more detail, and the geographical latitude impact on coordinates of the points of fall of a ballistic missile is analyzed on the basis of obtained graphs.The article individually considers a problem of the wind effect on the aircraft motion and defines dependences of the missile motion on the parameters of different wind loads, such as wind speed and height of its action.A mathematical model of the missile motion was built and numerically integrated, using the Runge-Kutta 4th order method, for implementation and subsequent analysis.Based on the analysis of the calculation results in the abovementioned models of the Earth, differences in impact of these models on the parameters of the

Survey of engineering computational methods and experimental programs for estimating supersonic missile aerodynamic characteristics

Science.gov (United States)

Sawyer, W. C.; Allen, J. M.; Hernandez, G.; Dillenius, M. F. E.; Hemsch, M. J.

1982-01-01

This paper presents a survey of engineering computational methods and experimental programs used for estimating the aerodynamic characteristics of missile configurations. Emphasis is placed on those methods which are suitable for preliminary design of conventional and advanced concepts. An analysis of the technical approaches of the various methods is made in order to assess their suitability to estimate longitudinal and/or lateral-directional characteristics for different classes of missile configurations. Some comparisons between the predicted characteristics and experimental data are presented. These comparisons are made for a large variation in flow conditions and model attitude parameters. The paper also presents known experimental research programs developed for the specific purpose of validating analytical methods and extending the capability of data-base programs.

Aircraft Engine Thrust Estimator Design Based on GSA-LSSVM

Science.gov (United States)

Sheng, Hanlin; Zhang, Tianhong

2017-08-01

In view of the necessity of highly precise and reliable thrust estimator to achieve direct thrust control of aircraft engine, based on support vector regression (SVR), as well as least square support vector machine (LSSVM) and a new optimization algorithm - gravitational search algorithm (GSA), by performing integrated modelling and parameter optimization, a GSA-LSSVM-based thrust estimator design solution is proposed. The results show that compared to particle swarm optimization (PSO) algorithm, GSA can find unknown optimization parameter better and enables the model developed with better prediction and generalization ability. The model can better predict aircraft engine thrust and thus fulfills the need of direct thrust control of aircraft engine.

Rankine-Brayton engine powered solar thermal aircraft

Science.gov (United States)

Bennett, Charles L [Livermore, CA

2009-12-29

A solar thermal powered aircraft powered by heat energy from the sun. A Rankine-Brayton hybrid cycle heat engine is carried by the aircraft body for producing power for a propulsion mechanism, such as a propeller or other mechanism for enabling sustained free flight. The Rankine-Brayton engine has a thermal battery, preferably containing a lithium-hydride and lithium mixture, operably connected to it so that heat is supplied from the thermal battery to a working fluid. A solar concentrator, such as reflective parabolic trough, is movably connected to an optically transparent section of the aircraft body for receiving and concentrating solar energy from within the aircraft. Concentrated solar energy is collected by a heat collection and transport conduit, and heat transported to the thermal battery. A solar tracker includes a heliostat for determining optimal alignment with the sun, and a drive motor actuating the solar concentrator into optimal alignment with the sun based on a determination by the heliostat.

Rankline-Brayton engine powered solar thermal aircraft

Science.gov (United States)

Bennett, Charles L [Livermore, CA

2012-03-13

A solar thermal powered aircraft powered by heat energy from the sun. A Rankine-Brayton hybrid cycle heat engine is carried by the aircraft body for producing power for a propulsion mechanism, such as a propeller or other mechanism for enabling sustained free flight. The Rankine-Brayton engine has a thermal battery, preferably containing a lithium-hydride and lithium mixture, operably connected to it so that heat is supplied from the thermal battery to a working fluid. A solar concentrator, such as reflective parabolic trough, is movably connected to an optically transparent section of the aircraft body for receiving and concentrating solar energy from within the aircraft. Concentrated solar energy is collected by a heat collection and transport conduit, and heat transported to the thermal battery. A solar tracker includes a heliostat for determining optimal alignment with the sun, and a drive motor actuating the solar concentrator into optimal alignment with the sun based on a determination by the heliostat.

Multi-Fuel Rotary Engine for General Aviation Aircraft

Science.gov (United States)

Jones, C.; Ellis, D. R.; Meng, P. R.

1983-01-01

Design studies, conducted for NASA, of Advanced Multi-fuel General Aviation and Commuter Aircraft Rotary Stratified Charge Engines are summarized. Conceptual design studies of an advanced engine sized to provide 186/250 shaft KW/HP under cruise conditions at 7620/25,000 m/ft. altitude were performed. Relevant engine development background covering both prior and recent engine test results of the direct injected unthrottled rotary engine technology, including the capability to interchangeably operate on gasoline, diesel fuel, kerosene, or aviation jet fuel, are presented and related to growth predictions. Aircraft studies, using these resultant growth engines, define anticipated system effects of the performance and power density improvements for both single engine and twin engine airplanes. The calculated results indicate superior system performance and 30 to 35% fuel economy improvement for the Rotary-engine airplanes as compared to equivalent airframe concept designs with current baseline engines. The research and technology activities required to attain the projected engine performance levels are also discussed.

Aircraft Flight Modeling During the Optimization of Gas Turbine Engine Working Process

Science.gov (United States)

Tkachenko, A. Yu; Kuz'michev, V. S.; Krupenich, I. N.

2018-01-01

The article describes a method for simulating the flight of the aircraft along a predetermined path, establishing a functional connection between the parameters of the working process of gas turbine engine and the efficiency criteria of the aircraft. This connection is necessary for solving the optimization tasks of the conceptual design stage of the engine according to the systems approach. Engine thrust level, in turn, influences the operation of aircraft, thus making accurate simulation of the aircraft behavior during flight necessary for obtaining the correct solution. The described mathematical model of aircraft flight provides the functional connection between the airframe characteristics, working process of gas turbine engines (propulsion system), ambient and flight conditions and flight profile features. This model provides accurate results of flight simulation and the resulting aircraft efficiency criteria, required for optimization of working process and control function of a gas turbine engine.

QCGAT aircraft/engine design for reduced noise and emissions

Science.gov (United States)

Lanson, L.; Terrill, K. M.

1980-01-01

The high bypass ratio QCGAT engine played an important role in shaping the aircraft design. The aircraft which evolved is a sleek, advanced design, six-place aircraft with 3538 kg (7,800 lb) maximum gross weight. It offers a 2778 kilometer (1500 nautical mile) range with cruise speed of 0.5 Mach number and will take-off and land on the vast majority of general aviation airfields. Advanced features include broad application of composite materials and a supercritical wing design with winglets. Full-span fowler flaps were introduced to improve landing capability. Engines are fuselage-mounted with inlets over the wing to provide shielding of fan noise by the wing surfaces. The design objectives, noise, and emission considerations, engine cycle and engine description are discussed as well as specific design features.

Cycle Counting Methods of the Aircraft Engine

Science.gov (United States)

Fedorchenko, Dmitrii G.; Novikov, Dmitrii K.

2016-01-01

The concept of condition-based gas turbine-powered aircraft operation is realized all over the world, which implementation requires knowledge of the end-of-life information related to components of aircraft engines in service. This research proposes an algorithm for estimating the equivalent cyclical running hours. This article provides analysis…

Missile sizing for ascent-phase intercept

Energy Technology Data Exchange (ETDEWEB)

Hull, D.G. [Univ. of Texas, Austin, TX (United States). Dept. of Aerospace Engineering and Engineering Mechanics; Salguero, D.E. [Sandia National Labs., Albuquerque, NM (United States)

1994-11-01

A computer code has been developed to determine the size of a ground-launched, multistage missile which can intercept a theater ballistic missile before it leaves the atmosphere. Typical final conditions for the inteceptor are 450 km range, 60 km altitude, and 80 sec flight time. Given the payload mass (35 kg), which includes a kinetic kill vehicle, and achievable values for the stage mass fractions (0.85), the stage specific impulses (290 sec), and the vehicle density (60 lb/ft{sup 3}), the launch mass is minimized with respect to the stage payload mass ratios, the stage burn times, and the missile angle of attack history subject to limits on the angle of attack (10 deg), the dynamic pressure (60,000 psf), and the maneuver load (200,000 psf deg). For a conical body, the minimum launch mass is approximately 1900 kg. The missile has three stages, and the payload coasts for 57 sec. A trade study has been performed by varying the flight time, the range, and the dynamic pressure Emits. With the results of a sizing study for a 70 lb payload and q{sub max} = 35,000 psf, a more detailed design has been carried out to determine heat shield mass, tabular aerodynamics, and altitude dependent thrust. The resulting missile has approximately 100 km less range than the sizing program predicted primarily because of the additional mass required for heat protection. On the other hand, launching the same missile from an aircraft increases its range by approximately 100 km. Sizing the interceptor for air launch with the same final conditions as the ground-launched missile reduces its launch mass to approximately 1000 kg.

Impact load time histories for viscoelastic missiles

International Nuclear Information System (INIS)

Stoykovich, M.

1977-01-01

Generation of the impact load time history at the contact point between a viscoelastic missile and its targets is presented. In the past, in the case of aircraft striking containment shell structure, the impact load time history was determined on the basis of actual measurements by subjecting a rigid wall to aircraft crash. The effects of elastic deformation of the target upon the impact load time history is formulated in this paper. The missile is idealized by a linear mass-spring-dashpot combination using viscoelastic models. These models can readily be processed taking into account the elastic as well as inelastic deformations of the missiles. The target is assumed to be either linearly elastic or rigid. In the case of the linearly elastic target, the normal mode theory is used to express the time-dependent displacements of the target which is simulated by lumped masses, elastic properties and dashpots in discrete parts. In the case of Maxwell viscoelastic model, the time-dependent displacements of the missile and the target are given in terms of the unknown impact load time history. This leads to an integral equation which may be solved by Laplace transformation. The normal mode theory is provided. The target structure may be composed of different materials with different components. Concrete and steel structural components have inherently different viscous friction damping properties. Hence, the equivalent modal damping depends on the degree of participation of these components in the modal response. An approximate rule for determining damping in any vibration mode by weighting the damping of each component according to the modal energy stored in each component is considered

Aircraft gas turbine engine vibration diagnostics

OpenAIRE

Stanislav Fábry; Marek Češkovič

2017-01-01

In the Czech and Slovak aviation are in service elderly aircrafts, usually produced in former Soviet Union. Their power units can be operated in more efficient way, in case of using additional diagnostic methods that allow evaluating their health. Vibration diagnostics is one of the methods indicating changes of rotational machine dynamics. Ground tests of aircraft gas turbine engines allow vibration recording and analysis. Results contribute to airworthiness evaluation and making corrections...

Study on afterburner of aircraft engine

Energy Technology Data Exchange (ETDEWEB)

Kashiwagi, T [Ishikawajima-Harima Heavy Industries Co. Ltd., Tokyo (Japan)

1991-07-01

Study on the afterburner for aircraft engines was reported which is used as an optimum means to produce the supersonic capability of military aircrafts. The basic principle and types of the afterburner were outlined, and as the major problem concerning turbofan afterburners, a combustion capacity at low temperature in fan air flow was discussed, in particular, flame stabilization and combustion efficiency. Basic studies were conducted by fuel spray test, combustion stability test, sector model combustion test and numerical analysis of afterburner internal flow. As a result, a mixing spray fuel injection system with injection of a small amount of fuel into flameholder wake resulted in broadening of a combustible region, and an original flameholder combined with a scoop and double gutters caused a high combustion efficiency. The prototype afterburner was developed for F3 turbofan engines in association with Japan Defence Agency, and a combustion efficiency of 74% was obtained in on-engine running test. 4 refs., 14 figs.

Trends in aircraft engines. Trends in aircraft gas turbines and subsonic engines

Energy Technology Data Exchange (ETDEWEB)

Murashima, Kanji

1988-06-10

While the emphasis of commercial, large aircraft engines is placed on low fuel consumption at high subsonic flight and the turbofan engines with high bypass ratio are dominating, high speed turboprop (ATP) of Mach 0.85 class with low fuel consumption are emerging. UHB with bypass ratio of 15 - 20 are planned with expection for application to intermediate size commercial planes. The pressure ratio is continuously rizing for improved cycle efficiency, reaching 35 - 40 in highest cases. Trends in design technique include: Use of computational aerodynamics and application of two-dimensional structural analysis and the digital simulation of engine characteristics. In the field of large, high bypass turbofan, serious competition is seen between GE and PNA at the thrust level of 5 - 60,000 pounds. Several engines for fighting planes have been approved in the type test and accepted as candidates for next generation of fighting planes including Japan. (15 figs, 36 refs)

Confidence estimation in the application of simulation in the development of aircraft self-protection measures

CSIR Research Space (South Africa)

Willers, CJ

2011-04-01

Full Text Available two-colour seekers, some even with imaging sensors. The proliferation of these ManPAD shoulder launched missiles poses a serious threat to military and civilian aircraft. As many as 150 000 of these missiles are available on the black market [2...]. Several attacks on civilian and military aircraft have been recorded in recent times [3]. To counter the infrared missile threat, a variety of coun- termeasures are used, including flares and directed infrared (laser) countermeasures (DIRCM...

Effect of broadened-specification fuels on aircraft engines and fuel systems

Science.gov (United States)

Rudey, R. A.

1979-01-01

A wide variety of studies on the potential effects of broadened-specification fuels on future aircraft engines and fuel systems are summarized. The compositions and characteristics of aircraft fuels that may be derived from current and future crude-oil sources are described, and the most critical properties that may affect aircraft engines and fuel systems are identified and discussed. The problems that are most likely to be encountered because of changes in selected fuel properties are described; and the related effects on engine performance, component durability and maintenance, and aircraft fuel-system performance are discussed. The ability of current technology to accept possible future fuel-specification changes is discussed, and selected technological advances that can reduce the severity of the potential problems are illustrated.

Optimal control in thermal engineering

CERN Document Server

Badescu, Viorel

2017-01-01

This book is the first major work covering applications in thermal engineering and offering a comprehensive introduction to optimal control theory, which has applications in mechanical engineering, particularly aircraft and missile trajectory optimization. The book is organized in three parts: The first part includes a brief presentation of function optimization and variational calculus, while the second part presents a summary of the optimal control theory. Lastly, the third part describes several applications of optimal control theory in solving various thermal engineering problems. These applications are grouped in four sections: heat transfer and thermal energy storage, solar thermal engineering, heat engines and lubrication.Clearly presented and easy-to-use, it is a valuable resource for thermal engineers and thermal-system designers as well as postgraduate students.

Design and test of aircraft engine isolators for reduced interior noise

Science.gov (United States)

Unruh, J. F.; Scheidt, D. C.

1982-01-01

Improved engine vibration isolation was proposed to be the most weight and cost efficient retrofit structure-borne noise control measure for single engine general aviation aircraft. A study was carried out the objectives: (1) to develop an engine isolator design specification for reduced interior noise transmission, (2) select/design candidate isolators to meet a 15 dB noise reduction design goal, and (3) carry out a proof of concept evaluation test. Analytical model of the engine, vibration isolators and engine mount structure were coupled to an empirical model of the fuselage for noise transmission evaluation. The model was used to develop engine isolator dynamic properties design specification for reduced noise transmission. Candidate isolators ere chosen from available product literature and retrofit to a test aircraft. A laboratory based test procedure was then developed to simulate engine induced noise transmission in the aircraft for a proof of concept evaluation test. Three candidate isolator configurations were evaluated for reduced structure-borne noise transmission relative to the original equipment isolators.

DDG-1000 Missile Integration: A Case Study

Science.gov (United States)

2014-03-01

Systems. 14. SUBJECT TERMS Systems Engineering, Integration 15. NUMBER OF PAGES 137 16. PRICE CODE 17. SECURITY CLASSIFICATION OF REPORT...military tasks. These range from detection and engagement of sea- skimming anti-ship cruise missiles to discrimination of a ballistic missile warhead...is affordable, funding is available, market research was conducted, an 32 analysis of alternatives was completed, the JROC is in agreement

Electronic Warfare: Towed Decoys Could Improve Survivability of Current Navy Aircraft

National Research Council Canada - National Science Library

Aiken, Michael

1997-01-01

Traditionally, DOD'S combat aircraft have used on-board electronic warfare devices called jammers for self-protection against radar-controlled weapons, including missiles and anti-aircraft artillery...

Aircraft Turbine Engine Control Research at NASA Glenn Research Center

Science.gov (United States)

Garg, Sanjay

2014-01-01

This lecture will provide an overview of the aircraft turbine engine control research at NASA (National Aeronautics and Space Administration) Glenn Research Center (GRC). A brief introduction to the engine control problem is first provided with a description of the current state-of-the-art control law structure. A historical aspect of engine control development since the 1940s is then provided with a special emphasis on the contributions of GRC. The traditional engine control problem has been to provide a means to safely transition the engine from one steady-state operating point to another based on the pilot throttle inputs. With the increased emphasis on aircraft safety, enhanced performance and affordability, and the need to reduce the environmental impact of aircraft, there are many new challenges being faced by the designers of aircraft propulsion systems. The Controls and Dynamics Branch (CDB) at GRC is leading and participating in various projects in partnership with other organizations within GRC and across NASA, other government agencies, the U.S. aerospace industry, and academia to develop advanced propulsion controls and diagnostics technologies that will help meet the challenging goals of NASA programs under the Aeronautics Research Mission. The second part of the lecture provides an overview of the various CDB technology development activities in aircraft engine control and diagnostics, both current and some accomplished in the recent past. The motivation for each of the research efforts, the research approach, technical challenges and the key progress to date are summarized. The technologies to be discussed include system level engine control concepts, gas path diagnostics, active component control, and distributed engine control architecture. The lecture will end with a futuristic perspective of how the various current technology developments will lead to an Intelligent and Autonomous Propulsion System requiring none to very minimum pilot interface

Effects of towed-decoys against an anti-air missile with a monopulse seeker

OpenAIRE

Yeh, Jia-Hsin

1995-01-01

This thesis evaluates the protection provided by towed decoys deployed by an aircraft during an engagement against an anti-air missile equipped with a monopulse seeker. The research emphasizes the use of passive decoys. Many of the operational parameters required before the deployment of towed-decoy are investigated, including the strength of reflection, the tether length, the direction of release, under different missile incoming directions. This thesis evaluated two reflection cases. One is...

Study of advanced rotary combustion engines for commuter aircraft

Science.gov (United States)

Berkowitz, M.; Jones, C.; Myers, D.

1983-01-01

Performance, weight, size, and maintenance data for advanced rotary aircraft engines suitable for comparative commuter aircraft system evaluation studies of alternate engine candidates are provided. These are turbocharged, turbocompounded, direct injected, stratified charge rotary engines. Hypothetical engines were defined (an RC4-74 at 895 kW and an RC6-87 at 1490 kW) based on the technologies and design approaches used in the highly advanced engine of a study of advanced general aviation rotary engines. The data covers the size range of shaft power from 597 kW (800 hp) to 1865 kW (2500 hp) and is in the form of drawings, tables, curves and written text. These include data on internal geometry and configuration, installation information, turbocharging and turbocompounding arrangements, design features and technologies, engine cooling, fuels, scaling for weight size BSFC and heat rejection for varying horsepower, engine operating and performance data, and TBO and maintenance requirements. The basic combustion system was developed and demonstrated; however the projected power densities and performance efficiencies require increases in engine internal pressures, thermal loading, and rotative speed.

Design and Manufacturing Process for a Ballistic Missile

Directory of Open Access Journals (Sweden)

Zaharia Sebastian Marian

2016-12-01

Full Text Available Designing a ballistic missile flight depends on the mission and the stress to which the missile is subject. Missile’s requests are determined by: the organization of components; flight regime type, engine configuration and aerodynamic performance of the rocket flight. In this paper has been developed a ballistic missile with a smooth fuselage type, 10 control surfaces, 8 directional surfaces for cornering execution, 2 for maneuvers of execution to change the angle of incidence and 4 stabilizers direction. Through the technology of gluing and clamping of the shell and the use of titanium components, mass of ballistic missile presented a significant decrease in weight and a structure with high strength.

Justification of Estimates for Fiscal Year 1984 Submitted to Congress January 1983: Missile Procurement.

Science.gov (United States)

1983-01-01

initial procurement of 224 missiles (RDT&E PE 64314F, 27163F) STINGER - STINOER is a man-portable, shoulder fired , anti-aircraft missile system for...864 and will consist of a prefabricated metal wall and roof panels, steel framing, concrete floor (reinforoed/unreinforced), blast walls, monorail ...HVAC, fire protection system and normal facilities required of a building of this nature/function. Building will be designed to include energy

Aircraft gas turbine engine vibration diagnostics

Directory of Open Access Journals (Sweden)

Stanislav Fábry

2017-11-01

Full Text Available In the Czech and Slovak aviation are in service elderly aircrafts, usually produced in former Soviet Union. Their power units can be operated in more efficient way, in case of using additional diagnostic methods that allow evaluating their health. Vibration diagnostics is one of the methods indicating changes of rotational machine dynamics. Ground tests of aircraft gas turbine engines allow vibration recording and analysis. Results contribute to airworthiness evaluation and making corrections, if needed. Vibration sensors distribution, signal recording and processing are introduced in a paper. Recorded and re-calculated vibration parameters are used in role of health indicators.

Organic positive ions in aircraft gas-turbine engine exhaust

Science.gov (United States)

Sorokin, Andrey; Arnold, Frank

Volatile organic compounds (VOCs) represent a significant fraction of atmospheric aerosol. However the role of organic species emitted by aircraft (as a consequence of the incomplete combustion of fuel in the engine) in nucleation of new volatile particles still remains rather speculative and requires a much more detailed analysis of the underlying mechanisms. Measurements in aircraft exhaust plumes have shown the presence of both different non-methane VOCs (e.g. PartEmis project) and numerous organic cluster ions (MPIK-Heidelberg). However the link between detected organic gas-phase species and measured mass spectrum of cluster ions is uncertain. Unfortunately, up to now there are no models describing the thermodynamics of the formation of primary organic cluster ions in the exhaust of aircraft engines. The aim of this work is to present first results of such a model development. The model includes the block of thermodynamic data based on proton affinities and gas basicities of organic molecules and the block of non-equilibrium kinetics of the cluster ions evolution in the exhaust. The model predicts important features of the measured spectrum of positive ions in the exhaust behind aircraft. It is shown that positive ions emitted by aircraft engines into the atmosphere mostly consist of protonated and hydrated organic cluster ions. The developed model may be explored also in aerosol investigations of the background atmosphere as well as in the analysis of the emission of fine aerosol particles by automobiles.

Proposed Rule and Related Materials for Control of Emissions of Air Pollution From Nonroad Diesel Engines Control of Air Pollution From Aircraft and Aircraft Engines; Proposed Emission Standards and Test Procedures

Science.gov (United States)

EPA is proposing to adopt emission standards and related provisions for aircraft gas turbine engines with rated thrusts greater than 26.7 kilonewtons. These engines are used primarily on commercial passenger and freight aircraft.

Engine-propeller power plant aircraft community noise reduction key methods

Science.gov (United States)

Moshkov P., A.; Samokhin V., F.; Yakovlev A., A.

2018-04-01

Basic methods of aircraft-type flying vehicle engine-propeller power plant noise reduction were considered including single different-structure-and-arrangement propellers and piston engines. On the basis of a semiempirical model the expressions for blade diameter and number effect evaluation upon propeller noise tone components under thrust constancy condition were proposed. Acoustic tests performed at Moscow Aviation institute airfield on the whole qualitatively proved the obtained ratios. As an example of noise and detectability reduction provision a design-and-experimental estimation of propeller diameter effect upon unmanned aircraft audibility boundaries was performed. Future investigation ways were stated to solve a low-noise power plant design problem for light aircraft and unmanned aerial vehicles.

Missile Aerodynamics (Aerodynamique des Missiles)

Science.gov (United States)

1998-11-01

of missiles, and therefore, less money for new developments. New types of international conflicts demand new kinds of missiles and a higher flexibility...us a lower production rate of missiles and, ods, while visualization helps in the development of therefore, less money for new developments. New...du mod~le de turbulence. Plusieurs Lauder [1 ~ 3].maillages distincts ont 6t 6tudi6s. Ils different essentiellement par le nombre de points dans la

Small Engine Technology (SET) Task 24 Business and Regional Aircraft System Studies

Science.gov (United States)

Lieber, Lysbeth

2003-01-01

This final report has been prepared by Honeywell Engines & Systems, Phoenix, Arizona, a unit of Honeywell International Inc., documenting work performed during the period June 1999 through December 1999 for the National Aeronautics and Space Administration (NASA) Glenn Research Center, Cleveland, Ohio, under the Small Engine Technology (SET) Program, Contract No. NAS3-27483, Task Order 24, Business and Regional Aircraft System Studies. The work performed under SET Task 24 consisted of evaluating the noise reduction benefits compared to the baseline noise levels of representative 1992 technology aircraft, obtained by applying different combinations of noise reduction technologies to five business and regional aircraft configurations. This report focuses on the selection of the aircraft configurations and noise reduction technologies, the prediction of noise levels for those aircraft, and the comparison of the noise levels with those of the baseline aircraft.

Take-off engine particle emission indices for in-service aircraft at Los Angeles International Airport

Science.gov (United States)

Moore, Richard H.; Shook, Michael A.; Ziemba, Luke D.; Digangi, Joshua P.; Winstead, Edward L.; Rauch, Bastian; Jurkat, Tina; Thornhill, Kenneth L.; Crosbie, Ewan C.; Robinson, Claire; Shingler, Taylor J.; Anderson, Bruce E.

2017-12-01

We present ground-based, advected aircraft engine emissions from flights taking off at Los Angeles International Airport. 275 discrete engine take-off plumes were observed on 18 and 25 May 2014 at a distance of 400 m downwind of the runway. CO2 measurements are used to convert the aerosol data into plume-average emissions indices that are suitable for modelling aircraft emissions. Total and non-volatile particle number EIs are of order 1016-1017 kg-1 and 1014-1016 kg-1, respectively. Black-carbon-equivalent particle mass EIs vary between 175-941 mg kg-1 (except for the GE GEnx engines at 46 mg kg-1). Aircraft tail numbers recorded for each take-off event are used to incorporate aircraft- and engine-specific parameters into the data set. Data acquisition and processing follow standard methods for quality assurance. A unique aspect of the data set is the mapping of aerosol concentration time series to integrated plume EIs, aircraft and engine specifications, and manufacturer-reported engine emissions certifications. The integrated data enable future studies seeking to understand and model aircraft emissions and their impact on air quality.

Take-off engine particle emission indices for in-service aircraft at Los Angeles International Airport.

Science.gov (United States)

Moore, Richard H; Shook, Michael A; Ziemba, Luke D; DiGangi, Joshua P; Winstead, Edward L; Rauch, Bastian; Jurkat, Tina; Thornhill, Kenneth L; Crosbie, Ewan C; Robinson, Claire; Shingler, Taylor J; Anderson, Bruce E

2017-12-19

We present ground-based, advected aircraft engine emissions from flights taking off at Los Angeles International Airport. 275 discrete engine take-off plumes were observed on 18 and 25 May 2014 at a distance of 400 m downwind of the runway. CO 2 measurements are used to convert the aerosol data into plume-average emissions indices that are suitable for modelling aircraft emissions. Total and non-volatile particle number EIs are of order 10 16 -10 17 kg -1 and 10 14 -10 16 kg -1 , respectively. Black-carbon-equivalent particle mass EIs vary between 175-941 mg kg -1 (except for the GE GEnx engines at 46 mg kg -1 ). Aircraft tail numbers recorded for each take-off event are used to incorporate aircraft- and engine-specific parameters into the data set. Data acquisition and processing follow standard methods for quality assurance. A unique aspect of the data set is the mapping of aerosol concentration time series to integrated plume EIs, aircraft and engine specifications, and manufacturer-reported engine emissions certifications. The integrated data enable future studies seeking to understand and model aircraft emissions and their impact on air quality.

Missile proliferation and missile defense

International Nuclear Information System (INIS)

Zarif, M. Javad

2002-01-01

The global security environment is becoming increasingly volatile and dangerous. A new arms race is looming in the horizon ... [Missiles have] become the strong weapon of the poor and the discriminated against who find themselves vulnerable to outside threat. They believe missiles may prove instrumental in deterring the enemy from beginning a full scale war ... the engagement of all states at the United Nations in the issue of missiles, through the panel of governmental experts, and the new idea of exploring the subject in the Conference on Disarmament do provide a dim light at the end of the tunnel. ... Efforts at non-proliferation of missiles are more likely to succeed when viewed as an integral part of a global and comprehensive negotiation and progress in other areas of disarmament. (author)

Advanced materials for aircraft engine applications. Koku engine yo zairyo no doko

Energy Technology Data Exchange (ETDEWEB)

1994-05-01

The thrust/weight ratio which is thrust per unit weight of engine is a parameter of aircraft engine performance. With a mean material density of 6.6g/cm[sup 3], some of the supersonic plane engines are 7.9 in thrust/weight ratio. Its attaining 20 is predicted by some reports. The turbine inlet temperature is a parameter of engine temperature heightening exceeds 1400[degree]C. Its attaining 2000[degree]C in the 21st century is also predicted by some reports. By dividing the aircraft engine materials into both improvement and innovation material systems, the present paper explained the characteristics and present status of materials, and how to put them in practical use. As an improvement material, titanium alloy, nickel base alloy and resinous composite materials were exhibited with examples of having improved the established material system in performance and cost. Used as a turbine vane member, the nickel base alloy contributes, as a unidirectional coagulation alloy, single crystal alloy and oxide dispersion exciting alloy, to the creep resistance strengthening at high temperatures against the fatigue due to thermal strain. It is also explained how to put TiAl and FRM to practical use. 8 refs., 13 figs., 2 tabs.

Structureborne noise investigations of a twin engine aircraft

Science.gov (United States)

Garrelick, J. M.; Cole, J. E., III; Martini, K.

1986-01-01

The interior noise of aircraft powered by advanced turbo-prop concepts is likely to have nonnegligible contributions from structureborne paths, these paths being those involving propeller loads transmitted to the structures of the lifting surfaces. As a means of examining these paths, structural measurements have been performed on a small twin-engine aircraft, and in addition analytical models of the structure have been developed. In this paper results from both portions of this study are presented.

Chemical composition and photochemical reactivity of exhaust from aircraft turbine engines

Directory of Open Access Journals (Sweden)

C. W. Spicer

1994-08-01

Full Text Available Assessment of the environmental impact of aircraft emissions is required by planners and policy makers. Seveal areas of concern are: 1. exposure of airport workers and urban residents to toxic chemicals emitted when the engines operate at low power (idle and taxi on the ground; 2. contributions to urban photochemical air pollution of aircraft volatile organic and nitrogen oxides emissions from operations around airports; and 3. emissions of nitrogen oxides and particles during high-altitude operation. The environmental impact of chemicals emitted from jet aircraft turbine engines has not been firmly established due to lack of data regarding emission rates and identities of the compounds emitted. This paper describes an experimental study of two different aircraft turbine engines designed to determine detailed organic emissions, as well as emissions of inorganic gases. Emissions were measured at several engine power settings. Measurements were made of detailed organic composition from C1 through C17, CO, CO2, NO, NOx, and polycyclic aromatic hydrocarbons. Measurements were made using a multi-port sampling pro be positioned directly behind the engine in the exhaust exit plane. The emission measurements have been used to determine the organic distribution by carbon number and the distribution by compound class at each engine power level. The sum of the organic species was compared with an independent measurement of total organic carbon to assess the carbon mass balance. A portion of the exhaust was captured and irradiated in outdoor smog chambers to assess the photochemical reactivity of the emissions with respect to ozone formation. The reactivity of emissions from the two engines was apportioned by chemical compound class.

Stratified charge rotary aircraft engine technology enablement program

Science.gov (United States)

Badgley, P. R.; Irion, C. E.; Myers, D. M.

1985-01-01

The multifuel stratified charge rotary engine is discussed. A single rotor, 0.7L/40 cu in displacement, research rig engine was tested. The research rig engine was designed for operation at high speeds and pressures, combustion chamber peak pressure providing margin for speed and load excursions above the design requirement for a high is advanced aircraft engine. It is indicated that the single rotor research rig engine is capable of meeting the established design requirements of 120 kW, 8,000 RPM, 1,379 KPA BMEP. The research rig engine, when fully developed, will be a valuable tool for investigating, advanced and highly advanced technology components, and provide an understanding of the stratified charge rotary engine combustion process.

Aircraft Piston Engine Exhaust Emission Symposium

Science.gov (United States)

1976-01-01

A 2-day symposium on the reduction of exhaust emissions from aircraft piston engines was held on September 14 and 15, 1976, at the Lewis Research Center in Cleveland, Ohio. Papers were presented by both government organizations and the general aviation industry on the status of government contracts, emission measurement problems, data reduction procedures, flight testing, and emission reduction techniques.

Military Tactical Aircraft Engine Noise Matching to Infrared Signatures

Science.gov (United States)

2016-12-16

Jet engine exhaust plumes also exhibit emission and absorption of radiation from their emitted chemical species, occurring at discrete spectra...Modulation,” Naval Postgraduate School MS thesis (1990). [8] Sinha, N., Ungewitter, R. J., Kenzakowski, D. C., and Seiner, J. M., “Gas Turbine Engine Jet...FINAL REPORT Military Tactical Aircraft Engine Noise Matching to Infrared Signatures SERDP Project WP-2404 JANUARY 2016 Dr

A modular ducted rocket missile model for threat and performance assessment

NARCIS (Netherlands)

Mayer, A.E.H.J.; Halswijk, W.H.C.; Komduur, H.J.; Lauzon, M.; Stowe, R.A.

2005-01-01

A model was developed to predict the thrust of throttled ramjet propelled missiles. The model is called DRCORE and fulfils the growing need to predict the performance of air breathing missiles. Each subsystem of the propulsion unit of this model is coded by using engineering formulae and enables the

Optimal Tuner Selection for Kalman-Filter-Based Aircraft Engine Performance Estimation

Science.gov (United States)

Simon, Donald L.; Garg, Sanjay

2011-01-01

An emerging approach in the field of aircraft engine controls and system health management is the inclusion of real-time, onboard models for the inflight estimation of engine performance variations. This technology, typically based on Kalman-filter concepts, enables the estimation of unmeasured engine performance parameters that can be directly utilized by controls, prognostics, and health-management applications. A challenge that complicates this practice is the fact that an aircraft engine s performance is affected by its level of degradation, generally described in terms of unmeasurable health parameters such as efficiencies and flow capacities related to each major engine module. Through Kalman-filter-based estimation techniques, the level of engine performance degradation can be estimated, given that there are at least as many sensors as health parameters to be estimated. However, in an aircraft engine, the number of sensors available is typically less than the number of health parameters, presenting an under-determined estimation problem. A common approach to address this shortcoming is to estimate a subset of the health parameters, referred to as model tuning parameters. The problem/objective is to optimally select the model tuning parameters to minimize Kalman-filterbased estimation error. A tuner selection technique has been developed that specifically addresses the under-determined estimation problem, where there are more unknown parameters than available sensor measurements. A systematic approach is applied to produce a model tuning parameter vector of appropriate dimension to enable estimation by a Kalman filter, while minimizing the estimation error in the parameters of interest. Tuning parameter selection is performed using a multi-variable iterative search routine that seeks to minimize the theoretical mean-squared estimation error of the Kalman filter. This approach can significantly reduce the error in onboard aircraft engine parameter estimation

A Low-Visibility Force Multiplier: Assessing China’s Cruise Missile Ambitions

Science.gov (United States)

2014-04-01

small radar signature, and very low altitude flight profile of cruise missiles stress air defense systems and airborne surveillance and tracking radars...for engines powering longer-range or large payload cruise missiles and requires a range of disciplines in metallurgy, air flow dynamics, heat ...Beijing-Mos- cow fallout, the Chinese persevered and conducted their first successful missile test in November 1960.3 The Soviets provided China with the

Chemical composition and photochemical reactivity of exhaust from aircraft turbine engines

Directory of Open Access Journals (Sweden)

T. F. Lyon

Full Text Available Assessment of the environmental impact of aircraft emissions is required by planners and policy makers. Seveal areas of concern are: 1. exposure of airport workers and urban residents to toxic chemicals emitted when the engines operate at low power (idle and taxi on the ground; 2. contributions to urban photochemical air pollution of aircraft volatile organic and nitrogen oxides emissions from operations around airports; and 3. emissions of nitrogen oxides and particles during high-altitude operation. The environmental impact of chemicals emitted from jet aircraft turbine engines has not been firmly established due to lack of data regarding emission rates and identities of the compounds emitted. This paper describes an experimental study of two different aircraft turbine engines designed to determine detailed organic emissions, as well as emissions of inorganic gases. Emissions were measured at several engine power settings. Measurements were made of detailed organic composition from C₁ through C₁₇, CO, CO₂, NO, NO_x, and polycyclic aromatic hydrocarbons. Measurements were made using a multi-port sampling pro be positioned directly behind the engine in the exhaust exit plane. The emission measurements have been used to determine the organic distribution by carbon number and the distribution by compound class at each engine power level. The sum of the organic species was compared with an independent measurement of total organic carbon to assess the carbon mass balance. A portion of the exhaust was captured and irradiated in outdoor smog chambers to assess the photochemical reactivity of the emissions with respect to ozone formation. The reactivity of emissions from the two engines was apportioned by chemical compound class.

Load-vs.-time functions resulting from the impact of missiles filled with a liquid; Last-Zeit-Funkionen beim Aufprall fluessigkeitsgefuellter Projektile

Energy Technology Data Exchange (ETDEWEB)

Bernhart, D. [Materialpruefungs- und Forschungsanstalt Karlsruhe (Germany)

2007-10-15

Considerations of possible external impacts on nuclear power plants require verification of the safety precautions in place. Especially the impact of large masses, such as a passenger aircraft, is a factor of major importance because of the damage potential it involves. The load impact resulting from an airplane crash was estimated already back in the 1960s. That approach, which was based on the conservation of momentum, was developed further in a modified form over the next few years. Recalculations of impact tests of a Phantom F-4 plane showed excellent agreement. The transferability to large passenger aircraft of this method of calculation has not been investigated so far. For this reason, the Institute for Solid Construction and Building Materials Technology of the University of Karlsruhe carried out small-scale tests with aluminium missiles. The geometry of the missiles and their stiffness distribution along the longitudinal axis were matched to those of a passenger aircraft. In addition, the influence of the speed of the aircraft on the force-vs.-time function, and the influence of various tank filling levels were studied. Another question to be answered is that of the influence of different angles of impact of the missiles. (orig.)

Number and mass analysis of particles emitted by aircraft engine

Directory of Open Access Journals (Sweden)

Jasiński Remigiusz

2017-01-01

Full Text Available Exhaust emissions from aircraft is a complex issue because of the limited possibility of measurements in flight conditions. Most of the studies on this subject were performed on the basis of stationary test. Engine certification data is used to calculate total emissions generated by air transport. However, it doesnt provide any information about the local effects of air traffic. The main threat to local communities is particulate matter emissions, which adversely affects human health. Emissions from air transport affect air quality, particularly in the vicinity of the airports; it also contributes to the greenhouse effect. The article presents the measurement results of the concentration and size distribution of particles emitted during aircraft landing operation. Measurements were carried out during the landings of aircraft at a civilian airport. It was found that a single landing operation causes particle number concentration value increase of several ten-fold in a short period of time. Using aircraft engine certification data, the methodology for determination of the total number of particles emitted during a single landing operation was introduced.

Fractographic Analysis of High-Cycle Fatgue in Aircraft Engines

National Research Council Canada - National Science Library

Shockey, Donald

2000-01-01

.... Fracture surfaces produced under systematically varied cydic load conditions in laboratory specimens of titanium turbine blade alloy were provided to the program by an aircraft engine manufacturer...

Fractographic Analysis of High-Cycle Fatigue in Aircraft Engines

National Research Council Canada - National Science Library

Shockey, Donald

2000-01-01

.... Fracture surfaces produced under systematically varied cyclic load conditions in laboratory specimens of titanium turbine blade alloy were provided to the program by an aircraft engine manufacturer...

77 FR 65823 - Control of Air Pollution From Aircraft and Aircraft Engines; Emission Standards and Test Procedures

Science.gov (United States)

2012-10-31

... ENVIRONMENTAL PROTECTION AGENCY 40 CFR Parts 87 [EPA-HQ-OAR-2010-0687; FRL-9678-1] RIN 2060-AO70 Control of Air Pollution From Aircraft and Aircraft Engines; Emission Standards and Test Procedures Correction In rule document 2012-13828 appearing on pages 36341-36386 in the issue of Monday, June 18, 2012, make the following corrections: Sec. 87.2...

Assessment of Containment Structures Against Missile Impact Threats

Institute of Scientific and Technical Information of China (English)

LI Q M

2006-01-01

In order to ensure the highest safety requirements,nuclear power plant structures (the containment structures,the fuel storages and transportation systems) should be assessed against all possible internal and external impact threats.The internal impact threats include kinetic missiles generated by the failure of high pressure vessels and pipes,the failure of high speed rotating machineries and accidental drops.The external impact threats may come from airborne missiles,aircraft impact,explosion blast and fragments.The impact effects of these threats on concrete and steel structures in a nuclear power plant are discussed.Methods and procedures for the impact assessment of nuclear power plants are introduced.Recent studies on penetration and perforation mechanics as well as progresses on dynamic properties of concrete-like materials are presented to increase the understanding of the impact effects on concrete containment structures.

Perm State University HPC-hardware and software services: capabilities for aircraft engine aeroacoustics problems solving

Science.gov (United States)

Demenev, A. G.

2018-02-01

The present work is devoted to analyze high-performance computing (HPC) infrastructure capabilities for aircraft engine aeroacoustics problems solving at Perm State University. We explore here the ability to develop new computational aeroacoustics methods/solvers for computer-aided engineering (CAE) systems to handle complicated industrial problems of engine noise prediction. Leading aircraft engine engineering company, including “UEC-Aviadvigatel” JSC (our industrial partners in Perm, Russia), require that methods/solvers to optimize geometry of aircraft engine for fan noise reduction. We analysed Perm State University HPC-hardware resources and software services to use efficiently. The performed results demonstrate that Perm State University HPC-infrastructure are mature enough to face out industrial-like problems of development CAE-system with HPC-method and CFD-solvers.

Trend of supersonic aircraft engine. Choonsokukiyo engine no doko

Energy Technology Data Exchange (ETDEWEB)

Yashima, S [Ishikawajima-Harima Heavy Industries, Co. Ltd., Tokyo (Japan)

1994-05-01

The present paper explained the R and D trend of supersonic aircraft engine in Europe, USA and Japan. Taking the high speed flight resistance into consideration, the engine must be characterized by its high exhaust gas speed and high specific thrust (ratio of thrust to the airflow rate) to secure strong thrust by a low airflow rate. Therefore, the turbojet is appropriate. However to reduce the fuel consumption during the cruising flight, the turbofan is normally used with a low by-pass ratio of 0.2 to 0.9. The thrust-to-weight ratio (thrust per unit weight) of low by-pass ratio turbofan engine equipped with afterburner is 7 to 8 in case of stronger thrust than 70kN. Its target value of development is 10. The specific thrust which is a performance parameter of engine exceeds 120s for the fighter engine and is about 30s for the passenger plane engine. The turbine inlet temperature is 2073K at the stage of element research. The overall pressure ratio ranges from 25 to 30. The reheating turbofan engine experimentally built for the research in Japan is 34kN in thrust and 7 in thrust-to-weight ratio. 8 refs., 9 figs.

Aircraft Wing for Over-The-Wing Mounting of Engine Nacelle

Science.gov (United States)

Hahn, Andrew S. (Inventor); Kinney, David J. (Inventor)

2011-01-01

An aircraft wing has an inboard section and an outboard section. The inboard section is attached (i) on one side thereof to the aircraft's fuselage, and (ii) on an opposing side thereof to an inboard side of a turbofan engine nacelle in an over-the-wing mounting position. The outboard section's leading edge has a sweep of at least 20 degrees. The inboard section's leading edge has a sweep between -15 and +15 degrees, and extends from the fuselage to an attachment position on the nacelle that is forward of an index position defined as an imaginary intersection between the sweep of the outboard section's leading edge and the inboard side of the nacelle. In an alternate embodiment, the turbofan engine nacelle is replaced with an open rotor engine nacelle.

Self Diagnostic Accelerometer Ground Testing on a C-17 Aircraft Engine

Science.gov (United States)

Tokars, Roger P.; Lekki, John D.

2013-01-01

The self diagnostic accelerometer (SDA) developed by the NASA Glenn Research Center was tested for the first time in an aircraft engine environment as part of the Vehicle Integrated Propulsion Research (VIPR) program. The VIPR program includes testing multiple critical flight sensor technologies. One such sensor, the accelerometer, measures vibrations to detect faults in the engine. In order to rely upon the accelerometer, the health of the accelerometer must be ensured. Sensor system malfunction is a significant contributor to propulsion in flight shutdowns (IFSD) which can lead to aircraft accidents when the issue is compounded with an inappropriate crew response. The development of the SDA is important for both reducing the IFSD rate, and hence reducing the rate at which this component failure type can put an aircraft in jeopardy, and also as a critical enabling technology for future automated malfunction diagnostic systems. The SDA is a sensor system designed to actively determine the accelerometer structural health and attachment condition, in addition to making vibration measurements. The SDA uses a signal conditioning unit that sends an electrical chirp to the accelerometer and recognizes changes in the response due to changes in the accelerometer health and attachment condition. In an effort toward demonstrating the SDAs flight worthiness and robustness, multiple SDAs were mounted and tested on a C-17 aircraft engine. The engine test conditions varied from engine off, to idle, to maximum power. The two SDA attachment conditions used were fully tight and loose. The newly developed SDA health algorithm described herein uses cross correlation pattern recognition to discriminate a healthy from a faulty SDA. The VIPR test results demonstrate for the first time the robustness of the SDA in an engine environment characterized by high vibration levels.

The influence of engine/transmission/governor on tilting proprotor aircraft dynamics

Science.gov (United States)

Johnson, W.

1975-01-01

An analytical model is developed for the dynamics of a tilting proprotor aircraft engine and drive train, including a rotor speed governor and interconnect shaft. The dynamic stability of a proprotor and cantilever wing is calculated, including the engine-transmission-governor model. It is concluded that the rotor behaves much as if windmilling as far as its dynamic behavior is concerned, with some influence of the turboshaft engine inertia and damping. The interconnect shaft has a significant influence on the antisymmetric dynamics of proprotor aircraft. The proprotor aerodynamics model is extended to include reverse flow, and a refinement on the method used to calculate the kinematic pitch-bending coupling of the blade is developed.

Extractive sampling and optical remote sensing of F100 aircraft engine emissions.

Science.gov (United States)

Cowen, Kenneth; Goodwin, Bradley; Joseph, Darrell; Tefend, Matthew; Satola, Jan; Kagann, Robert; Hashmonay, Ram; Spicer, Chester; Holdren, Michael; Mayfield, Howard

2009-05-01

The Strategic Environmental Research and Development Program (SERDP) has initiated several programs to develop and evaluate techniques to characterize emissions from military aircraft to meet increasingly stringent regulatory requirements. This paper describes the results of a recent field study using extractive and optical remote sensing (ORS) techniques to measure emissions from six F-15 fighter aircraft. Testing was performed between November 14 and 16, 2006 on the trim-pad facility at Tyndall Air Force Base in Panama City, FL. Measurements were made on eight different F100 engines, and the engines were tested on-wing of in-use aircraft. A total of 39 test runs were performed at engine power levels that ranged from idle to military power. The approach adopted for these tests involved extractive sampling with collocated ORS measurements at a distance of approximately 20-25 nozzle diameters downstream of the engine exit plane. The emission indices calculated for carbon dioxide, carbon monoxide, nitric oxide, and several volatile organic compounds showed very good agreement when comparing the extractive and ORS sampling methods.

The Effect of Modified Control Limits on the Performance of a Generic Commercial Aircraft Engine

Science.gov (United States)

Csank, Jeffrey T.; May, Ryan D.; Gou, Ten-Huei; Litt, Jonathan S.

2012-01-01

This paper studies the effect of modifying the control limits of an aircraft engine to obtain additional performance. In an emergency situation, the ability to operate an engine above its normal operating limits and thereby gain additional performance may aid in the recovery of a distressed aircraft. However, the modification of an engine s limits is complex due to the risk of an engine failure. This paper focuses on the tradeoff between enhanced performance and risk of either incurring a mechanical engine failure or compromising engine operability. The ultimate goal is to increase the engine performance, without a large increase in risk of an engine failure, in order to increase the probability of recovering the distressed aircraft. The control limit modifications proposed are to extend the rotor speeds, temperatures, and pressures to allow more thrust to be produced by the engine, or to increase the rotor accelerations and allow the engine to follow a fast transient. These modifications do result in increased performance; however this study indicates that these modifications also lead to an increased risk of engine failure.

Sliding Mode Fault Tolerant Control with Adaptive Diagnosis for Aircraft Engines

Science.gov (United States)

Xiao, Lingfei; Du, Yanbin; Hu, Jixiang; Jiang, Bin

2018-03-01

In this paper, a novel sliding mode fault tolerant control method is presented for aircraft engine systems with uncertainties and disturbances on the basis of adaptive diagnostic observer. By taking both sensors faults and actuators faults into account, the general model of aircraft engine control systems which is subjected to uncertainties and disturbances, is considered. Then, the corresponding augmented dynamic model is established in order to facilitate the fault diagnosis and fault tolerant controller design. Next, a suitable detection observer is designed to detect the faults effectively. Through creating an adaptive diagnostic observer and based on sliding mode strategy, the sliding mode fault tolerant controller is constructed. Robust stabilization is discussed and the closed-loop system can be stabilized robustly. It is also proven that the adaptive diagnostic observer output errors and the estimations of faults converge to a set exponentially, and the converge rate greater than some value which can be adjusted by choosing designable parameters properly. The simulation on a twin-shaft aircraft engine verifies the applicability of the proposed fault tolerant control method.

Space and Missile Systems Center Standard: Systems Engineering Requirements and Products

Science.gov (United States)

2013-07-01

MISSILE SYSTEMS CENTER Air Force Space Command 483 N. Aviation Blvd. El Segundo, CA 90245 4. This standard has been approved for use on all Space...Any RF receiver with a burnout level of less than 30 dBm (1 mW). b. A summary of all significant areas are addressed in the EMC Control Plan...address 7. Date Submitted 8. Preparing Activity Space and Missile Systems Center AIR FORCE SPACE COMMAND 483 N. Aviation Blvd. El Segundo, CA 91245 Attention: SMC/EN February 2013

77 FR 39623 - Airworthiness Standards: Aircraft Engines; Technical Amendment

Science.gov (United States)

2012-07-05

...: AIRCRAFT ENGINES 0 1. The authority citation for part 33 continues to read as follows: Authority: 49 U.S.C..., analysis, and component test. * * * * * Issued in Washington, DC, on June 7, 2012. Lirio Liu, Acting...

REQUIREMENT VERIFICATION AND SYSTEMS ENGINEERING TECHNICAL REVIEW (SETR) ON A COMMERCIAL DERIVATIVE AIRCRAFT (CDA) PROGRAM

Science.gov (United States)

2017-09-01

VERIFICATION AND SYSTEMS ENGINEERING TECHNICAL REVIEW (SETR) ON A COMMERCIAL DERIVATIVE AIRCRAFT (CDA) PROGRAM by Theresa L. Thomas September... ENGINEERING TECHNICAL REVIEW (SETR) ON A COMMERCIAL DERIVATIVE AIRCRAFT (CDA) PROGRAM 5. FUNDING NUMBERS 6. AUTHOR(S) Theresa L. Thomas 7...CODE 13. ABSTRACT (maximum 200 words) The Naval Air Systems Command (NAVAIR) systems engineering technical review (SETR) process does not

Multi-Objective Climb Path Optimization for Aircraft/Engine Integration Using Particle Swarm Optimization

Directory of Open Access Journals (Sweden)

Aristeidis Antonakis

2017-04-01

Full Text Available In this article, a new multi-objective approach to the aircraft climb path optimization problem, based on the Particle Swarm Optimization algorithm, is introduced to be used for aircraft–engine integration studies. This considers a combination of a simulation with a traditional Energy approach, which incorporates, among others, the use of a proposed path-tracking scheme for guidance in the Altitude–Mach plane. The adoption of population-based solver serves to simplify case setup, allowing for direct interfaces between the optimizer and aircraft/engine performance codes. A two-level optimization scheme is employed and is shown to improve search performance compared to the basic PSO algorithm. The effectiveness of the proposed methodology is demonstrated in a hypothetic engine upgrade scenario for the F-4 aircraft considering the replacement of the aircraft’s J79 engine with the EJ200; a clear advantage of the EJ200-equipped configuration is unveiled, resulting, on average, in 15% faster climbs with 20% less fuel.

Accurate Measurements of Aircraft Engine Soot Emissions Using a CAPS PMssa Monitor

Science.gov (United States)

Onasch, Timothy; Thompson, Kevin; Renbaum-Wolff, Lindsay; Smallwood, Greg; Make-Lye, Richard; Freedman, Andrew

2016-04-01

We present results of aircraft engine soot emissions measurements during the VARIAnT2 campaign using CAPS PMssa monitors. VARIAnT2, an aircraft engine non-volatile particulate matter (nvPM) emissions field campaign, was focused on understanding the variability in nvPM mass measurements using different measurement techniques and accounting for possible nvPM sampling system losses. The CAPS PMssa monitor accurately measures both the optical extinction and scattering (and thus single scattering albedo and absorption) of an extracted sample using the same sample volume for both measurements with a time resolution of 1 second and sensitivity of better than 1 Mm-1. Absorption is obtained by subtracting the scattering signal from the total extinction. Given that the single scattering albedo of the particulates emitted from the aircraft engine measured at both 630 and 660 nm was on the order of 0.1, any inaccuracy in the scattering measurement has little impact on the accuracy of the ddetermined absorption coefficient. The absorption is converted into nvPM mass using a documented Mass Absorption Coefficient (MAC). Results of soot emission indices (mass soot emitted per mass of fuel consumed) for a turbojet engine as a function of engine power will be presented and compared to results obtained using an EC/OC monitor.

Roles, uses, and benefits of general aviation aircraft in aerospace engineering education

Science.gov (United States)

Odonoghue, Dennis P.; Mcknight, Robert C.

1994-01-01

Many colleges and universities throughout the United States offer outstanding programs in aerospace engineering. In addition to the fundamentals of aerodynamics, propulsion, flight dynamics, and air vehicle design, many of the best programs have in the past provided students the opportunity to design and fly airborne experiments on board various types of aircraft. Sadly, however, the number of institutions offering such 'airborne laboratories' has dwindled in recent years. As a result, opportunities for students to apply their classroom knowledge, analytical skills, and engineering judgement to the development and management of flight experiments on an actual aircraft are indeed rare. One major reason for the elimination of flight programs by some institutions, particularly the smaller colleges, is the prohibitive cost of operating and maintaining an aircraft as a flying laboratory. The purpose of this paper is to discuss simple, low-cost, relevant flight experiments that can be performed using readily available general aviation aircraft. This paper examines flight experiments that have been successfully conducted on board the NASA Lewis Research Center's T-34B aircraft, as part of the NASA/AIAA/University Flight Experiment Program for Students (NAUFEPS) and discusses how similar experiments could be inexpensively performed on other general aviation aircraft.

Missile Defense: Ballistic Missile Defense System Testing Delays Affect Delivery of Capabilities

Science.gov (United States)

2016-04-28

Page 1 GAO-16-339R Ballistic Missile Defense 441 G St. N.W. Washington, DC 20548 April 28, 2016 Congressional Committees Missile Defense... Ballistic Missile Defense System Testing Delays Affect Delivery of Capabilities For over half a century, the Department of Defense (DOD) has been...funding efforts to develop a system to detect, track, and defeat enemy ballistic missiles. The current system—the Ballistic Missile Defense System

Turboelectric Distributed Propulsion Engine Cycle Analysis for Hybrid-Wing-Body Aircraft

Science.gov (United States)

Felder, James L.; Kim, Hyun Dae; Brown, Gerald V.

2009-01-01

Meeting NASA's N+3 goals requires a fundamental shift in approach to aircraft and engine design. Material and design improvements allow higher pressure and higher temperature core engines which improve the thermal efficiency. Propulsive efficiency, the other half of the overall efficiency equation, however, is largely determined by the fan pressure ratio (FPR). Lower FPR increases propulsive efficiency, but also dramatically reduces fan shaft speed through the combination of larger diameter fans and reduced fan tip speed limits. The result is that below an FPR of 1.5 the maximum fan shaft speed makes direct drive turbines problematic. However, it is the low pressure ratio fans that allow the improvement in propulsive efficiency which, along with improvements in thermal efficiency in the core, contributes strongly to meeting the N+3 goals for fuel burn reduction. The lower fan exhaust velocities resulting from lower FPRs are also key to meeting the aircraft noise goals. Adding a gear box to the standard turbofan engine allows acceptable turbine speeds to be maintained. However, development of a 50,000+ hp gearbox required by fans in a large twin engine transport aircraft presents an extreme technical challenge, therefore another approach is needed. This paper presents a propulsion system which transmits power from the turbine to the fan electrically rather than mechanically. Recent and anticipated advances in high temperature superconducting generators, motors, and power lines offer the possibility that such devices can be used to transmit turbine power in aircraft without an excessive weight penalty. Moving to such a power transmission system does more than provide better matching between fan and turbine shaft speeds. The relative ease with which electrical power can be distributed throughout the aircraft opens up numerous other possibilities for new aircraft and propulsion configurations and modes of operation. This paper discusses a number of these new

Numerical methods for engine-airframe integration

International Nuclear Information System (INIS)

Murthy, S.N.B.; Paynter, G.C.

1986-01-01

Various papers on numerical methods for engine-airframe integration are presented. The individual topics considered include: scientific computing environment for the 1980s, overview of prediction of complex turbulent flows, numerical solutions of the compressible Navier-Stokes equations, elements of computational engine/airframe integrations, computational requirements for efficient engine installation, application of CAE and CFD techniques to complete tactical missile design, CFD applications to engine/airframe integration, and application of a second-generation low-order panel methods to powerplant installation studies. Also addressed are: three-dimensional flow analysis of turboprop inlet and nacelle configurations, application of computational methods to the design of large turbofan engine nacelles, comparison of full potential and Euler solution algorithms for aeropropulsive flow field computations, subsonic/transonic, supersonic nozzle flows and nozzle integration, subsonic/transonic prediction capabilities for nozzle/afterbody configurations, three-dimensional viscous design methodology of supersonic inlet systems for advanced technology aircraft, and a user's technology assessment

Damage Propagation Modeling for Aircraft Engine Run-to-Failure Simulation

Data.gov (United States)

National Aeronautics and Space Administration — This paper describes how damage propagation can be modeled within the modules of aircraft gas turbine engines. To that end, response surfaces of all sensors are...

Sonic IR crack detection of aircraft turbine engine blades with multi-frequency ultrasound excitations

International Nuclear Information System (INIS)

Zhang, Ding; Han, Xiaoyan; Newaz, Golam

2014-01-01

Effectively and accurately detecting cracks or defects in critical engine components, such as turbine engine blades, is very important for aircraft safety. Sonic Infrared (IR) Imaging is such a technology with great potential for these applications. This technology combines ultrasound excitation and IR imaging to identify cracks and flaws in targets. In general, failure of engine components, such as blades, begins with tiny cracks. Since the attenuation of the ultrasound wave propagation in turbine engine blades is small, the efficiency of crack detection in turbine engine blades can be quite high. The authors at Wayne State University have been developing the technology as a reliable tool for the future field use in aircraft engines and engine parts. One part of the development is to use finite element modeling to assist our understanding of effects of different parameters on crack heating while experimentally hard to achieve. The development has been focused with single frequency ultrasound excitation and some results have been presented in a previous conference. We are currently working on multi-frequency excitation models. The study will provide results and insights of the efficiency of different frequency excitation sources to foster the development of the technology for crack detection in aircraft engine components

75 FR 22439 - Advance Notice of Proposed Rulemaking on Lead Emissions From Piston-Engine Aircraft Using Leaded...

Science.gov (United States)

2010-04-28

... piston-engine aircraft as well as certain high performance engines such as race cars. \\33\\ See http://www... for all remaining uses, including use as fuel in aircraft, racing cars, and nonroad engines such as.... These include the voluntary partnership between EPA and the National Association for Stock Car Auto...

The High Level Mathematical Models in Calculating Aircraft Gas Turbine Engine Parameters

Directory of Open Access Journals (Sweden)

Yu. A. Ezrokhi

2017-01-01

Full Text Available The article describes high-level mathematical models developed to solve special problems arising at later stages of design with regard to calculation of the aircraft gas turbine engine (GTE under real operating conditions. The use of blade row mathematics models, as well as mathematical models of a higher level, including 2D and 3D description of the working process in the engine units and components, makes it possible to determine parameters and characteristics of the aircraft engine under conditions significantly different from the calculated ones.The paper considers application of mathematical modelling methods (MMM for solving a wide range of practical problems, such as forcing the engine by injection of water into the flowing part, estimate of the thermal instability effect on the GTE characteristics, simulation of engine start-up and windmill starting condition, etc. It shows that the MMM use, when optimizing the laws of the compressor stator control, as well as supplying cooling air to the hot turbine components in the motor system, can significantly improve the integral traction and economic characteristics of the engine in terms of its gas-dynamic stability, reliability and resource.It ought to bear in mind that blade row mathematical models of the engine are designed to solve purely "motor" problems and do not replace the existing models of various complexity levels used in calculation and design of compressors and turbines, because in “quality” a description of the working processes in these units is inevitably inferior to such specialized models.It is shown that the choice of the mathematical modelling level of an aircraft engine for solving a particular problem arising in its designing and computational study is to a large extent a compromise problem. Despite the significantly higher "resolution" and information ability the motor mathematical models containing 2D and 3D approaches to the calculation of flow in blade machine

Numerical study of influence of biofuels on the combustion characteristics and performance of aircraft engine system

International Nuclear Information System (INIS)

Zhou, Li; Liu, Zeng-wen; Wang, Zhan-xue

2015-01-01

The atomization and combustion flowfield of the combustion chamber with swirl-nozzle were simulated using different biofuels; the thermodynamic cycle of the aircraft engine system were also analyzed, influences of biofuels on the combustion characteristics and performance of aircraft engine system were explored. Results show that viscosity and caloric value are key factors affecting the atomization and combustion characteristics of biofuels, and then dominate the distribution of the temperature and NO concentration. Due to the characteristic of low viscosity and low caloric value for biofuels adopted, the biofuels accumulate near the head of combustion chamber, and the corresponding NO emission is lower than that it has for conventional kerosene. When biofuels with low caloric value are used under the operation condition which is same as the condition for the conventional kerosene, lower turbine inlet temperature, lower thrust and higher specific fuel consumption would be achieved for the aircraft engine. - Highlights: • Influences of biofuels properties on combustion characteristic are explored. • Effects of biofuels on cycle parameters of aircraft engine are discussed. • Viscosity and caloric value are key factors affecting combustion of biofuels. • NO emission becomes lower when biofuels with low caloric value is adopted. • The performance of aircraft engine becomes worse for biofuels with low caloric value.

Leakage Account for Radial Face Contact Seal in Aircraft Engine Support

Science.gov (United States)

Vinogradov, A. S.; Sergeeva, T. V.

2018-01-01

The article is dedicated to the development of a methodology for the radial face contact seal design taking into consideration the supporting elements deformations in different aircraft engine operating modes. Radial face contact seals are popular in the aircraft engines bearing support. However, there are no published leakage calculation methodologies of these seals. Radial face contact seal leakage is determined by the gap clearance in the carbon seal ring split. In turn, the size gap clearance depends on the deformation of the seal assembly parts and from the engine operation. The article shows the leakage detection sequence in the intershaft radial face contact seal of the compressor support for take-off and cruising modes. Evaluated calculated leakage values (2.4 g/s at takeoff and 0.75 g/s at cruising) go with experience in designing seals.

NATO Pallet with Javelin Missiles, MIL-STD-1660 Tests

National Research Council Canada - National Science Library

2004-01-01

The U.S. Army Defense Ammunition Center (DAC), Validation Engineering Division (SJMAC-DEV) conducted tests in accordance with MIL-STD-1660, "Design Criteria for Ammunition Unit Loads" on the NATO pallet with Javelin missiles...

Causes and risk factors for fatal accidents in non-commercial twin engine piston general aviation aircraft.

Science.gov (United States)

Boyd, Douglas D

2015-04-01

Accidents in twin-engine aircraft carry a higher risk of fatality compared with single engine aircraft and constitute 9% of all general aviation accidents. The different flight profile (higher airspeed, service ceiling, increased fuel load, and aircraft yaw in engine failure) may make comparable studies on single-engine aircraft accident causes less relevant. The objective of this study was to identify the accident causes for non-commercial operations in twin engine aircraft. A NTSB accident database query for accidents in twin piston engine airplanes of 4-8 seat capacity with a maximum certified weight of 3000-8000lbs. operating under 14CFR Part 91 for the period spanning 2002 and 2012 returned 376 accidents. Accident causes and contributing factors were as per the NTSB final report categories. Total annual flight hour data for the twin engine piston aircraft fleet were obtained from the FAA. Statistical analyses employed Chi Square, Fisher's Exact and logistic regression analysis. Neither the combined fatal/non-fatal accident nor the fatal accident rate declined over the period spanning 2002-2012. Under visual weather conditions, the largest number, n=27, (27%) of fatal accidents was attributed to malfunction with a failure to follow single engine procedures representing the most common contributing factor. In degraded visibility, poor instrument approach procedures resulted in the greatest proportion of fatal crashes. Encountering thunderstorms was the most lethal of all accident causes with all occupants sustaining fatal injuries. At night, a failure to maintain obstacle/terrain clearance was the most common accident cause leading to 36% of fatal crashes. The results of logistic regression showed that operations at night (OR 3.7), off airport landings (OR 14.8) and post-impact fire (OR 7.2) all carried an excess risk of a fatal flight. This study indicates training areas that should receive increased emphasis for twin-engine training/recency. First, increased

Aircraft Maintenance Engineering: Factors Impacting Airlines E-Maintenance Technologies, Authoring and Illustrations

Science.gov (United States)

Karayianes, Frank

The purpose of this research was to evaluate factors influencing acceptance and use of technologies in the field of aircraft maintenance authoring, graphics, and documentation. Maintenance engineering authors convert complex engineering used in aircraft production and transform that data using technology (tools) into usable technical publications data. While the current literature includes a large volume of research in technology acceptance in various domains of industry and business, the problem is that no such studies exist with respect to the aircraft maintenance engineering authoring, allowing any number of tools to be used and acceptance to be unsure. The study was based on theoretical approaches of the Technology Acceptance Model and the associated hypothesis related to eight research questions. A survey questionnaire was developed for data collection from a selected population of aircraft maintenance engineering authors. Data collected from 148 responses were exposed to a range of statistical methods and analyses. Analysis of data were performed within the structural equation model using exploratory factor analysis, confirmatory factor analysis, and a range of regression methods. The analyses generally provided results consistent with prior literature. Two survey questions yielded unexpected results contrary to similar studies. The relationship between prior experience and job level did not show a significant relationship with perceived usefulness or perceived ease of use. Other results included the significant relationship between Perceived Usefulness and Perceived Ease of Use with Technology acceptance. Recommendations include understanding how Technology Acceptance can be improved for the industry and the need for further research not covered to refine recommendations for technology acceptance related to the aviation industry.

Final Rule for Control of Air Pollution from Aircraft and Aircraft Engines: Emission Standards and Test Procedures

Science.gov (United States)

EPA is amending the existing emission standards for oxides of nitrogen (NOx) for new commercial aircraft engines. These standards are equivalent to the NOx emission standards of the United Nations International Civil Aviation Organization (ICAO).

Annual Systems Engineering Conference (9th): Focusing on Improving Performance of Defense Systems Programs. Volume 3. Wednesday

Science.gov (United States)

2006-10-26

Bubble and Requirements Management by Mr. Jimmy Thai Cost Efficient Risk Management Through Integrated T&E Throughout the Systems Engineering Life-Cycle...ACSG/ Miller Seven Steps of an Effective Lessons Learned Process by Mr. Jimmy Thai Lessons Learned from a Mature DMSMS Program by SQNLDR P.D.Weeding...Aircraft AAR-47 Missile Warning System (MWS) GTRI_B-9 Lessons Learned with System Integration - 9 Theatre Airborne Reconnaissance System (TARS

Assessment of Turbulence-Chemistry Interactions in Missile Exhaust Plume Signature Analysis

National Research Council Canada - National Science Library

Calhoon, W

2002-01-01

... components and missile defense systems. Current engineering level models neglect turbulence chemistry interactions and typically underpredict the intensity of plume afterburning and afterburning burnout...

Combustion Dynamics and Control for Ultra Low Emissions in Aircraft Gas-Turbine Engines

Science.gov (United States)

DeLaat, John C.

2011-01-01

Future aircraft engines must provide ultra-low emissions and high efficiency at low cost while maintaining the reliability and operability of present day engines. The demands for increased performance and decreased emissions have resulted in advanced combustor designs that are critically dependent on efficient fuel/air mixing and lean operation. However, all combustors, but most notably lean-burning low-emissions combustors, are susceptible to combustion instabilities. These instabilities are typically caused by the interaction of the fluctuating heat release of the combustion process with naturally occurring acoustic resonances. These interactions can produce large pressure oscillations within the combustor and can reduce component life and potentially lead to premature mechanical failures. Active Combustion Control which consists of feedback-based control of the fuel-air mixing process can provide an approach to achieving acceptable combustor dynamic behavior while minimizing emissions, and thus can provide flexibility during the combustor design process. The NASA Glenn Active Combustion Control Technology activity aims to demonstrate active control in a realistic environment relevant to aircraft engines by providing experiments tied to aircraft gas turbine combustors. The intent is to allow the technology maturity of active combustion control to advance to eventual demonstration in an engine environment. Work at NASA Glenn has shown that active combustion control, utilizing advanced algorithms working through high frequency fuel actuation, can effectively suppress instabilities in a combustor which emulates the instabilities found in an aircraft gas turbine engine. Current efforts are aimed at extending these active control technologies to advanced ultra-low-emissions combustors such as those employing multi-point lean direct injection.

Wind tunnel investigation of an STOL aircraft model. STOL zenki mokei-fudo shiken. ; Engine nacelle keijo koka

Energy Technology Data Exchange (ETDEWEB)

1993-01-01

The nacelle shape of a mimic engine mounted on the wind tunnel test model for an STOL aircraft developed by the National Aerospace Laboratory has much larger length than in the nacelle of a scale reduced to 8% of an actual engine, and the shape below the nacelle is different. Therefore, in order to estimate the air force in the actual aircraft from the aerodynamic data obtained in a wind tunnel test, the data are corrected by using differences in aerodynamic loads (estimated values) applied on the mimic engine and the actual engine. For the purpose of discussing the reasonability of this correction, an 8%-scale flow through nacelle with the same shape as in the actual aircraft (the actual aircraft type) and a flow through nacelle for a wind tunnel testing model of the experimental STOL aircraft were fabricated and wind tunnel tests were performed. These results were compared with the corrected results of the mimic engine wind tunnel test. As a result, it was made clear that the force data have been corrected excessively, and the moments have been corrected considerably well. 7 refs., 32 figs., 7 tabs.

Hazards from aircraft

International Nuclear Information System (INIS)

Grund, J.E.; Hornyik, K.

1975-01-01

The siting of nuclear power plants has created innumerable environmental concerns. Among the effects of the ''man-made environment'' one of increasing importance in recent nuclear plant siting hazards analysis has been the concern about aircraft hazards to the nuclear plant. These hazards are of concern because of the possibility that an aircraft may have a malfunction and crash either near the plant or directly into it. Such a crash could be postulated to result, because of missile and/or fire effects, in radioactive releases which would endanger the public health and safety. The majority of studies related to hazards from air traffic have been concerned with the determination of the probability associated with an aircraft striking vulnerable portions of a given plant. Other studies have focused on the structural response to such a strike. This work focuses on the problem of strike probability. 13 references

Advanced liquid-cooled, turbocharged and intercooled stratified charge rotary engines for aircraft

Science.gov (United States)

Mount, Robert E.; Bartel, John; Hady, William F.

1987-01-01

Developments concerning stratified-charge rotary (SCR) engines over the past 10 years are reviewed. Aircraft engines being developed using SCR technology are shown and described, and the ability of such technology to meet general aviation engine needs is considered. Production timing and availability of SCR technology for the development of aviation rotary engines are discussed, and continuing efforts toward improving this technology, including NASA efforts, are described.

Cobalt: A vital element in the aircraft engine industry

Science.gov (United States)

Stephens, J. R.

1981-01-01

Recent trends in the United States consumption of cobalt indicate that superalloys for aircraft engine manufacture require increasing amounts of this strategic element. Superalloys consume a lion's share of total U.S. cobalt usage which was about 16 million pounds in 1980. In excess of 90 percent of the cobalt used in this country was imported, principally from the African countries of Zaire and Zambia. Early studies on the roles of cobalt as an alloying element in high temperature alloys concentrated on the simple Ni-Cr and Nimonic alloy series. The role of cobalt in current complex nickel base superalloys is not well defined and indeed, the need for the high concentration of cobalt in widely used nickel base superalloys is not firmly established. The current cobalt situation is reviewed as it applies to superalloys and the opportunities for research to reduce the consumption of cobalt in the aircraft engine industry are described.

Pollution reduction technology program for small jet aircraft engines: Class T1

Science.gov (United States)

Bruce, T. W.; Davis, F. G.; Mongia, H. C.

1977-01-01

Small jet aircraft engines (EPA class T1, turbojet and turbofan engines of less than 35.6 kN thrust) were evaluated with the objective of attaining emissions reduction consistent with performance constraints. Configurations employing the technological advances were screened and developed through full scale rig testing. The most promising approaches in full-scale engine testing were evaluated.

Local impact effects on concrete target due to missile: An empirical and numerical approach

International Nuclear Information System (INIS)

Ranjan, Rajiv; Banerjee, Sauvik; Singh, R.K.; Banerji, Pradipta

2014-01-01

Highlights: • Local impact effect of hard missile on reinforced concrete targets has been studied. • Review of empirical formulation for predicting local response carried out. • Numerical simulation of experimental test of Kojima (1991) carried out. • Divergence of FE results with those obtained using emperical formulations. • Close match of numerical simulation results with experimental data. - Abstract: Concrete containment walls and internal concrete barrier walls of a Nuclear Power Plant safety related structures are often required to be designed for externally and internally generated missiles. Potential missiles include external extreme wind generated missiles, aircraft crash and internal accident generated missiles such as impact due to turbine blade failure and steel pipe missiles resulting from pipe break. The objective of the present paper is to compare local missile impact effects on reinforced concrete target using available empirical formulations with those obtained using LS-DYNA numerical simulation. The use of numerical simulations for capturing the transient structural response has become increasingly used for structural design against impact loads. They overcome the limits of applicability of the empirical formulae and also provide information on stress and deformation fields, which may be used to improve the resistance of the concrete. Finite element (FE) analyses of an experimental impact problem reported by Kojima (1991) are carried out that are able to capture the missile impact effects; in terms of local and global damage. The continuous surface cap model has been used for modelling concrete behaviour. A range of missile velocity has been considered to simulate local missile impact phenomenon and modes of failure and to capture the concrete response from elastic to plastic fracture. A comparison is then made between the empirical formulations, numerical simulation results, and available experimental results of slab impact tests

Missile proliferation and missile defence

International Nuclear Information System (INIS)

Marin-Bosch, Miguel

2002-01-01

Nothing should serve to justify the acquisition and development of ballistic missiles. The solution to this problem is similar to that of all weapons of mass destruction, including nuclear weapons, i.e., a total ban of their use, testing, manufacture and development. Unfortunately, given the present international climate, ballistic missiles will continue to be an important component of the arsenals of several countries for years to come. ...what you invent today to enhance your security has a tendency to reappear later elsewhere as a threat. (author)

Aircraft Engine Technology for Green Aviation to Reduce Fuel Burn

Science.gov (United States)

Hughes, Christopher E.; VanZante, Dale E.; Heidmann, James D.

2013-01-01

The NASA Fundamental Aeronautics Program Subsonic Fixed Wing Project and Integrated Systems Research Program Environmentally Responsible Aviation Project in the Aeronautics Research Mission Directorate are conducting research on advanced aircraft technology to address the environmental goals of reducing fuel burn, noise and NOx emissions for aircraft in 2020 and beyond. Both Projects, in collaborative partnerships with U.S. Industry, Academia, and other Government Agencies, have made significant progress toward reaching the N+2 (2020) and N+3 (beyond 2025) installed fuel burn goals by fundamental aircraft engine technology development, subscale component experimental investigations, full scale integrated systems validation testing, and development validation of state of the art computation design and analysis codes. Specific areas of propulsion technology research are discussed and progress to date.

Lightweight two-stroke cycle aircraft diesel engine technology enablement program, volume 2

Science.gov (United States)

Freen, P. D.; Berenyi, S. G.; Brouwers, A. P.; Moynihan, M. E.

1985-01-01

An experimental Single Cylinder Test Engine Program is conducted to confirm the analytically projected performance of a two-stroke cycle diesel engine for aircraft applications. Testing confirms the ability of a proposed 4-cylinder version of such an engine to reach the target power at altitude in a highly turbocharged configuration. The experimental program defines all necessary parameters to permit a design of a multicylinder engine for eventual flight applications.

Aircraft crash upon a containment structure of a nuclear power plant

International Nuclear Information System (INIS)

Paul, D.K.; Abbas, H.; Godbole, P.N.; Nayak, G.C.

1993-01-01

The reinforced concrete outer containment of a Nuclear Power Plant (NPP) is required to be designed to withstand the impact of aircraft and aircrash debris etc. The problem is of strategic significance because the damage caused to the structure by these missiles may lead to the leakage of nuclear radiations. The safety design of NPP against aircraft crash requires the evaluation of crash probability. If the probability is smaller than the allowable value then the aircraft crash is neglected as design basis item. Otherwise adequate measures are taken to bring the released radioactive material within the permissible limit. The aircrafts and their striking velocity to be considered in the design of a structure are decided by the accident analysis. The probabilistic aspect of the problem has not been covered in the present work. The non-affordability of coupled analysis of large problems like aircraft crash on NPP, automobile impact on a structure etc. due to the requirement of excessive amount of manual as well as computer time and storage compels us to switch over to the uncoupled analysis. Moreover, the results of coupled analysis are heavily influenced by the analyst's modelling technique and choice of increment size. It is uncoupling of the missile and the target which converts the impact load to the impulse load. This impulse can be found by taking into consideration only the inertial and stiffness properties of missile and considering the target to be rigid. Though the impulse load so obtained disregards the inertial and stiffness characteristics of the target but its effect can be incorporated by modifying it for the inertial and stiffness properties of target at different time steps as we march in time domain during the analysis of the target

76 FR 72087 - Special Conditions: Diamond Aircraft Industries, Model DA-40NG; Electronic Engine Control (EEC...

Science.gov (United States)

2011-11-22

...; Special Conditions No. 23-253-SC] Special Conditions: Diamond Aircraft Industries, Model DA-40NG..., Model DA-40NG airplane. This airplane will have a novel or unusual design feature(s) associated with an... include the new model DA- 40NG with the Austro Engine GmbH model E4 Aircraft Diesel Engine (ADE). The...

Future-proofing an aircraft self-protection IR signature database

CSIR Research Space (South Africa)

Alayeda, M

2012-09-01

Full Text Available Aircraft self-protection against heat seeking missile threats is an extremely important topic worldwide, recently even more so with the instability in the Middle East region due to, for example, the large number of man-portable air defense systems...

Teaching Risk Analysis in an Aircraft Gas Turbine Engine Design Capstone Course

Science.gov (United States)

2016-01-01

support the required performance specifications (Brandt, 2004) ( Raymer , 1989). There is no specific step to treat a selected design performance...a Design Perspective, 2nd ed.: AIAA Education Series, 2004. Raymer , Daniel P. 1989. Aircraft Design: A Conceptual Approach.: AIAA Educational...Mattingly, Jack D., Heiser, William H., Pratt, David T. 2002. Aircraft Engine Design, 2nd ed.: AIAA Education Series, 2002. Drews, Robert W. 2006. The

Exergetic analysis of an aircraft turbojet engine with an afterburner

OpenAIRE

Ehyaei M.A.; Anjiridezfuli A.; Rosen M.A.

2013-01-01

An exergy analysis is reported of a J85-GE-21 turbojet engine and its components for two altitudes: sea level and 11,000 meters. The turbojet engine with afterburning operates on the Brayton cycle and includes six main parts: diffuser, compressor, combustion chamber, turbine, afterburner and nozzle. Aircraft data are utilized in the analysis with simulation data. The highest component exergy efficiency at sea level is observed to be for the compressor, at 9...

Curved electromagnetic missiles

International Nuclear Information System (INIS)

Myers, J.M.; Shen, H.M.; Wu, T.T.

1989-01-01

Transient electromagnetic fields can exhibit interesting behavior in the limit of great distances from their sources. In situations of finite total radiated energy, the energy reaching a distant receiver can decrease with distance much more slowly than the usual r - 2 . Cases of such slow decrease have been referred to as electromagnetic missiles. All of the wide variety of known missiles propagate in essentially straight lines. A sketch is presented here of a missile that can follow a path that is strongly curved. An example of a curved electromagnetic missile is explicitly constructed and some of its properties are discussed. References to details available elsewhere are given

Aircraft Gas Turbine Engine Health Monitoring System by Real Flight Data

Directory of Open Access Journals (Sweden)

Mustagime Tülin Yildirim

2018-01-01

Full Text Available Modern condition monitoring-based methods are used to reduce maintenance costs, increase aircraft safety, and reduce fuel consumption. In the literature, parameters such as engine fan speeds, vibration, oil pressure, oil temperature, exhaust gas temperature (EGT, and fuel flow are used to determine performance deterioration in gas turbine engines. In this study, a new model was developed to get information about the gas turbine engine’s condition. For this model, multiple regression analysis was carried out to determine the effect of the flight parameters on the EGT parameter and the artificial neural network (ANN method was used in the identification of EGT parameter. At the end of the study, a network that predicts the EGT parameter with the smallest margin of error has been developed. An interface for instant monitoring of the status of the aircraft engine has been designed in MATLAB Simulink. Any performance degradation that may occur in the aircraft’s gas turbine engine can be easily detected graphically or by the engine performance deterioration value. Also, it has been indicated that it could be a new indicator that informs the pilots in the event of a fault in the sensor of the EGT parameter that they monitor while flying.

How will the Indian military's upgrade and modernization of its ISR, precision strike, and missile defense affect the stability in South Asia?

OpenAIRE

Dewan, Jay P.

2005-01-01

Approved for public release, distribution is unlimited India has made a concerted effort to upgrade its ISR, precision strike, and missile defense capabilities as it competes with China and Pakistan for regional power. The Phalcon Airborne Warning and Control System, Su-30MKI fighter-bomber aircraft, and S-300PMU surface-to-air missile system are some examples of the new capabilities India is acquiring. I argue that if India continues its military modernization, Pakistan will become more i...

Aircraft Engine Noise Research and Testing at the NASA Glenn Research Center

Science.gov (United States)

Elliott, Dave

2015-01-01

The presentation will begin with a brief introduction to the NASA Glenn Research Center as well as an overview of how aircraft engine noise research fits within the organization. Some of the NASA programs and projects with noise content will be covered along with the associated goals of aircraft noise reduction. Topics covered within the noise research being presented will include noise prediction versus experimental results, along with engine fan, jet, and core noise. Details of the acoustic research conducted at NASA Glenn will include the test facilities available, recent test hardware, and data acquisition and analysis methods. Lastly some of the actual noise reduction methods investigated along with their results will be shown.

Aircraft and ancillary materials. 2. ; Engine materials. Kokuki to sono shuhen zairyo. 2. ; Engine zairyo

Energy Technology Data Exchange (ETDEWEB)

1993-04-05

This paper summarizes materials for aircraft engines. Jet engines are the mainstream today, which are classified according to their operation process into a turbo jet engine, a turbo prop engine, a turbo shaft engine, and a turbo fan engine. Japan has produced 1543 engines in the past decade, almost all of which are supplied to the Defense Agency. Jet engines use mainly Ni-group heat-resistant alloys, titanium alloys and steels. Improvement of engine efficiency has caused turbine inlet temperatures to rise to 1400[degree]C to 1500[degree]C that give rise to grain boundary cracking. To prevent this, discussions are in progress on monocrystal blades replacing the conventional polycrystal precision casts. Intermetallic compounds including Al/Ti are expected especially of use as jet engine constructing materials from their high melting point and formability. Discussions are preceding on ceramics as to coating them intended of improving heat resistance. Composite materials have a problem of insufficient mechanical strength remaining unsolved. 8 figs., 5 tabs.

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.

Engine jet entrainment in the near field of an aircraft

Energy Technology Data Exchange (ETDEWEB)

Garnier, F.; Jacquin, L.; Laverdant, A. [Office National d`Etudes et de Recherches Aerospatiales (ONERA), 92 - Chatillon (France)

1997-12-31

A simplified approach has been applied to analyse the mixing and entrainment processes of the engine exhaust through their interaction with the vortex wake of an aircraft. These investigations are focused on the near filed, extending from exit nozzle to the beginning of the vortex phase (i.e. to about twenty seconds after the wake is generated). This study is performed using an integral model and a numerical simulation for a two-engine large civil aircraft. The properties of the wing-tip vortices on the calculation of the dilution ratio (defined as a tracer concentration) have been shown. The mixing process is also affected by the buoyancy effect, but only after the jet regime, when the trapping in the vortex core has occurred. Qualitative comparison with contrail photography shows similar features. Finally the distortion and stretching of the plume streamlines inside the vortices can be observed, and the role of the descent of the vortices on the maximum tracer concentration has been discussed. (author) 19 refs.

Engine jet entrainment in the near field of an aircraft

Energy Technology Data Exchange (ETDEWEB)

Garnier, F; Jacquin, L; Laverdant, A [Office National d` Etudes et de Recherches Aerospatiales (ONERA), 92 - Chatillon (France)

1998-12-31

A simplified approach has been applied to analyse the mixing and entrainment processes of the engine exhaust through their interaction with the vortex wake of an aircraft. These investigations are focused on the near filed, extending from exit nozzle to the beginning of the vortex phase (i.e. to about twenty seconds after the wake is generated). This study is performed using an integral model and a numerical simulation for a two-engine large civil aircraft. The properties of the wing-tip vortices on the calculation of the dilution ratio (defined as a tracer concentration) have been shown. The mixing process is also affected by the buoyancy effect, but only after the jet regime, when the trapping in the vortex core has occurred. Qualitative comparison with contrail photography shows similar features. Finally the distortion and stretching of the plume streamlines inside the vortices can be observed, and the role of the descent of the vortices on the maximum tracer concentration has been discussed. (author) 19 refs.

Impact of future fuel properties on aircraft engines and fuel systems

Science.gov (United States)

Rudey, R. A.; Grobman, J. S.

1978-01-01

From current projections of the availability of high-quality petroleum crude oils, it is becoming increasingly apparent that the specifications for hydrocarbon jet fuels may have to be modified. The problems that are most likely to be encountered as a result of these modifications relate to engine performance, component durability and maintenance, and aircraft fuel-system performance. The effect on engine performance will be associated with changes in specific fuel consumption, ignition at relight limits, at exhaust emissions. Durability and maintenance will be affected by increases in combustor liner temperatures, carbon deposition, gum formation in fuel nozzles, and erosion and corrosion of turbine blades and vanes. Aircraft fuel-system performance will be affected by increased deposits in fuel-system heat exchangers and changes in the pumpability and flowability of the fuel. The severity of the potential problems is described in terms of the fuel characteristics most likely to change in the future. Recent data that evaluate the ability of current-technology aircraft to accept fuel specification changes are presented, and selected technological advances that can reduce the severity of the problems are described and discussed.

Reducing Conservatism in Aircraft Engine Response Using Conditionally Active Min-Max Limit Regulators

Science.gov (United States)

May, Ryan D.; Garg, Sanjay

2012-01-01

Current aircraft engine control logic uses a Min-Max control selection structure to prevent the engine from exceeding any safety or operational limits during transients due to throttle commands. This structure is inherently conservative and produces transient responses that are slower than necessary. In order to utilize the existing safety margins more effectively, a modification to this architecture is proposed, referred to as a Conditionally Active (CA) limit regulator. This concept uses the existing Min-Max architecture with the modification that limit regulators are active only when the operating point is close to a particular limit. This paper explores the use of CA limit regulators using a publicly available commercial aircraft engine simulation. The improvement in thrust response while maintaining all necessary safety limits is demonstrated in a number of cases.

Characteristics of tornado generated missiles

International Nuclear Information System (INIS)

Bhattacharyya, A.K.; Boritz, R.C.; Niyogi, P.K.

1975-10-01

The development of techniques designed to calculate tornado missile velocities is traced. It is shown that there is a need for a consistent method for obtaining missile velocities for a variety of tornado parameters. A consistent method for determination of trajectories and velocities of missiles generated by a tornado is described. The effects of plant layout upon missile impact velocity at a given building are discussed from the point of view of determining the necessary missile barrier characteristics. 19 references

76 FR 55293 - Special Conditions: Diamond Aircraft Industries, Model DA-40NG; Electronic Engine Control (EEC...

Science.gov (United States)

2011-09-07

... with an electronic engine control (EEC), also known as a Full Authority Digital Engine Control (FADEC... engine design certification, and the certification requirements for engine control systems are driven by... aircraft supplied power and data failures on the engine control system, and the resulting effects on engine...

Analysis of aircraft impact to concrete structures

International Nuclear Information System (INIS)

Arros, Jorma; Doumbalski, Nikolay

2007-01-01

Analysis of aircraft impact to nuclear power plant structures is discussed utilizing a simplified model of a 'fictitious nuclear building' to perform analyses using LS-DYNA software, representing the loading: (i) by the Riera force history method and (ii) by modeling the crash by impacting a model of a plane similar to Boeing 747-400 to the structure (i.e., 'missile-target interaction method'). Points discussed include: (1) comparison of shock loading within the building as obtained from the Riera force history analysis versus from the missile-target interaction analysis, (2) sensitivity of the results on the assumed Riera force loading area, (3) linear versus nonlinear modeling and (4) on failure criteria

Optimal Tuner Selection for Kalman Filter-Based Aircraft Engine Performance Estimation

Science.gov (United States)

Simon, Donald L.; Garg, Sanjay

2010-01-01

A linear point design methodology for minimizing the error in on-line Kalman filter-based aircraft engine performance estimation applications is presented. This technique specifically addresses the underdetermined estimation problem, where there are more unknown parameters than available sensor measurements. A systematic approach is applied to produce a model tuning parameter vector of appropriate dimension to enable estimation by a Kalman filter, while minimizing the estimation error in the parameters of interest. Tuning parameter selection is performed using a multi-variable iterative search routine which seeks to minimize the theoretical mean-squared estimation error. This paper derives theoretical Kalman filter estimation error bias and variance values at steady-state operating conditions, and presents the tuner selection routine applied to minimize these values. Results from the application of the technique to an aircraft engine simulation are presented and compared to the conventional approach of tuner selection. Experimental simulation results are found to be in agreement with theoretical predictions. The new methodology is shown to yield a significant improvement in on-line engine performance estimation accuracy

Electronic Warfare and Radar Systems Engineering Handbook. 4th Edition

Science.gov (United States)

2013-10-01

Instantaneous Frequency Measurement IFR Instrument Flight Rules IG Inspector General IIR Imaging Infrared I-Level Intermediate Level of Repair (also...Review TS Top Secret TSS Tangential Sensitivity TSSAM Tri-Service Standoff Attack Weapon TT Target Track TTI Time To Impact /Intercept TTG Time-to-Go...missile time-of-flight, i.e. A missile shot at a target 36 NM away, may be only 12 NM away from the firing aircraft at missile impact . 4-8.5

Computational modelling of an Organic Rankine Cycle (ORC waste heat recovery system for an aircraft engine

Directory of Open Access Journals (Sweden)

Saadon S.

2018-01-01

Full Text Available Escalating fuel prices and carbon dioxide emission are causing new interest in methods to increase the thrust force of an aircraft engine with limitation of fuel consumption. One viable means is the conversion of exhaust engine waste heat to a more useful form of energy or to be used in the aircraft environmental system. A one-dimensional analysis method has been proposed for the organic Rankine cycle (ORC waste heat recovery system for turbofan engine in this paper. The paper contains two main parts: validation of the numerical model and a performance prediction of turbofan engine integrated to an ORC system. The cycle is compared with industrial waste heat recovery system from Hangzhou Chinen Steam Turbine Power CO., Ltd. The results show that thrust specific fuel consumption (TSFC of the turbofan engine reach lowest value at 0.91 lbm/lbf.h for 7000 lbf of thrust force. When the system installation weight is applied, the system results in a 2.0% reduction in fuel burn. Hence implementation of ORC system for waste heat recovery to an aircraft engine can bring a great potential to the aviation industry.

A Novel Modeling Method for Aircraft Engine Using Nonlinear Autoregressive Exogenous (NARX) Models Based on Wavelet Neural Networks

Science.gov (United States)

Yu, Bing; Shu, Wenjun; Cao, Can

2018-05-01

A novel modeling method for aircraft engine using nonlinear autoregressive exogenous (NARX) models based on wavelet neural networks is proposed. The identification principle and process based on wavelet neural networks are studied, and the modeling scheme based on NARX is proposed. Then, the time series data sets from three types of aircraft engines are utilized to build the corresponding NARX models, and these NARX models are validated by the simulation. The results show that all the best NARX models can capture the original aircraft engine's dynamic characteristic well with the high accuracy. For every type of engine, the relative identification errors of its best NARX model and the component level model are no more than 3.5 % and most of them are within 1 %.

Ballistic missile defense effectiveness

Science.gov (United States)

Lewis, George N.

2017-11-01

The potential effectiveness of ballistic missile defenses today remains a subject of debate. After a brief discussion of terminal and boost phase defenses, this chapter will focus on long-range midcourse defenses. The problems posed by potential countermeasures to such midcourse defenses are discussed as are the sensor capabilities a defense might have available to attempt to discriminate the actual missile warhead in a countermeasures environment. The role of flight testing in assessing ballistic missile defense effectiveness is discussed. Arguments made about effectiveness by missile defense supporters and critics are summarized.

Study of LH2-fueled topping cycle engine for aircraft propulsion

Science.gov (United States)

Turney, G. E.; Fishbach, L. H.

1983-01-01

An analytical investigation was made of a topping cycle aircraft engine system which uses a cryogenic fuel. This system consists of a main turboshaft engine which is mechanically coupled (by cross-shafting) to a topping loop which augments the shaft power output of the system. The thermodynamic performance of the topping cycle engine was analyzed and compared with that of a reference (conventional-type) turboshaft engine. For the cycle operating conditions selected, the performance of the topping cycle engine in terms of brake specific fuel consumption (bsfc) was determined to be about 12 percent better than that of the reference turboshaft engine. Engine weights were estimated for both the topping cycle engine and the reference turboshaft engine. These estimates were based on a common shaft power output for each engine. Results indicate that the weight of the topping cycle engine is comparable to that of the reference turboshaft engine.

The development of turbojet aircraft in Germany, Britain, and the United States: A multi-national comparison of aeronautical engineering, 1935--1946

Science.gov (United States)

Pavelec, Sterling Michael

In the 1930s aeronautical engineering needed revision. A presumptive anomaly was envisaged as piston-engine aircraft flew higher and faster. Radical alternatives to piston engines were considered in the unending quest for speed. Concurrently, but unwittingly, two turbojet engine programs were undertaken in Europe. The air-breathing three-stage turbojet engine was based on previous turbine technology; the revolutionary idea was the gas turbine as a prime mover for aircraft. In Germany, Dr. Hans von Ohain was the first to complete a flight-worthy turbojet engine for aircraft. Installed in a Heinkel designed aircraft, the Germans began the jet age on 27 August 1939. The Germans led throughout the war and were the first to produce jet aircraft for combat operations. The principal limiting factor for the German jet program was a lack of reliable engines. The continuing myths that Hitler orders, too little fuel, or too few pilots hindered the program are false. In England, Frank Whittle, without substantial support, but with dogged determination, also developed a turbojet engine. The British came second in the jet race when the Whittle engine powered the Gloster Pioneer on 15 May 1941. The Whittle-Gloster relationship continued and produced the only Allied combat jet aircraft during the war, the Meteor, which was confined to Home Defense in Britain. The American turbojet program was built directly from the Whittle engine. General Electric copied the Whittle designs and Bell Aircraft was contracted to build the first American jet plane. The Americans began the jet age on 1 October 1942 with a lackluster performance from their first jet, the Airacomet. But the Americans forged ahead, and had numerous engine and airframe programs in development by the end of the war. But, the Germans did it right and did it first. Partly because of a predisposition towards excellent engineering and physics, partly out of necessity, the Germans were able to produce combat turbojet aircraft

Development of Demonstrably Predictive Models for Emissions from Alternative Fuels Based Aircraft Engines

Science.gov (United States)

2017-05-01

Engineering Chemistry Fundamentals, Vol. 5, No. 3, 1966, pp. 356–363. [14] Burns, R. A., Development of scalar and velocity imaging diagnostics...in an Aero- Engine Model Combustor at Elevated Pressure Using URANS and Finite- Rate Chemistry ,” 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference...FINAL REPORT Development of Demonstrably Predictive Models for Emissions from Alternative Fuels Based Aircraft Engines SERDP Project WP-2151

76 FR 17757 - Airworthiness Directives; Thielert Aircraft Engines GmbH Models TAE 125-01, TAE 125-02-99, and...

Science.gov (United States)

2011-03-31

... Airworthiness Directives; Thielert Aircraft Engines GmbH Models TAE 125-01, TAE 125-02-99, and TAE 125-02-114.... Applicability (c) This AD applies to Thielert Aircraft Engines GmbH models TAE 125-01, TAE 125-02-99, and TAE...) For TAE 125-02-99 and TAE 125-02-114 engines, Operation & Maintenance Manual OM-02-02, Version 2...

Charging process analysis of an opposed-piston two-stroke aircraft Diesel engine

Directory of Open Access Journals (Sweden)

Grabowski Łukasz

2017-01-01

Full Text Available This paper presents the research results on a 1D model of an opposed-piston two-stroke aircraft Diesel engine. The research aimed at creating a model of the engine in question to investigate how engine performance is affected by the compressor gear ratio. The power was constant at all the operating points. The research results are presented as graphs of power consumed by the compressor, compressor efficiency and brake specific fuel consumption. The optimal range of compressor gear ratio in terms of engine efficiency was defined from the research results.

Embedded Systems - Missile Detection/Interception

Directory of Open Access Journals (Sweden)

Luis Cintron

2010-01-01

Full Text Available Missile defense systems are often related to major military resources aimed at shielding a specific region from incoming attacks. They are intended to detect, track, intercept, and destruct incoming enemy missiles. These systems vary in cost, efficiency, dependability, and technology. In present times, the possession of these types of systems is associated with large capacity military countries. Demonstrated here are the mathematical techniques behind missile systems which calculate trajectories of incoming missiles and potential intercept positions after initial missile detection. This procedure involved the use of vector-valued functions, systems of equations, and knowledge of projectile motion concepts.

A Hybrid PCA-CART-MARS-Based Prognostic Approach of the Remaining Useful Life for Aircraft Engines

Directory of Open Access Journals (Sweden)

Fernando Sánchez Lasheras

2015-03-01

Full Text Available Prognostics is an engineering discipline that predicts the future health of a system. In this research work, a data-driven approach for prognostics is proposed. Indeed, the present paper describes a data-driven hybrid model for the successful prediction of the remaining useful life of aircraft engines. The approach combines the multivariate adaptive regression splines (MARS technique with the principal component analysis (PCA, dendrograms and classification and regression trees (CARTs. Elements extracted from sensor signals are used to train this hybrid model, representing different levels of health for aircraft engines. In this way, this hybrid algorithm is used to predict the trends of these elements. Based on this fitting, one can determine the future health state of a system and estimate its remaining useful life (RUL with accuracy. To evaluate the proposed approach, a test was carried out using aircraft engine signals collected from physical sensors (temperature, pressure, speed, fuel flow, etc.. Simulation results show that the PCA-CART-MARS-based approach can forecast faults long before they occur and can predict the RUL. The proposed hybrid model presents as its main advantage the fact that it does not require information about the previous operation states of the input variables of the engine. The performance of this model was compared with those obtained by other benchmark models (multivariate linear regression and artificial neural networks also applied in recent years for the modeling of remaining useful life. Therefore, the PCA-CART-MARS-based approach is very promising in the field of prognostics of the RUL for aircraft engines.

The Apache Longbow-Hellfire Missile Test at Yuma Proving Ground: Introduction and Problem Formulation for a Multiple Stressor Risk Assessment

International Nuclear Information System (INIS)

Efroymson, Rebecca Ann; Peterson, Mark J.; Jones, Daniel Steven; Suter, Glenn

2008-01-01

An ecological risk assessment was conducted at Yuma Proving Ground, Arizona, as a demonstration of the Military Ecological Risk Assessment Framework (MERAF). The focus of the assessment was a testing program at Cibola Range, which involved an Apache Longbow helicopter firing Hellfire missiles at moving targets, i.e., M60-A1 tanks. The problem formulation for the assessment included conceptual models for three component activities of the test, helicopter overflight, missile firing, and tracked vehicle movement, and two ecological endpoint entities, woody desert wash communities and desert mule deer (Odocoileus hemionus crooki) populations. An activity-specific risk assessment framework was available to provide guidance for assessing risks associated with aircraft overflights. Key environmental features of the study area include barren desert pavement and tree-lined desert washes. The primary stressors associated with helicopter overflights were sound and the view of the aircraft. The primary stressor associated with Hellfire missile firing was sound. The principal stressor associated with tracked vehicle movement was soil disturbance, and a resulting, secondary stressor was hydrological change. Water loss to washes and wash vegetation was expected to result from increased ponding, infiltration and/or evaporation associated with disturbances to desert pavement. A plan for estimating integrated risks from the three military activities was included in the problem formulation

Exergetic analysis of an aircraft turbojet engine with an afterburner

Directory of Open Access Journals (Sweden)

Ehyaei M.A.

2013-01-01

Full Text Available An exergy analysis is reported of a J85-GE-21 turbojet engine and its components for two altitudes: sea level and 11,000 meters. The turbojet engine with afterburning operates on the Brayton cycle and includes six main parts: diffuser, compressor, combustion chamber, turbine, afterburner and nozzle. Aircraft data are utilized in the analysis with simulation data. The highest component exergy efficiency at sea level is observed to be for the compressor, at 96.7%, followed by the nozzle and turbine with exergy efficiencies of 93.7 and 92.3%, respectively. At both considered heights, reducing of engine intake air speed leads to a reduction in the exergy efficiencies of all engine components and overall engine. The exergy efficiency of the turbojet engine is found to decrease by 0.45% for every 1°C increase in inlet air temperature.

Aircraft Engine Life-Consumption Monitoring for Real-Time Reliability Determination, Phase II

Data.gov (United States)

National Aeronautics and Space Administration — The object of this research is to develop an in-service life-monitor system for the prediction of the remaining component and system life of aircraft engines. The...

Floor Response Evaluation for Auxiliary Building Subjected to Aircraft Impact Loading

International Nuclear Information System (INIS)

Shin, Sang Shup; Hahm, Daegi; Choi, Inkil

2014-01-01

These studies have been aimed to verify and ensure the safety of the targeted walls and structures especially in the viewpoint of the deterministic approach. However, a probabilistic safety assessment as well as deterministic approach for the damage of the internal component in the nuclear power plants (NPPs) subjected to aircraft crash is also needed. A probabilistic safety assessment for aircraft crash includes many uncertainties such as impact velocity, mass, impact location, shape, size, material etc. of aircraft. In this paper, an impact location was selected among the various parameters. This paper found the acceleration floor response spectra at specified locations (safety related components) on the target structure that assumed to be impact velocity 150m/s and maximum fuel for the specified aircraft model. In order to obtain the floor response in case of the crash with a various locations, the analyses for the auxiliary building subjected to aircraft impact were performed using Riera force history method and missile-target interaction method. The difference between responses in case of the building floor subjected to impact was occurred. Thus, in order to obtain the more accurate results, missile-target interaction method was used. This paper found the response at the selected point (node point No. 51). In order to probabilistic assessment for the safety related components, the assessment for a various parameters (velocity, mass, materials etc.) as well as impact locations should be needed

Flowfield and Radiation Analysis of Missile Exhaust Plumes Using a Turbulent-Chemistry Interaction Model

National Research Council Canada - National Science Library

Calhoon, W. H; Kenzakowski, D. C

2000-01-01

... components and missile defense systems. Current engineering level models neglect turbulent-chemistry interactions and typically underpredict the intensity of plume afterburning and afterburning burnout...

Failure Investigation of WB-57 Aircraft Engine Cowling

Science.gov (United States)

Martinez, J. E.; Gafka, T.; Figert, J.

2014-01-01

The NASA Johnson Space Center (JSC) in Houston, Texas is the home of the NASA WB-57 High Altitude Research Program. Three fully operational WB-57 aircraft are based near JSC at Ellington Field. The aircraft have been flying research missions since the early 1960's, and continue to be an asset to the scientific community with professional, reliable, customer-oriented service designed to meet all scientific objectives. The NASA WB-57 Program provides unique, high-altitude airborne platforms to US Government agencies, academic institutions, and commercial customers in order to support scientific research and advanced technology development and testing at locations around the world. Mission examples include atmospheric and earth science, ground mapping, cosmic dust collection, rocket launch support, and test bed operations for future airborne or spaceborne systems. During the return from a 6 hour flight, at 30,000 feet, in the clean configuration, traveling at 175 knots indicated airspeed, in un-accelerated flight with the auto pilot engaged, in calm air, the 2-man crew heard a mechanical bang and felt a slight shudder followed by a few seconds of high frequency vibration. The crew did not notice any other abnormalities leading up to, or for the remaining 1 hour of flight and made an uneventful landing. Upon taxi into the chocks, the recovery ground crew noticed the high frequency long wire antenna had become disconnected from the vertical stabilizer and was trailing over the left inboard wing, and that the left engine upper center removable cowling panel was missing, with noticeable damage to the left engine inboard cowling fixed structure. The missing cowling panel was never recovered. Each engine cowling panel is attached to the engine nacelle using six bushings made of 17-4 PH steel. The cylinder portions of four of the six bushings were found still attached to the aircraft (Fig 1). The other two bushings were lost with the panel. The other four bushings exhibited

Supercharging system behavior for high altitude operation of an aircraft 2-stroke Diesel engine

International Nuclear Information System (INIS)

Carlucci, Antonio Paolo; Ficarella, Antonio; Laforgia, Domenico; Renna, Alessandro

2015-01-01

Highlights: • Different supercharging architectures have been compared for an aircraft 2T engine. • The supercharging architectures are compared to minimize the fuel consumption. • The architecture with the highest conversion efficiency was determined. - Abstract: Different studies on both 2- and 4-stroke engines have shown how the choice of different supercharging architectures can influence engine performance. Among them, architectures coupling one turbocharger with a mechanical compressor or two turbochargers are found to be the most performing in terms of engine output power and efficiency. However, defining the best supercharging architecture for aircraft 2-stroke engines is a quite complex task because the supercharging system as well as the ambient conditions influence the engine performance/efficiency. This is due to the close interaction between supercharging, trapping, scavenging and combustion processes. The aim of the present work is the comparison between different architectures (single turbocharger, double turbocharger, single turbocharger combined with a mechanical compressor, single turbocharger with an electrically-assisted turbocharger, with intercooler or aftercooler) designed to supercharge an aircraft 2-stroke Diesel engine for general aviation and unmanned aerial vehicles characterized by a very high altitude operation and long fuel distance. A 1D model of the engine purposely designed has been used to compare the performance of the different supercharging systems in terms of power, fuel consumption, and their effect on trapping and scavenging efficiency at different altitudes. The analysis shows that the engine target power is reached by a 2 turbochargers architecture; in this way, in fact, the cylinder filling, and consequently the engine performance, are maximized. Moreover, it is shown that the performance of a 2 turbochargers architecture performance can be further improved connecting electrically and not mechanically the low

Protivoklopni vođeni projektili zapadne Evrope, Izraela i Indije / Anti-tank guided missiles of western Europe, Israel and India

Directory of Open Access Journals (Sweden)

Goran M. Lazić

2010-10-01

Full Text Available Protivoklopni vođeni projektili namenjeni su za uništavanje teško-oklopljenih tenkova, kao i drugih oklopnih vozila. Ovaj rad nudi istorijsko-tehnički pregled (razvoj projektila kroz generacije i osnovni podaci vezani za borbeno-operativno dejstvo ovih projektila ovog tipa naoružanja koje poseduju zemlje zapadne Evrope, Izraela i Indije. Pored osnovnih podataka navode se i cene nekih projektila ponaosob, kao i tendencije razvoja u ovoj grani naoružanja. / Anti-tank guided missiles are designed to hit and destroy heavily armored tanks and other armored fighting vehicles. This review offers a historical and technical overview (development of missiles throughout generations and basic data about combat and operational actions of this type of weapons in Western Europe, Israel and India. The review also offers prices of some missiles and tendencies of development in this branch. Anti-tank guided missiles are primarily designed to destroy armoured tanks as well as other armoured vehicles. Anti-tank guided systems differ in size, from small ones (shoulder-launched missile weapons carried by a single person to complex weapon systems (crewserved, vehicle-mounted and airborne systems. The first generation of anti-tank guided missiles is a manually guided MCLOS (Manual Command to Line of Sight projectile requiring an operator to guide and steer it to a target by a joystick. Vickers vigilant is a British anti-tank wire-guided missile, produced in 1956. The Bantam (Bofors Anti-Tank Missile or Robot 53 (RB 53 is a Swedish anti-tank wire-guided missile, produced in 1963. Cobra is a German - Swiss product which entered the operational use in 1956. It was replaced by Cobra 2000 and Mamaba systems, which are anti-tank guided missiles of the first generation, but with improved guidance and electronics. ENTAC (Engin téléguidé anti-char or MGM Petronor-32A is a French anti-tank wire-guided missile, widely spread and still in the operational use in many

Physical characterization of the fine particle emissions from commercial aircraft engines during the Aircraft Particle Emissions eXperiment (APEX) 1-3

Science.gov (United States)

Kinsey, John S.; Dong, Yuanji; Williams, D. Craig; Logan, Russell

2010-06-01

The fine particulate matter (PM) emissions from nine commercial aircraft engine models were determined by plume sampling during the three field campaigns of the Aircraft Particle Emissions Experiment (APEX). Ground-based measurements were made primarily at 30 m behind the engine for PM mass and number concentration, particle size distribution, and total volatile matter using both time-integrated and continuous sampling techniques. The experimental results showed a PM mass emission index (EI) ranging from 10 to 550 mg kg -1 fuel depending on engine type and test parameters as well as a characteristic U-shaped curve of the mass EI with increasing fuel flow for the turbofan engines tested. Also, the Teflon filter sampling indicated that ˜40-80% of the total PM mass on a test-average basis was comprised of volatile matter (sulfur and organics) for most engines sampled. The number EIs, on the other hand, varied from ˜10 15 to 10 17 particles kg -1 fuel with the turbofan engines exhibiting a logarithmic decay with increasing fuel flow. Finally, the particle size distributions of the emissions exhibited a single primary mode that were lognormally distributed with a minor accumulation mode also observed at higher powers for all engines tested. The geometric (number) mean particle diameter ranged from 9.4 to 37 nm and the geometric standard deviation ranged from 1.3 to 2.3 depending on engine type, fuel flow, and test conditions.

A Modular Aero-Propulsion System Simulation of a Large Commercial Aircraft Engine

Science.gov (United States)

DeCastro, Jonathan A.; Litt, Jonathan S.; Frederick, Dean K.

2008-01-01

A simulation of a commercial engine has been developed in a graphical environment to meet the increasing need across the controls and health management community for a common research and development platform. This paper describes the Commercial Modular Aero Propulsion System Simulation (C-MAPSS), which is representative of a 90,000-lb thrust class two spool, high bypass ratio commercial turbofan engine. A control law resembling the state-of-the-art on board modern aircraft engines is included, consisting of a fan-speed control loop supplemented by relevant engine limit protection regulator loops. The objective of this paper is to provide a top-down overview of the complete engine simulation package.

Tornado-borne missile speeds. Final report

International Nuclear Information System (INIS)

Simiu, E.; Cordes, M.

1976-04-01

An investigation of the question of tornado-borne missile speeds was carried out, with a view to identify pertinent areas of uncertainty and to estimate credible tornado-borne missile speeds - within the limitations inherent in the present state of the art. The investigation consists of two parts: (1) a study in which a rational model for the missile motion is proposed, and numerical experiments are carried out corresponding to various assumptions on the initial conditions of the missile motion, the structure of the tornado flow, and the aerodynamic properties of the missile; (2) a theoretical and experimental study of tornado-borne missile aerodynamics, conducted by Colorado State Univ. (CSU) to be covered in a separate report by CSU. In the present report, the factors affecting missile motion and their influence upon such motion are examined

Strategic Missile Defense & Nuclear Deterrence

Science.gov (United States)

Grego, Laura

The United States has pursued defenses against nuclear-armed long-range ballistic missiles since at least the 1950s. At the same time, concerns that missile defenses could undermine nuclear deterrence and potentially spark an arms race led the United States and Soviet Union to negotiate limits on these systems. The 1972 Anti-Ballistic Missile Treaty constrained strategic missile defenses for thirty years. After abandoning the treaty in 2002, President George W. Bush began fielding the Ground-based Midcourse Defense (GMD) homeland missile defense system on an extremely aggressive schedule, nominally to respond to threats from North Korea and Iran. Today, nearly fifteen years after its initial deployment, the potential and the limits of this homeland missile defense are apparent. Its test record is poor and it has no demonstrated ability to stop an incoming missile under real-world conditions. No credible strategy is in place to solve the issue of discriminating countermeasures. Insufficient oversight has not only exacerbated the GMD system's problems, but has obscured their full extent, which could encourage politicians and military leaders to make decisions that actually increase the risk of a missile attack against the United States. These are not the only costs. Both Russia and China have repeatedly expressed concerns that U.S. missile defenses adversely affect their own strategic capabilities and interests, particularly taken in light of the substantial US nuclear forces. This in turn affects these countries' nuclear modernization priorities. This talk will provide a technical overview of the US strategic missile defense system, and how it relates to deterrence against non-peer adversaries as well as how it affects deterrence with Russia and China and the long-term prospects for nuclear reductions

Missile rolling tail brake torque system. [simulating bearing friction on canard controlled missiles

Science.gov (United States)

Davis, W. T. (Inventor)

1984-01-01

Apparatus for simulating varying levels of friction in the bearings of a free rolling tail afterbody on a canard-controlled missile to determine friction effects on aerodynamic control characteristics is described. A ring located between the missile body and the afterbody is utilized in a servo system to create varying levels of friction between the missile body and the afterbody to simulate bearing friction.

15 CFR 742.5 - Missile technology.

Science.gov (United States)

2010-01-01

... 15 Commerce and Foreign Trade 2 2010-01-01 2010-01-01 false Missile technology. 742.5 Section 742... BASED CONTROLS § 742.5 Missile technology. (a) License requirements. (1) In support of U.S. foreign... establish the existence of a contract. (d) Missile Technology Control Regime. Missile Technology Control...

Detecting cracks in aircraft engine fan blades using vibrothermography nondestructive evaluation

International Nuclear Information System (INIS)

Gao, Chunwang; Meeker, William Q.; Mayton, Donna

2014-01-01

Inspection is an important part of many maintenance processes, especially for safety-critical system components. This work was motivated by the need to develop more effective methods to detect cracks in rotating components of aircraft engines. This paper describes the analysis of data from vibrothermography inspections on aircraft engine turbine blades. Separate but similar analysis were done for two different purposes. In both analyses, we fit statistical models with random effects to describe the crack-to-crack variability and the effect that the experimental variables have on the responses. In the first analysis, the purpose of the study was to find vibrothermography equipment settings that will provide good crack detection capability over the population of similar cracks in the particular kind of aircraft engine turbine blades that were inspected. Then, the fitted model was used to determine the test conditions where the probability of detection (POD) is expected to be high and probability of alarm is expected to be low. In our second analysis, crack size information was added and a similar model was fit. This model provides an estimate of POD as a function of crack size for specified test conditions. This function is needed as an input to models for planning in-service inspection intervals. - Highlights: • Developed experimental design methods to optimize the inspection parameters for a vibrothermography inspection system. • Used mixed effects modeling to describe crack-to-crack variability. • Fit an extended model to provide estimates of the probability of detection as a function of crack length. • Investigated the coverage probability of confidence intervals for probability of detection

Nonlinear transient responses of beams and rings to impulse loading or fragment impact

International Nuclear Information System (INIS)

Witmer, E.A.; Stagliano, T.R.; Rodal, J.J.A.

1977-01-01

Nuclear power plant protective structures may be subjected to various external missiles such as aircraft and tornado-generated missiles: telephone poles, planks, pipes, rods, automobiles, and other blown vehicles. Also, 'internally-generated missiles' such as fragments from powerplant rotors and aircraft engine rotors may impact protective structures. The present paper is concerned with a very limited part of the cited fragment threat; namely, fragments from high speed rotating machinery such as (1) aircraft engine rotors and (2) stationary power plant turbine rotors. Further, it is assumed that the structures intended to contain or control these fragments consist of initially-isotopic elastic-plastic metals. Certain potential containment/control (C/C) structures behave in a planar (or two-dimensional) fashion while other fragment-attacked C/C structures will undergo general three-dimensional deformations. Predictions for only the former category of fragment-attacked structures are discussed in the present paper. Pertinent experimental data discussed on fragment-attacked structures include (a) steel-sphere impact data involving beam targets and (b) engine rotor fragment impact against a steel containment ring. In all of these cases large-deflection, elastic-plastic transient structural responses occur. (Auth.)

Advanced Missile Signature Center

Data.gov (United States)

Federal Laboratory Consortium — The Advanced Missile Signature Center (AMSC) is a national facility supporting the Missile Defense Agency (MDA) and other DoD programs and customers with analysis,...

Aircraft dual-shaft jet engine with indirect action fuel flow controller

Science.gov (United States)

Tudosie, Alexandru-Nicolae

2017-06-01

The paper deals with an aircraft single-jet engine's control system, based on a fuel flow controller. Considering the engine as controlled object and its thrust the most important operation effect, from the multitude of engine's parameters only its rotational speed n is measurable and proportional to its thrust, so engine's speed has become the most important controlled parameter. Engine's control system is based on fuel injection Qi dosage, while the output is engine's speed n. Based on embedded system's main parts' mathematical models, the author has described the system by its block diagram with transfer functions; furthermore, some Simulink-Matlab simulations are performed, concerning embedded system quality (its output parameters time behavior) and, meanwhile, some conclusions concerning engine's parameters mutual influences are revealed. Quantitative determinations are based on author's previous research results and contributions, as well as on existing models (taken from technical literature). The method can be extended for any multi-spool engine, single- or twin-jet.

The Effect of Faster Engine Response on the Lateral Directional Control of a Damaged Aircraft

Science.gov (United States)

May, Ryan D.; Lemon, Kimberly A.; Csank, Jeffrey T.; Litt, Jonathan S.; Guo, Ten-Huei

2012-01-01

The integration of flight control and propulsion control has been a much discussed topic, especially for emergencies where the engines may be able to help stabilize and safely land a damaged aircraft. Previous research has shown that for the engines to be effective as flight control actuators, the response time to throttle commands must be improved. Other work has developed control modes that accept a higher risk of engine failure in exchange for improved engine response during an emergency. In this effort, a nonlinear engine model (the Commercial Modular Aero-Propulsion System Simulation 40k) has been integrated with a nonlinear airframe model (the Generic Transport Model) in order to evaluate the use of enhanced-response engines as alternative yaw rate control effectors. Tests of disturbance rejection and command tracking were used to determine the impact of the engines on the aircraft's dynamical behavior. Three engine control enhancements that improve the response time of the engine were implemented and tested in the integrated simulation. The enhancements were shown to increase the engine s effectiveness as a yaw rate control effector when used in an automatic feedback loop. The improvement is highly dependent upon flight condition; the airframe behavior is markedly improved at low altitude, low speed conditions, and relatively unchanged at high altitude, high speed.

Constructing an Efficient Self-Tuning Aircraft Engine Model for Control and Health Management Applications

Science.gov (United States)

Armstrong, Jeffrey B.; Simon, Donald L.

2012-01-01

Self-tuning aircraft engine models can be applied for control and health management applications. The self-tuning feature of these models minimizes the mismatch between any given engine and the underlying engineering model describing an engine family. This paper provides details of the construction of a self-tuning engine model centered on a piecewise linear Kalman filter design. Starting from a nonlinear transient aerothermal model, a piecewise linear representation is first extracted. The linearization procedure creates a database of trim vectors and state-space matrices that are subsequently scheduled for interpolation based on engine operating point. A series of steady-state Kalman gains can next be constructed from a reduced-order form of the piecewise linear model. Reduction of the piecewise linear model to an observable dimension with respect to available sensed engine measurements can be achieved using either a subset or an optimal linear combination of "health" parameters, which describe engine performance. The resulting piecewise linear Kalman filter is then implemented for faster-than-real-time processing of sensed engine measurements, generating outputs appropriate for trending engine performance, estimating both measured and unmeasured parameters for control purposes, and performing on-board gas-path fault diagnostics. Computational efficiency is achieved by designing multidimensional interpolation algorithms that exploit the shared scheduling of multiple trim vectors and system matrices. An example application illustrates the accuracy of a self-tuning piecewise linear Kalman filter model when applied to a nonlinear turbofan engine simulation. Additional discussions focus on the issue of transient response accuracy and the advantages of a piecewise linear Kalman filter in the context of validation and verification. The techniques described provide a framework for constructing efficient self-tuning aircraft engine models from complex nonlinear

Aircraft Engine Sensor/Actuator/Component Fault Diagnosis Using a Bank of Kalman Filters

Science.gov (United States)

Kobayashi, Takahisa; Simon, Donald L. (Technical Monitor)

2003-01-01

In this report, a fault detection and isolation (FDI) system which utilizes a bank of Kalman filters is developed for aircraft engine sensor and actuator FDI in conjunction with the detection of component faults. This FDI approach uses multiple Kalman filters, each of which is designed based on a specific hypothesis for detecting a specific sensor or actuator fault. In the event that a fault does occur, all filters except the one using the correct hypothesis will produce large estimation errors, from which a specific fault is isolated. In the meantime, a set of parameters that indicate engine component performance is estimated for the detection of abrupt degradation. The performance of the FDI system is evaluated against a nonlinear engine simulation for various engine faults at cruise operating conditions. In order to mimic the real engine environment, the nonlinear simulation is executed not only at the nominal, or healthy, condition but also at aged conditions. When the FDI system designed at the healthy condition is applied to an aged engine, the effectiveness of the FDI system is impacted by the mismatch in the engine health condition. Depending on its severity, this mismatch can cause the FDI system to generate incorrect diagnostic results, such as false alarms and missed detections. To partially recover the nominal performance, two approaches, which incorporate information regarding the engine s aging condition in the FDI system, will be discussed and evaluated. The results indicate that the proposed FDI system is promising for reliable diagnostics of aircraft engines.

Problems of Formation of Diagnostic Features in the Diagnosis of Aircraft Engines

Directory of Open Access Journals (Sweden)

Pronyakin V.I.

2017-01-01

Full Text Available The article is devoted to the evaluation of current technical condition of aircraft engines. Deals with the choice of the detection method of diagnostic features required for degradation assessment, emergency protection and detection of incipient defects on the example of cyclic machines and mechanisms. For the formation of diagnostic features in the diagnosis of aircraft engines use different physical effects (vibration, shock, heat radiation, electrodynamic and thermal processes, wear debris in oil, etc.. Classification of defects and requirements for the development of diagnostics systems is formed based on them. The article describes the requirements for diagnostic signs. The article provides a promising phase method that allows obtaining stable diagnostic characters in exploitation. The result of applying the method is shown. Diagnostic signs are formed. In mathematical modeling it was used the traditional theory of the description of rotary mechanisms. The data obtained are compared with experimental data.

Research and development of turbofan engine for supersonic aircraft. Choonsokukiyo turbofan engine no kenkyu kaihatsu

Energy Technology Data Exchange (ETDEWEB)

Yashima, S [Ishikawajima-Harima Heavy Industries Co. Ltd., Tokyo (Japan)

1992-01-01

This paper described the researched results of the demonstrator of a turbofan engine for supersonic aircraft (IHI-17). A turbofan engine with an afterburner was experimentally fabricated and various engine tests have been carried out since 1988. Although the engine size is small, the fighter engine specifications were applied to its design and the prior or simultaneous research on each component was carried out. As a result, the system integration technique by which an engine was assembled by integrating each component could be established. New materials and new manufacturing techniques such as turbine blades of single crystal, turbine disks of powder metallurgy and deep chemical milling for a duct were developed to use for the long term engine test and the prospect to commercialization could be obtained. The following techniques have been established and the results satisfying target specifications could be achieved: the three dimensional aerodynamic design of compressor and turbine, the adoption of air blast fuel atomizer to suppress the smoke generation, an afterburner of spray bar system and the mounting type FADEC (full authority digital electronic control) to control the engine with the afterburner. 4 refs., 15 figs., 4 tabs.

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.

Study of a LH2-fueled topping cycle engine for aircraft propulsion

Science.gov (United States)

Turney, G. E.; Fishbach, L. H.

1983-01-01

An analytical investigation was made of a topping cycle aircraft engine system which uses a cryogenic fuel. This system consists of a main turboshaft engine which is mechanically coupled (by cross-shafting) to a topping loop which augments the shaft power output of the system. The thermodynamic performance of the topping cycle engine was analyzed and compared with that of a reference (conventional-type) turboshaft engine. For the cycle operating conditions selected, the performance of the topping cycle engine in terms of brake specific fuel consumption (bsfc) was determined to be about 12 percent better than that of the reference turboshaft engine. Engine weights were estimated for both the topping cycle engine and the reference turboshaft engine. These estimates were based on a common shaft power output for each engine. Results indicate that the weight of the topping cycle engine is comparable to that of the reference turboshaft engine. Previously announced in STAR as N83-34942

Uncertainty quantification in computational fluid dynamics and aircraft engines

CERN Document Server

Montomoli, Francesco; D'Ammaro, Antonio; Massini, Michela; Salvadori, Simone

2015-01-01

This book introduces novel design techniques developed to increase the safety of aircraft engines. The authors demonstrate how the application of uncertainty methods can overcome problems in the accurate prediction of engine lift, caused by manufacturing error. This in turn ameliorates the difficulty of achieving required safety margins imposed by limits in current design and manufacturing methods. This text shows that even state-of-the-art computational fluid dynamics (CFD) are not able to predict the same performance measured in experiments; CFD methods assume idealised geometries but ideal geometries do not exist, cannot be manufactured and their performance differs from real-world ones. By applying geometrical variations of a few microns, the agreement with experiments improves dramatically, but unfortunately the manufacturing errors in engines or in experiments are unknown. In order to overcome this limitation, uncertainty quantification considers the probability density functions of manufacturing errors...

Local behavior of reinforced concrete slabs to aircraft engine projectile impact

International Nuclear Information System (INIS)

Yoo, Hyeon Kyeong; Choi, Hyun; Chung, Chul Hun; Lee, Jung Whee; Kim, Sang Yun

2011-01-01

Structural safety evaluation of nuclear power plant considers two distinct types of structural failure, local failure and global failure. In the local failure evaluation, considered projectiles can be divided as internal and external projectile according to the impact location, and they also can be divided as rigid and soft projectile according to the deformation level after impact. Frequently considered projectiles are aircraft engine, tornado, and turbine projectile. When the speed and weight of the projectiles are considered, the most influential projectile is aircraft engine, which is one of the soft projectiles. Sugano et al. performed impact test using an engine model projectile, which is derived from GE-J79 engine and concentrated mass-spring model idealization. Kojima and Sugano et al. demonstrated from their experiments that steel liner on the rear side of the concrete wall reduces impact induced damage and suppresses debris scattering. Chung et al. performed comparison study of various formulae suggested for local damage evaluation using previously performed numerous local impact test results. Also, they validated a methodology of numerical analysis for impact simulation using LS-DYNA. Previously suggested formulae and research results do not consider the effect of liner plate or curved shape of the containment building walls on the local damage. In this research, flat wall and curved wall are individually modeled using the same curvature of nuclear power plants, and the effects of curvature and liner plates on the local damage are analytically investigated

Individual aircraft life monitoring: An engineering approach for fatigue damage evaluation

Directory of Open Access Journals (Sweden)

Rui JIAO

2018-04-01

Full Text Available Individual aircraft life monitoring is required to ensure safety and economy of aircraft structure, and fatigue damage evaluation based on collected operational data of aircraft is an integral part of it. To improve the accuracy and facilitate the application, this paper proposes an engineering approach to evaluate fatigue damage and predict fatigue life for critical structures in fatigue monitoring. In this approach, traditional nominal stress method is applied to back calculate the S-N curve parameters of the realistic structure details based on full-scale fatigue test data. Then the S-N curve and Miner’s rule are adopted in damage estimation and fatigue life analysis for critical locations under individual load spectra. The relationship between relative small crack length and fatigue life can also be predicted with this approach. Specimens of 7B04-T74 aluminum alloy and TA15M titanium alloy are fatigue tested under two types of load spectra, and there is a good agreement between the experimental results and analysis results. Furthermore, the issue concerning scatter factor in individual aircraft damage estimation is also discussed. Keywords: Fatigue damage, Fatigue monitoring, Fatigue test, Scatter factor, S-N curve

Aircraft Engine Gas Path Diagnostic Methods: Public Benchmarking Results

Science.gov (United States)

Simon, Donald L.; Borguet, Sebastien; Leonard, Olivier; Zhang, Xiaodong (Frank)

2013-01-01

Recent technology reviews have identified the need for objective assessments of aircraft engine health management (EHM) technologies. To help address this issue, a gas path diagnostic benchmark problem has been created and made publicly available. This software tool, referred to as the Propulsion Diagnostic Method Evaluation Strategy (ProDiMES), has been constructed based on feedback provided by the aircraft EHM community. It provides a standard benchmark problem enabling users to develop, evaluate and compare diagnostic methods. This paper will present an overview of ProDiMES along with a description of four gas path diagnostic methods developed and applied to the problem. These methods, which include analytical and empirical diagnostic techniques, will be described and associated blind-test-case metric results will be presented and compared. Lessons learned along with recommendations for improving the public benchmarking processes will also be presented and discussed.

Eddy current testing for blade edge micro cracks of aircraft engine

Science.gov (United States)

Zhang, Wei-min; Xu, Min-dong; Gao, Xuan-yi; Jin, Xin; Qin, Feng

2017-10-01

Based on the problems of low detection efficiency in the micro cracks detection of aircraft engine blades, a differential excitation eddy current testing system was designed and developed. The function and the working principle of the system were described, the problems which contained the manufacture method of simulated cracks, signal generating, signal processing and the signal display method were described. The detection test was carried out by taking a certain model aircraft engine blade with simulated cracks as a tested specimen. The test data was processed by digital low-pass filter in the computer and the crack signals of time domain display and Lissajous figure display were acquired. By comparing the test results, it is verified that Lissajous figure display shows better performance compared to time domain display when the crack angle is small. The test results show that the eddy current testing system designed in this paper is feasible to detect the micro cracks on the aeroengine blade and can effectively improve the detection efficiency of micro cracks in the practical detection work.

Analysis of the overall structural behavior due to the impact of deformable missiles

International Nuclear Information System (INIS)

Ettouney, M.M.; Radini, R.R.; Hsueh, P.S.

1979-01-01

This paper presents a method of analysis to evaluate the overall behavior of reinforced concrete structures subjected to impact from deformable missiles. This method approaches the analysis in a very simple and practical way. The analysis is based on approximating the structure-missile system by a two-degree of freedom model. The two degrees of freedom model represents the missile and the structure, respectively. The hysteretic damping effects are considered implicitly through the nonlinearity of the two springs. Empirical formulas are presented for the evaluation of the dynamic properties of the nonlinear spring representing the concrete structure. The impact is simulated by applying an impulse on the two degrees of freedom system, then by the method of step by step numerical time integration (central difference formula is used) the time histories of the displacements and velocities of both the missile and structure are obtained. The numerical procedure is simple enough to be programmed by a hand or desk calculator which makes the method handy for most engineers and analysis. (orig.)

State of Aircraft Turboshaft Engines by Means of Tribotechnical Diagnostic

Science.gov (United States)

Mihalčová, Janka

2018-03-01

The contribution describes concrete example of application of tribotechnical methods for the determination of the bearing wear state in aircraft turboshaft engines. Tribotechnical methods, which will be mentioned, deal with qualitative and quantitative characterization of particles occurred in oil. Here belong method optical emission spectrometry method with rotating disc electrode for determination of chemical elements concentration in oil. Method of optical particles counting for detection of particles distribution according to their scale, determination of their number and ferrographic analysis. Exploitation of these methods make it possible to determine quickly and correctly the friction regime and wearing of friction pair that is washed by oil in observed engines.

Fragility assessment method of Concrete Wall Subjected to Impact Loading

International Nuclear Information System (INIS)

Hahm, Daegi; Shin, Sang Shup; Choi, In-Kil

2014-01-01

These studies have been aimed to verify and ensure the safety of the targeted walls and structures especially in the viewpoint of the deterministic approach. However, recently, the regulation and the assessment of the safety of the nuclear power plants (NPPs) against to an aircraft impact are strongly encouraged to adopt a probabilistic approach, i.e., the probabilistic risk assessment of an aircraft impact. In Korea, research to develop aircraft impact risk quantification technology was initiated in 2012 by Korea Atomic Energy Research Institute (KAERI). In this paper, for the one example of the probabilistic safety assessment approach, a method to estimate the failure probability and fragility of concrete wall subjected to impact loading caused by missiles or engine parts of aircrafts will be introduced. This method and the corresponding results will be used for the total technical roadmap and the procedure to assess the aircraft impact risk (Fig.1). A method and corresponding results of the estimation of the failure probability and fragility for a concrete wall subjected to impact loadings caused by missiles or engine parts of aircrafts was introduced. The detailed information of the target concrete wall in NPP, and the example aircraft engine model is considered safeguard information (SGI), and is not contained in this paper

Aircraft gas turbines

Energy Technology Data Exchange (ETDEWEB)

Sekido, T [Ishikawajima-Harima Heavy Industries, Co. Ltd., Tokyo (Japan)

1994-03-01

Current developmental activities of aircraft gas turbines in Japan are reviewed. V2500-A5 engine with thrust of 30,000 LBF is scheduled to be used for real aircraft in 1994, and intensive developmental activities are also proceeding in larger engines over 90,000 LBF. Recently, developmental programs of engines for 75-100 seat aircraft have been actively discussed, and Japanese engine makers are having discussions towards international collaboration. Such engines will be high bypass turbofans of 12,000-22,000 LBF. Development of SST/HST engines in a speed range from subsonic to Mach 5 is under the initiative of the Agency of Industrial Science and Technology. The Technical Research and Development Institute of Japan, Defence Agency achieved the target thrust of 3.4 tons in the small turbofan engine program, and the small turboshaft engine for small helicopters is also under development. Both National Aerospace Laboratory (NAL) and Institute of Space and Aeronautical Science (ISAS) are now conducting the research programs on turbo-ramjet engines under a component test phase. 1 fig.

Missile defense in the United States

OpenAIRE

Heurlin, Bertil

2004-01-01

The basic arguments of this paper are, first, that the current US-missile defense, being operative from fall 2004, is based upon the former experiences with missile defense, second, that missile defense closely associated with weapons of mass destruction has gained the highest priority in American national security policy due to the 9.11 attacks, and third, that the superior argument for establishing an American missile defense is to maintain global, long term political-strategic superiority....

Correlation between electrical, mechanical and chemical properties of fresh and used aircraft engine oils

Science.gov (United States)

Gajewski, Juliusz B.; Głogowski, Marek J.; Paszkowski, Maciej; Czarnik-Matusewicz, Bogusława

2011-06-01

In this paper the results are presented of measurements of electrical, mechanical and chemical properties of fresh and used aircraft engine oils. Oils were used in a four-stroke aircraft engine and their samples were taken after the 50-hour work of the engine. The resistivity, permittivity and viscosity of oils were measured as a function of temperature. Additionally, some measurements of the absorbance spectra and size of particles contained in the oils were carried out. The significant reduction in the resistivity of the used Total oil was observed. The relative permittivity of both used oils was slightly increased. The oil's relative viscosity depends on temperature of oil and given time that elapsed from the very first moment when the shear force was applied in a rheometer. The results obtained allowed one to identify more precisely the chemical and physico-chemical interactions occurring in the tested samples, as compared with a typical infrared spectroscopy.

Computerized systems analysis and optimization of aircraft engine performance, weight, and life cycle costs

Science.gov (United States)

Fishbach, L. H.

1979-01-01

The computational techniques utilized to determine the optimum propulsion systems for future aircraft applications and to identify system tradeoffs and technology requirements are described. The characteristics and use of the following computer codes are discussed: (1) NNEP - a very general cycle analysis code that can assemble an arbitrary matrix fans, turbines, ducts, shafts, etc., into a complete gas turbine engine and compute on- and off-design thermodynamic performance; (2) WATE - a preliminary design procedure for calculating engine weight using the component characteristics determined by NNEP; (3) POD DRG - a table look-up program to calculate wave and friction drag of nacelles; (4) LIFCYC - a computer code developed to calculate life cycle costs of engines based on the output from WATE; and (5) INSTAL - a computer code developed to calculate installation effects, inlet performance and inlet weight. Examples are given to illustrate how these computer techniques can be applied to analyze and optimize propulsion system fuel consumption, weight, and cost for representative types of aircraft and missions.

Correlation between electrical, mechanical and chemical properties of fresh and used aircraft engine oils

International Nuclear Information System (INIS)

Gajewski, Juliusz B; Glogowski, Marek J; Paszkowski, Maciej; Czarnik-Matusewicz, Boguslawa

2011-01-01

In this paper the results are presented of measurements of electrical, mechanical and chemical properties of fresh and used aircraft engine oils. Oils were used in a four-stroke aircraft engine and their samples were taken after the 50-hour work of the engine. The resistivity, permittivity and viscosity of oils were measured as a function of temperature. Additionally, some measurements of the absorbance spectra and size of particles contained in the oils were carried out. The significant reduction in the resistivity of the used Total oil was observed. The relative permittivity of both used oils was slightly increased. The oil's relative viscosity depends on temperature of oil and given time that elapsed from the very first moment when the shear force was applied in a rheometer. The results obtained allowed one to identify more precisely the chemical and physico-chemical interactions occurring in the tested samples, as compared with a typical infrared spectroscopy.

Potential for Fuel Tank Fire and Hydrodynamic Ram from Uncontained Aircraft Engine Debris

Science.gov (United States)

1997-01-01

This report addresses the potential consequences of the impact and penetration of fuel tanks by debris from uncontained engine failures on commercial jet aircraft. The report presents a brief review of accident data and of the pertinent technical lit...

CSIR in aerospace: An engine for future industrial growth

CSIR Research Space (South Africa)

Naidoo, Kavendra

2017-10-01

Full Text Available for industry impact 3 A brief summary of previous and current activities in SA aerospace Argos-II Airborne Observation System SumbandilaSat Satellite 4 RAVIN Light Aircraft JS1 Championship Glider Sling Light Sport Aircraft AIRBUS SUPPLIER... BOEING SUPPLIER SAAB Light Fighter Aircraft Airbus Military Transport Agusta Military Helicopter A brief summary of previous and current activities in SA aerospace A-Darter Short Range Air to Air Missile 5 Test flight centre Alkantpan...

Assessment of engine noise shielding by the wings of current turbofan aircraft

NARCIS (Netherlands)

Alves Vieira, A.E.; Snellen, M.; Simons, D.G.; Gibbs, B.

2017-01-01

The shielding of engine noise by the aircraft wings and fuselage can lead to a significant reduction on perceived noise on ground. Most research on noise shielding is focused on BlendedWing Body (BWB) configurations because of the large dimension of the fuselage. However, noise shielding is also

Multi-channel, passive, short-range anti-aircraft defence system

Science.gov (United States)

Gapiński, Daniel; Krzysztofik, Izabela; Koruba, Zbigniew

2018-01-01

The paper presents a novel method for tracking several air targets simultaneously. The developed concept concerns a multi-channel, passive, short-range anti-aircraft defence system based on the programmed selection of air targets and an algorithm of simultaneous synchronisation of several modified optical scanning seekers. The above system is supposed to facilitate simultaneous firing of several self-guided infrared rocket missiles at many different air targets. From the available information, it appears that, currently, there are no passive self-guided seekers that fulfil such tasks. This paper contains theoretical discussions and simulations of simultaneous detection and tracking of many air targets by mutually integrated seekers of several rocket missiles. The results of computer simulation research have been presented in a graphical form.

Some failure analyses of South African Air Force aircraft engine and airframe components

CSIR Research Space (South Africa)

Benson, JM

1998-06-01

Full Text Available Failure analyses of various engine and airframe components from South African Air Force aircraft have been performed by the Division of Materials Science and Technology over several years and these have ranged from crash investigations to minor...

Study on afterburner of aircraft engine. Koku engine yo afterburner no kenkyu

Energy Technology Data Exchange (ETDEWEB)

Kashiwagi, T [Ishikawajima-Harima Heavy Industries, Co. Ltd., Tokyo (Japan)

1991-03-01

This paper explains concepts of aircraft engine afterburner, and describes history of afterburner study, and describe the result of major research items. An afterburner is located down stream of a fan, compressor, burner, and turbine in a jet engine. Its basic principle is that fuel is injected into turbine exhaust and fan air flows from an fuel injector, ignited by a spark plug using oxygen remaining in the exhaust gas flow, burned and flame-held by a flame stabilizer. The combustion gas of high temperature (1,700 to 1,800 {degree}c) thus generated is jetted out from an exhaust nozzle to increase the thrust. The prototype afterburner is featured by adoption of a mixed type fuel injection system that provides wide stable combustion range, and flame stabilizer with a scoop aimed at improving the ignition performance and combustion efficiency. A confirmation test verified smooth ignition and wide air to fuel ratio for stabilized combustion. 4 refs., 16 figs.

Missile non-proliferation: an alternative approach

International Nuclear Information System (INIS)

Delory, Stephane

2011-01-01

In this report, the author first proposes an overview of the notion of missile prohibition. He notices that the association between weapons of mass destruction and missiles is a prelude to the legitimacy of missile control, notably within the framework of the Missile Technology Control Regime or MTCR. He also comments the notion of total ban. In a second part, the author analyses and discusses the limitations of the control of technology diffusion. He discusses the role of the MTCR, comments the evolution of this regime with the taking of China and Russia into consideration, the impacts of national implementations of export regimes on the MTCR, and economic aspects of control implementation. In the next part, the author addresses other kinds of limitations, i.e. those related with capacity evolutions of proliferating States. The last part addresses the evolution towards a new definition of approach to missile non-proliferation, notably in terms of perception of missile roles and of technology transfer controls

Solar thermal aircraft

Science.gov (United States)

Bennett, Charles L.

2007-09-18

A solar thermal powered aircraft powered by heat energy from the sun. A heat engine, such as a Stirling engine, is carried by the aircraft body for producing power for a propulsion mechanism, such as a propeller. The heat engine has a thermal battery in thermal contact with it so that heat is supplied from the thermal battery. A solar concentrator, such as reflective parabolic trough, is movably connected to an optically transparent section of the aircraft body for receiving and concentrating solar energy from within the aircraft. Concentrated solar energy is collected by a heat collection and transport conduit, and heat transported to the thermal battery. A solar tracker includes a heliostat for determining optimal alignment with the sun, and a drive motor actuating the solar concentrator into optimal alignment with the sun based on a determination by the heliostat.

Design and evaluation of combustors for reducing aircraft engine pollution

Science.gov (United States)

Jones, R. E.; Grobman, J.

1973-01-01

Various techniques and test results are briefly described and referenced for detail. The effort arises from the increasing concern for the measurement and control of emissions from gas turbine engines. The greater part of this research is focused on reducing the oxides of nitrogen formed during takeoff and cruise in both advanced CTOL, high pressure ratio engines, and advanced supersonic aircraft engines. The experimental approaches taken to reduce oxides of nitrogen emissions include the use of: multizone combustors incorporating reduced dwell time, fuel-air premixing, air atomization, fuel prevaporization, water injection, and gaseous fuels. In the experiments conducted to date, some of these techniques were more successful than others in reducing oxides of nitrogen emissions. Tests are being conducted on full-annular combustors at pressures up to 6 atmospheres and on combustor segments at pressures up to 30 atmospheres.

Recent technologies for reduction of aircraft propulsion noise. Kokuki engine soon teigenka no saikin no gijutsu shinpo ni tsuite

Energy Technology Data Exchange (ETDEWEB)

Kobayashi, H [National Aerospace Lab., Chofu, Tokyo (Japan)

1994-03-10

Inside the jet engine, the propulsion engine for an aircraft, a high speed air current is flowing, and the rotors such as the fan, compress or, turbine and so forth are rotating with a high speed in its flowing current. The flow itself in which a high speed exhaust jet is discharged in the air from engine exhaust port, and the aerodynamic noise generated by an interaction of the flow with the material bodies are the main noise sources of the aircraft engine. Because the supersonic planes are necessary to fly with mach number 2 - 3 during cruising, the turbojet engine with a large jet exhaust speed or the low bypass ratio turbofan engine is selected. Since a noise reduction by reducing the jet exhaust speed, which was an effective measure for the high subsonic speed passenger plane, can not be applied, a reduction of the supersonic jet noise, which is hard to be reduced, becomes a necessity. In addition, in recent years, a research and development of the advanced turbo prop (ATP) aircraft with a further higher thrust efficiency are advanced as well. The aerodynamical noise reduction technologies of these engines for supersonic airplanes are summarized. 14 refs., 11 figs., 1 tab.

Evaluation of Methods for the Determination of Black Carbon Emissions from an Aircraft Gas Turbine Engine

Science.gov (United States)

The emissions from aircraft gas turbine engines consist of nanometer size black carbon (BC) particles plus gas-phase sulfur and organic compounds which undergo gas-to-particle conversion downstream of the engine as the plume cools and dilutes. In this study, four BC measurement ...

Strength analysis of an aircraft turbo-compressor engine turbine disc

Science.gov (United States)

Klimko, Marek

2017-09-01

This article deals with a strength analysis of a gas turbine rotor disc of the concrete type of an aircraft turbo-compressor engine (ATCE). The introductory part is dedicated to a basic description of the given engine, including the main technical parameters entering the calculation. The calculation is carried out by the finite difference method. This method allows to determine the tension of a generally shaped disc, which is affected by centrifugal forces of its weight, external load and heat stress caused by the difference of thermal gradients along the disc radius. The result of calculations are dependencies of the most important parameters, such as the reduced stress, radial stress, or the safety coefficient along the disc radius.

Engine Yaw Augmentation for Hybrid-Wing-Body Aircraft via Optimal Control Allocation Techniques

Science.gov (United States)

Taylor, Brian R.; Yoo, Seung Yeun

2011-01-01

Asymmetric engine thrust was implemented in a hybrid-wing-body non-linear simulation to reduce the amount of aerodynamic surface deflection required for yaw stability and control. Hybrid-wing-body aircraft are especially susceptible to yaw surface deflection due to their decreased bare airframe yaw stability resulting from the lack of a large vertical tail aft of the center of gravity. Reduced surface deflection, especially for trim during cruise flight, could reduce the fuel consumption of future aircraft. Designed as an add-on, optimal control allocation techniques were used to create a control law that tracks total thrust and yaw moment commands with an emphasis on not degrading the baseline system. Implementation of engine yaw augmentation is shown and feasibility is demonstrated in simulation with a potential drag reduction of 2 to 4 percent. Future flight tests are planned to demonstrate feasibility in a flight environment.

Protection against external impacts and missiles - Load assumption and effects on the plant design of a 1300 MW PWR-Plant

International Nuclear Information System (INIS)

Gremm, O.; Orth, K.H.

1978-01-01

The load assumptions and effects of the external impacts are given. The fundamental properties of the KWU standard design according to these impacts and the consequences for the engineering safeguards are explained. The protection against external impacts includes the protection against all external missiles. The basic measure of protection against internal missiles is the strict separation of redundancies. (author)

An Archeological Overview and Management Plan for the Tarheel Army Missile Plant Alamance County, North Carolina.

Science.gov (United States)

1984-05-21

factory planning engineer, noted that bedrock lies about 22 feet be- low the surface in the eastern portion of the main plant area, but had not...Carolina Press. Lee, James B. 1983. Personal communication. Factory Planning Engineer, Western Electric Company, Tarheel Army Missile Plant. Lefl1cr, Hugh

Japan and Ballistic Missile Defense

National Research Council Canada - National Science Library

Swaine, Michael

2001-01-01

Spurred by a perceived growing ballistic missile threat from within the Asia-Pacific region and requests from the United States to support research and development on components of a missile defense...

Thrust Performance Evaluation of a Turbofan Engine Based on Exergetic Approach and Thrust Management in Aircraft

Science.gov (United States)

Yalcin, Enver

2017-05-01

The environmental parameters such as temperature and air pressure which are changing depending on altitudes are effective on thrust and fuel consumption of aircraft engines. In flights with long routes, thrust management function in airplane information system has a structure that ensures altitude and performance management. This study focused on thrust changes throughout all flight were examined by taking into consideration their energy and exergy performances for fuel consumption of an aircraft engine used in flight with long route were taken as reference. The energetic and exergetic performance evaluations were made under the various altitude conditions. The thrust changes for different altitude conditions were obtained to be at 86.53 % in descending direction and at 142.58 % in ascending direction while the energy and exergy efficiency changes for the referenced engine were found to be at 80.77 % and 84.45 %, respectively. The results revealed here can be helpful to manage thrust and reduce fuel consumption, but engine performance will be in accordance with operation requirements.

A Potent Vector: Assessing Chinese Cruise Missile Developments

Science.gov (United States)

2014-01-01

likelihood that they will successfully penetrate defenses.1 Employed in salvos, perhaps in tandem with ballistic missiles, cruise missiles could...series cruise missiles for export.4 Finally, for three decades China has marketed a wide range of indig- enously produced cruise missiles (and other...distances and thus more vulnerable to at- tacks from advanced air defense systems, such as Aegis. Both missiles execute sea- skimming attacks at an

Ballistic Missile Defense in Europe

OpenAIRE

Sarihan, Ali; Bush, Amy; Summers, Lawrence; Thompson, Brent; Tomasszewski, Steven

2009-01-01

This paper will build on ballistic missile defense in Europe. In the first part, a brief historical overview will place the current public management issue into light. This is followed by a discussion of the main actors in the international debate, the problems that arise and the available options and recommendations to address missile defense. In the second part, differences between George W. Bush and Barack H. Obama will analyze under the title “Ballistic Missile Defense in Europe: Evolving...

Joint Air-to-Surface Standoff Missile (JASSM)

Science.gov (United States)

2015-12-01

6.1.3) All Ops All Ops Joint Critical Ops All Ops All Ops Missile Reliability (KSA) (CPD para 6.2.8) 4th Lot .91 4th Lot .91 IOT &E .80 4th Lot .85 IOT &E...the ORD 303-95-III dated January 20, 2004 Change Explanations None Acronyms and Abbreviations IOT &E - Initial Operational Test and Evaluation KSA... Actuator Control Card, Lots 12 and 4 Systems Engineering Program Support/Program Tooling and Test Equipment, and JASSM-ER Standard Data Protocol (DS

Effects of acoustic treatment on the interior noise levels of a twin-engine propeller aircraft - Experimental flight results and theoretical predictions

Science.gov (United States)

Beyer, T. B.; Powell, C. A.; Daniels, E. F.; Pope, L. D.

1984-01-01

In-flight noise level measurements were made within two cabin configurations of a general aviation business aircraft. The Fairchild Merlin IVC twin-engine aircraft was tested with bare walls and fiberglass insulation and in an executive trim configuration. Narrow-band and octave format data were subjected to analyses which permitted identification of the blade passage harmonics (BPH). Cabin noise level reductions (insertion losses) due to added insulation varied with position in the cabin, the BPH number, cabin pressure, and engine torque. The measurements were closely predicted using the propeller aircraft interior noise (PAIN) mode.

U.S. Army Unmanned Aircraft Systems (UAS) - A Historical Perspective to Identifying and Understanding Stakeholder Relationships

Science.gov (United States)

2014-06-01

U.S. Army (USA) to train Nike anti-aircraft missile crews and others through the 1970s. Mach 2 UAV targets consisted of several prototypes such as...manufacturers with the largest share of the global UAS market include General Atomics (20.4 percent), Northrop Grumman (18.9 percent), Boeing (1.5... mix of both manned and unmanned aircraft systems. By combining advanced sensors, tactical RSTA, MUM teaming of UAS, attack and reconnaissance

Starting the aircraft engines and gas-turbine drive by means of electric starter

Directory of Open Access Journals (Sweden)

І.М. Іщенко

2004-04-01

Full Text Available  In the article the questions of the starting the aircraft engines and gas-turbine drive by means of electric starter is considered. In the same way in the article are determined the main requirements to steady-state converter for feeding electric starter.

Historical development of world wide guided missiles

Science.gov (United States)

Spearman, M. L.

1978-01-01

This paper attempts to put in perspective the development of missiles from early history to present time. The influence of World War II in accelerating the development of guided missiles, particularly through German scientists, is discussed. The dispersion of German scientists to other countries and the coupling of their work with native talent to develop guided missiles is traced. Particular emphasis is placed on the evolution of the missile in the U.S. and the U.S.S.R. Since the Soviets possess what is probably the world's most complete array of dedicated missile system types, their known inventory is reviewed in some detail.

Hyper Velocity Missiles For Defence

Directory of Open Access Journals (Sweden)

Faqir Minhas

2005-10-01

Full Text Available The paper reviews the history of technical development in the field of hypervelocity missiles. It highlights the fact that the development of anti-ballistic systems in USA, Russia, France, UK, Sweden, and Israel is moving toward the final deployment stage; that USA and Israel are trying to sell PAC 2 and Arrow 2 to India; and that India’s Agni and Prithvi missiles have improved their accuracy, with assistance from Russia. Consequently, the paper proposes enhanced effort for development in Pakistan of a basic hypersonic tactical missile, with 300 KM range, 500 KG payload, and multi-rolecapability. The author argues that a system, developed within the country, at the existing or upgraded facilities, will not violate MTCR restrictions, and would greatly enhance the country’s defense capability. Furthermore, it would provide high technology jobs toPakistani citizens. The paper reinforces the idea by suggesting that evolution in the field of aviation and electronics favors the development of ballistic, cruise and guided missile technologies; and that flight time of short and intermediate range missiles is so short that its interception is virtually impossible.

Analysis of a topping-cycle, aircraft, gas-turbine-engine system which uses cryogenic fuel

Science.gov (United States)

Turney, G. E.; Fishbach, L. H.

1984-01-01

A topping-cycle aircraft engine system which uses a cryogenic fuel was investigated. This system consists of a main turboshaft engine that is mechanically coupled (by cross-shafting) to a topping loop, which augments the shaft power output of the system. The thermodynamic performance of the topping-cycle engine was analyzed and compared with that of a reference (conventional) turboshaft engine. For the cycle operating conditions selected, the performance of the topping-cycle engine in terms of brake specific fuel consumption (bsfc) was determined to be about 12 percent better than that of the reference turboshaft engine. Engine weights were estimated for both the topping-cycle engine and the reference turboshaft engine. These estimates were based on a common shaft power output for each engine. Results indicate that the weight of the topping-cycle engine is comparable with that of the reference turboshaft engine.

Cost of space-based laser ballistic missile defense.

Science.gov (United States)

Field, G; Spergel, D

1986-03-21

Orbiting platforms carrying infrared lasers have been proposed as weapons forming the first tier of a ballistic missile defense system under the President's Strategic Defense Initiative. As each laser platform can destroy a limited number of missiles, one of several methods of countering such a system is to increase the number of offensive missiles. Hence it is important to know whether the cost-exchange ratio, defined as the ratio of the cost to the defense of destroying a missile to the cost to the offense of deploying an additional missile, is greater or less than 1. Although the technology to be used in a ballistic missile defense system is still extremely uncertain, it is useful to examine methods for calculating the cost-exchange ratio. As an example, the cost of an orbiting infrared laser ballistic missile defense system employed against intercontinental ballistic missiles launched simultaneously from a small area is compared to the cost of additional offensive missiles. If one adopts lower limits to the costs for the defense and upper limits to the costs for the offense, the cost-exchange ratio comes out substantially greater than 1. If these estimates are confirmed, such a ballistic missile defense system would be unable to maintain its effectiveness at less cost than it would take to proliferate the ballistic missiles necessary to overcome it and would therefore not satisfy the President's requirements for an effective strategic defense. Although the method is illustrated by applying it to a space-based infrared laser system, it should be straightforward to apply it to other proposed systems.

Cost Effective Regional Ballistic Missile Defense

Science.gov (United States)

2016-02-16

deploying advanced air defense systems18, such as the Russian S-300 and S-500, and concealing them in hardened, camouflaged sites, such as extensive... Russian objections to the European Phased Adaptive Approach (EPAA) and fund homeland defense priorities.39 Furthermore, the PTSS system was also... Theatre Ballistic Missile Defence Capability Becomes Operational,” Jane’s Missiles & Rockets, 1 February 2011. 55 Joseph W. Kirschbaum, REGIONAL MISSILE

Ballistic Missile Defense

OpenAIRE

Mayer, Michael

2011-01-01

At the 2010 NATO summit in Lisbon, the alliance decided to move forward on the development of a territorial ballistic missile defense (BMD) system and explore avenues for cooperation with Russia in this endeavor. Substantial progress on BMD has been made over the past decade, but some questions remain regarding the ultimate strategic utility of such a system and whether its benefi ts outweigh the possible opportunity costs. Missile defense has been a point of contention between the US and its...

Small Transport Aircraft Technology /STAT/ Propulsion Study

Science.gov (United States)

Heldenbrand, R. W.; Baerst, C. F.; Rowse, J. H.

1980-01-01

The NASA Small Transport Aircraft Technology (STAT) Propulsion Study was established to identify technology requirements and define the research and development required for new commuter aircraft. Interim results of the studies defined mission and design characteristics for 30- and 50-passenger aircraft. Sensitivities were defined that relate changes in engine specific fuel consumption (SFC), weight, and cost (including maintenance) to changes in the aircraft direct operating cost (DOC), takeoff gross weight, and empty weight. A comparison of performance and economic characteristics is presented between aircraft powered by 1980 production engines and those powered by a 1990 advanced technology baseline engine.

An Integrated Architecture for On-Board Aircraft Engine Performance Trend Monitoring and Gas Path Fault Diagnostics

Science.gov (United States)

Simon, Donald L.

2010-01-01

Aircraft engine performance trend monitoring and gas path fault diagnostics are closely related technologies that assist operators in managing the health of their gas turbine engine assets. Trend monitoring is the process of monitoring the gradual performance change that an aircraft engine will naturally incur over time due to turbomachinery deterioration, while gas path diagnostics is the process of detecting and isolating the occurrence of any faults impacting engine flow-path performance. Today, performance trend monitoring and gas path fault diagnostic functions are performed by a combination of on-board and off-board strategies. On-board engine control computers contain logic that monitors for anomalous engine operation in real-time. Off-board ground stations are used to conduct fleet-wide engine trend monitoring and fault diagnostics based on data collected from each engine each flight. Continuing advances in avionics are enabling the migration of portions of the ground-based functionality on-board, giving rise to more sophisticated on-board engine health management capabilities. This paper reviews the conventional engine performance trend monitoring and gas path fault diagnostic architecture commonly applied today, and presents a proposed enhanced on-board architecture for future applications. The enhanced architecture gains real-time access to an expanded quantity of engine parameters, and provides advanced on-board model-based estimation capabilities. The benefits of the enhanced architecture include the real-time continuous monitoring of engine health, the early diagnosis of fault conditions, and the estimation of unmeasured engine performance parameters. A future vision to advance the enhanced architecture is also presented and discussed

A Model Stitching Architecture for Continuous Full Flight-Envelope Simulation of Fixed-Wing Aircraft and Rotorcraft from Discrete Point Linear Models

Science.gov (United States)

2016-04-01

AND ROTORCRAFT FROM DISCRETE -POINT LINEAR MODELS Eric L. Tobias and Mark B. Tischler Aviation Development Directorate Aviation and Missile...Stitching Architecture for Continuous Full Flight-Envelope Simulation of Fixed-Wing Aircraft and Rotorcraft from Discrete -Point Linear Models 5...of discrete -point linear models and trim data. The model stitching simulation architecture is applicable to any aircraft configuration readily

Probability and containment of turbine missiles

International Nuclear Information System (INIS)

Yeh, G.C.K.

1976-01-01

With the trend toward ever larger power generating plants with large high-speed turbines, an important plant design consideration is the potential for and consequences of mechanical failure of turbine rotors. Such rotor failure could result in high-velocity disc fragments (turbine missiles) perforating the turbine casing and jeopardizing vital plant systems. The designer must first estimate the probability of any turbine missile damaging any safety-related plant component for his turbine and his plant arrangement. If the probability is not low enough to be acceptable to the regulatory agency, he must design a shield to contain the postulated turbine missiles. Alternatively, the shield could be designed to retard (to reduce the velocity of) the missiles such that they would not damage any vital plant system. In this paper, some of the presently available references that can be used to evaluate the probability, containment and retardation of turbine missiles are reviewed; various alternative methods are compared; and subjects for future research are recommended. (Auth.)

Experimental simulation of a light aircraft crash on to a nuclear power plant auxiliary building roof

International Nuclear Information System (INIS)

Barnes, D.; Barr, P.; Garton, G.; Howe, W.D.; Neilson, A.J.

1984-08-01

The experiments described were conducted at a reduced scale with geometric dimensions of prototype structures of one-fifth full size. The target was based on the auxiliary buildings for the proposed Sizewell PWR. Descriptions of the simulated aircraft model and the test panels are given, together with the instrumentation. Details are given of the test programme and the results are summarized and discussed. Comparison is made of the model aircraft tests with an equivalent hard missile impact. (U.K.)

Modeling and Detection of Ice Particle Accretion in Aircraft Engine Compression Systems

Science.gov (United States)

May, Ryan D.; Simon, Donald L.; Guo, Ten-Huei

2012-01-01

The accretion of ice particles in the core of commercial aircraft engines has been an ongoing aviation safety challenge. While no accidents have resulted from this phenomenon to date, numerous engine power loss events ranging from uneventful recoveries to forced landings have been recorded. As a first step to enabling mitigation strategies during ice accretion, a detection scheme must be developed that is capable of being implemented on board modern engines. In this paper, a simple detection scheme is developed and tested using a realistic engine simulation with approximate ice accretion models based on data from a compressor design tool. These accretion models are implemented as modified Low Pressure Compressor maps and have the capability to shift engine performance based on a specified level of ice blockage. Based on results from this model, it is possible to detect the accretion of ice in the engine core by observing shifts in the typical sensed engine outputs. Results are presented in which, for a 0.1 percent false positive rate, a true positive detection rate of 98 percent is achieved.

A fully adaptive hybrid optimization of aircraft engine blades

Science.gov (United States)

Dumas, L.; Druez, B.; Lecerf, N.

2009-10-01

A new fully adaptive hybrid optimization method (AHM) has been developed and applied to an industrial problem in the field of the aircraft engine industry. The adaptivity of the coupling between a global search by a population-based method (Genetic Algorithms or Evolution Strategies) and the local search by a descent method has been particularly emphasized. On various analytical test cases, the AHM method overperforms the original global search method in terms of computational time and accuracy. The results obtained on the industrial case have also confirmed the interest of AHM for the design of new and original solutions in an affordable time.

Structureborne noise measurements on a small twin-engine aircraft

Science.gov (United States)

Cole, J. E., III; Martini, K. F.

1988-01-01

Structureborne noise measurements performed on a twin-engine aircraft (Beechcraft Baron) are reported. There are two overall objectives of the test program. The first is to obtain data to support the development of analytical models of the wing and fuselage, while the second is to evaluate effects of structural parameters on cabin noise. Measurements performed include structural and acoustic responses to impact excitation, structural and acoustic loss factors, and modal parameters of the wing. Path alterations include added mass to simulate fuel, variations in torque of bolts joining wing and fuselage, and increased acoustic absorption. Conclusions drawn regarding these measurements are presented.

Influence of Missile Fusillade Engagement Mode on Operation Efficiency

Institute of Scientific and Technical Information of China (English)

BU Xian-jin; REN Yi-guang; SHA Ji-chang

2008-01-01

Shoot efficiency is one of the most important evaluation indexes of the operation efficiency of weapon system. In this paper, based on definitions of the probability and the expected number of missed attacking missiles, the expected numbers of anti-missiles and attacking missiles hit by single anti-missile, fusillade mechanism of multi-missile is analyzed systematically. The weapon operation efficiency in various engagement patterns is also studied. The results show that double missiles fusillade is the most feasible manner for increasing the weapon operation efficiency.

Tornado missile simulation and risk analysis

International Nuclear Information System (INIS)

Twisdale, L.A.; Dunn, W.L.; Chu, J.

1978-01-01

Mathematical models of the contributing events to the tornado missile hazard at nuclear power plants have been developed in which the major sources of uncertainty have been considered in a probabilistic framework. These models have been structured into a sequential event formalism which permits the treatment of both single and multiple missile generation events. A simulation computer code utilizing these models has been developed to obtain estimates of tornado missile event likelihoods. Two case studies have been analyzed; the results indicate that the probability of a single missile from the sampling population impacting any of the plant's targets is less then about 10 -7 per reactor-year. Additional work is needed for verification and sensitivity study

Pratt & Whitney aircraft nuclear J-8 turbojet engine performance variation with radiator diameter

International Nuclear Information System (INIS)

Larson, John W.

1960-01-01

The variation of engine performance with liquid metal radiator diameter and flight altitude has been estimated for both the 1600F NaK and 1800F NaK radiators at Mach 0.6 and hot day atmospheric conditions. The net thrust, air flow and reactor power is presented in 3 figures for the Pratt & Whitney Aircraft J-58 engine with the 1600F NaK radiator. The net thrust, air flow and reactor power for the 1800F NaK radiator are also presented in figures.

A Hybrid Neural Network-Genetic Algorithm Technique for Aircraft Engine Performance Diagnostics

Science.gov (United States)

Kobayashi, Takahisa; Simon, Donald L.

2001-01-01

In this paper, a model-based diagnostic method, which utilizes Neural Networks and Genetic Algorithms, is investigated. Neural networks are applied to estimate the engine internal health, and Genetic Algorithms are applied for sensor bias detection and estimation. This hybrid approach takes advantage of the nonlinear estimation capability provided by neural networks while improving the robustness to measurement uncertainty through the application of Genetic Algorithms. The hybrid diagnostic technique also has the ability to rank multiple potential solutions for a given set of anomalous sensor measurements in order to reduce false alarms and missed detections. The performance of the hybrid diagnostic technique is evaluated through some case studies derived from a turbofan engine simulation. The results show this approach is promising for reliable diagnostics of aircraft engines.

Tornado missile impact study

International Nuclear Information System (INIS)

McDonald, J.R.

1991-01-01

UCRL-15910 specifies wind and tornado missiles for moderate- and high-hazard DOE facilities. Wall-barrier specimens have been tested at the Tornado Missile Impact Facility at Texas Tech University. The facility has an air-activated tornado missile cannon capable of firing 2x4 timber planks weighing 12 lb at speeds up to 150 mph and 3-in-diameter steel pipes weighing 75 lb at speeds to 7 5 mph. Wall barriers tested to date include reinforced concrete walls from 4-in. to 10-in. thick; 8-in. and 12-in. walls of reinforced concrete masonry units (CMU); two other masonry wall configurations consisting of an 8-in. CMU with a 4-in. clay-brick veneer and a 10-in. composite wall with two wythes of 4-in. clay brick. The impact test series is designed to determine the impact speed that will produce backface spall of each wall barrier. A set of 15 wall sections has been constructed and tested at this time. Preliminary finding suggest that all cells of CMU walls must be grouted to prevent missile penetration. Walls recommended in the workshop on UCRL-15910 provide acceptable protection if cracking can be accepted

Detection technique of targets for missile defense system

Science.gov (United States)

Guo, Hua-ling; Deng, Jia-hao; Cai, Ke-rong

2009-11-01

Ballistic missile defense system (BMDS) is a weapon system for intercepting enemy ballistic missiles. It includes ballistic-missile warning system, target discrimination system, anti-ballistic-missile guidance systems, and command-control communication system. Infrared imaging detection and laser imaging detection are widely used in BMDS for surveillance, target detection, target tracking, and target discrimination. Based on a comprehensive review of the application of target-detection techniques in the missile defense system, including infrared focal plane arrays (IRFPA), ground-based radar detection technology, 3-dimensional imaging laser radar with a photon counting avalanche photodiode (APD) arrays and microchip laser, this paper focuses on the infrared and laser imaging detection techniques in missile defense system, as well as the trends for their future development.

HOMA: Israel's National Missile Defense Strategy (Abridged Version)

National Research Council Canada - National Science Library

Lailari, Guermantes

2002-01-01

... (Hebrew for Fortress Wall), Chapter 1 discusses the fundamentals of missile defense and the reason why Israel's missile defense system affects US national security interests, Chapter 2 describes Israel's missile defense...

Model-Based Control of an Aircraft Engine using an Optimal Tuner Approach

Science.gov (United States)

Connolly, Joseph W.; Chicatelli, Amy; Garg, Sanjay

2012-01-01

This paper covers the development of a model-based engine control (MBEC) method- ology applied to an aircraft turbofan engine. Here, a linear model extracted from the Commercial Modular Aero-Propulsion System Simulation 40,000 (CMAPSS40k) at a cruise operating point serves as the engine and the on-board model. The on-board model is up- dated using an optimal tuner Kalman Filter (OTKF) estimation routine, which enables the on-board model to self-tune to account for engine performance variations. The focus here is on developing a methodology for MBEC with direct control of estimated parameters of interest such as thrust and stall margins. MBEC provides the ability for a tighter control bound of thrust over the entire life cycle of the engine that is not achievable using traditional control feedback, which uses engine pressure ratio or fan speed. CMAPSS40k is capable of modeling realistic engine performance, allowing for a verification of the MBEC tighter thrust control. In addition, investigations of using the MBEC to provide a surge limit for the controller limit logic are presented that could provide benefits over a simple acceleration schedule that is currently used in engine control architectures.

A New Approach to Modeling the Cost of Ownership for Aircraft Systems.

Science.gov (United States)

1981-08-01

expensive airborne missiles (e.g., Maverick, SRAM ) are funded in separate program elements of their own. If an aircraft system generates requirements for...PNTS b-I p,y,b,u EIR -u p9Y RTOK (FH/MO)QPA pUF PREPGNp ( - DCR) ) BUE b pp PGEN~)~1b-I ~ SER. = SEt. SEF j J,y j CIDM - CIDMP + CIDME + CIDMEI

Applying Best Practices to Military Commercial-Derivative Aircraft Engine Sustainment: Assessment of Using Parts Manufacturer Approval (PMA) Parts and Designated Engineering Representative (DER) Repairs

Science.gov (United States)

2016-01-01

savings through greater use of non-OEM alternate parts and services 5 According to Broderick (2013), the FAA developed regulations governing PMA parts...when operators of surplus military aircraft wanted to keep them operat- ing safely and the OEMs were no longer making new parts ( Broderick , 2013...of the world’s aircraft and engines will be leased by the year 2020 (Sean Broderick , 2014). Categorization of Risks of Greater Use of PMA Parts and

Aerodynamic Performance Predictions of a SA- 2 Missile Using Missile DATCOM

Science.gov (United States)

2009-09-01

transformation that is given by Eqs. (4) and (5). Eqs. (8)–(10) show the formulation in the body and wind axis terminology. 2,0D AC C kC   L (8) 10 cos...by Teo (2008) using Missile LAB code. However, the missile geometry then was set up from a rudimentary drawing and not one that represented a high...provided by MSIC. These particular cases were run forcing turbulent flow with a surface roughness of 0.001016 cm, which was found by Teo (2008) to

A review of electromagnetic missiles

International Nuclear Information System (INIS)

Wu, T.T.; Shen, H.M.; Myers, J.M.

1988-01-01

Theoretical results are reviewed pertaining to the behavior of transient electromagnetic fields in the limit of great distances from their sources. In 1985 it was shown that pulses of finite total radiated energy could propagate to a distant receiver, delivering energy that decreases much more slowly than the usual r - 2 . Such pulses have been referred to as electromagnetic (EM) missiles. The types first discovered propagate along a straight line with a monotonically (though slowly) decreasing time-integrated flux. Other types are now known. One type can be made to rise and fall with increasing distance; another is the curved EM missile. Early efforts to classify EM missiles are reviewed

Welding of High-Strength Steels for Aircraft and Missile Applications

Science.gov (United States)

1959-10-12

the aircraft industry for years. The alloys that have been most widely used have been AISI 4130, 4140 , and 4340. However, only the AISI 4340 steel...MARTENSITIC STEELS ................. . .. . . . 6 AISI 4340 and AMS 6434 ..................... ....................... 7 Welding Procedures...metal. A survey of the procedures currently being used is presented. Low-Alloy Martensitic Steels AISI 4340, AMS 6434, XZOO, 300M, and 17-Z2AS all are

Aerodynamic Engine/Airframe Integration for High Performance Aircraft and Missiles (L’Integration Aerodynamique des Moteurs et des Cellules dans les Avions et les Missiles a Hautes Performances)

Science.gov (United States)

1992-09-01

baisse du niveas da plateau supersonique (Fig.9). L’onde de choc DCZ 0,30 0068avance de 1% dc Ia corde ci cc dilplacement ye rilperesic sur toute CX 104...propulsion component, which is very helpful for a better understanding of the underlying pheno- mena and finding possible areas of improve- men t.I...of excessive, and for a plane and plug nozzle of a hypersonic aircraft, for probably prohibitive, fine meshes. It has to be men - a highly integrated

Problems and proposed solution in evaluating tornado-borne missile speed

International Nuclear Information System (INIS)

Eguchi, Yuzuru; Sugimoto, Soichiro; Hattori, Yasuo; Hirakuchi, Hiromaru

2014-01-01

Large variation was found among the design values of tornado missile speed shown in current standards and guides in Japan and U.S. It was also found that the design missile speed indicated in the Guide issued by the Nuclear Regulation Authority of Japan is the most restrictive among them. The primary reason is due to the evaluation method where all the objects are unconditionally assumed to be placed in air as high as 40 m, even if the object should be on the ground. In order to solve this problem, the authors have adopted the tornado engineering model DBT-77 proposed by Dr. Fujita as a wind field model, and developed a numerical analysis code TONBOS with adding an object liftoff model. The effectiveness of the numerical analysis code was demonstrated by simulating liftoff and flight of a truck struck by an F3 tornado in Saroma. (author)

Turbine-missile casing exit tests

International Nuclear Information System (INIS)

Yoshimura, H.R.; Sliter, G.E.

1978-01-01

Nuclear power plant designers are required to provide safety-related components with adequate protection against hypothetical turbine-missile impacts. In plants with a ''peninsula'' arrangement, protection is provided by installing the turbine axis radially from the reactor building, so that potential missile trajectories are not in line with the plant. In plants with a ''non-peninsula'' arrangement (turbine axis perpendicular to a radius), designers rely on the low probability of a missile strike and on the protection provided by reinforced concrete walls in order to demonstrate an adequate level of protection USNRC Regulatory Guide 1.115). One of the critical first steps in demonstrating adequacy is the determination of the energy and spin of the turbine segments as they exit the turbine casing. The spin increases the probability that a subsequent impact with a protective barrier will be off-normal and therefore less severe than the normal impact assumed in plant designs. Two full-scale turbine-missile casing exit tests which were conducted by Sandia Laboratories at their rocket-sled facility in Albuquerque, New Mexico, are described. Because of wide variations in turbine design details, postulated failure conditions, and missile exit scenarios, the conditions for the two tests were carefully selected to be as prototypical as possible, while still maintaining the well-controlled and well-characterized test conditions needed for generating benchmark data

Analyzing and designing object-oriented missile simulations with concurrency

Science.gov (United States)

Randorf, Jeffrey Allen

2000-11-01

A software object model for the six degree-of-freedom missile modeling domain is presented. As a precursor, a domain analysis of the missile modeling domain was started, based on the Feature-Oriented Domain Analysis (FODA) technique described by the Software Engineering Institute (SEI). It was subsequently determined the FODA methodology is functionally equivalent to the Object Modeling Technique. The analysis used legacy software documentation and code from the ENDOSIM, KDEC, and TFrames 6-DOF modeling tools, including other technical literature. The SEI Object Connection Architecture (OCA) was the template for designing the object model. Three variants of the OCA were considered---a reference structure, a recursive structure, and a reference structure with augmentation for flight vehicle modeling. The reference OCA design option was chosen for maintaining simplicity while not compromising the expressive power of the OMT model. The missile architecture was then analyzed for potential areas of concurrent computing. It was shown how protected objects could be used for data passing between OCA object managers, allowing concurrent access without changing the OCA reference design intent or structure. The implementation language was the 1995 release of Ada. OCA software components were shown how to be expressed as Ada child packages. While acceleration of several low level and other high operations level are possible on proper hardware, there was a 33% degradation of 4th order Runge-Kutta integrator performance of two simultaneous ordinary differential equations using Ada tasking on a single processor machine. The Defense Department's High Level Architecture was introduced and explained in context with the OCA. It was shown the HLA and OCA were not mutually exclusive architectures, but complimentary. HLA was shown as an interoperability solution, with the OCA as an architectural vehicle for software reuse. Further directions for implementing a 6-DOF missile modeling

Engineering assessment of in situ sulfate production onboard aircraft at high altitude

Science.gov (United States)

Smith, J.; Dykema, J. A.; Keith, D.

2016-12-01

Stratospheric injection of scattering aerosols has been proposed as a way to reduce global temperature increases by decreasing net atmospheric radiative forcing. Several methods have been suggested as a means of implementing solar geoengineering, and high altitude aircraft have been identified as an accessible means delivering sulfate aerosols to the lower and mid-stratosphere. This research initiative analyzes the design features of an onboard open cycle chemical plant capable of in situ sulfur to sulfate conversion, and compares the required mass to that of transporting pre-fabricated gaseous or liquid sulfate aerosol precursors. Scaling from aero-derivative gas turbine engines, commercial catalytic converters, and existing aerospace materials indicate that aircraft equipped with such a system could provide a substantial mass benefit compared to direct transport of compound sulfate products.

Laser Options for National Missile Defense

National Research Council Canada - National Science Library

Leonard, Steven

1998-01-01

The Cold War threat that was characterized by a USSR launch of a large number of ballistic missiles towards the United States has been replaced today by an even less stable ballistic missile security environment...

Lightweight two-stroke cycle aircraft diesel engine technology enablement program, volume 1

Science.gov (United States)

Freen, P. D.; Berenyi, S. G.; Brouwers, A. P.; Moynihan, M. E.

1985-01-01

An experimental Single Cylinder Test Engine Program is conducted to confirm the analytically projected performance of a two-stroke cycle diesel engine for aircraft applications. The test engine delivered 78kW indicated power from 1007cc displacement, operating at 3500 RPM on Schnuerle loop scavenged two-stroke cycle. Testing confirms the ability of a proposed 4-cylinder version of such an engine to reach the target power at altitude, in a highly turbocharged configuration. The experimental program defines all necessary parameters to permit design of a multicylinder engine for eventual flight applications; including injection system requirement, turbocharging, heat rejection, breathing, scavenging, and structural requirements. The multicylinder engine concept is configured to operate with an augmented turbocharger, but with no primary scavenge blower. The test program is oriented to provide a balanced turbocharger compressor to turbine power balance without an auxiliary scavenging system. Engine cylinder heat rejection to the ambient air has been significantly reduced and the minimum overall turbocharger efficiency required is within the range of commercially available turbochargers. Analytical studies and finite element modeling is made of insulated configurations of the engines - including both ceramic and metallic versions. A second generation test engine is designed based on current test results.

Probabilistic assessment of tornado-borne missile speeds. Final report

International Nuclear Information System (INIS)

Simiu, E.; Cordes, M.R.

1980-09-01

A procedure was developed for estimating speeds with which postulated missiles hit any given set of targets in a nuclear power plant or similar installation. Hit speeds corresponding to probabilities of occurrence of .0000001 were calculated for a given nuclear power plant under various assumptions concerning the magnitude of the force opposing missile take-off, direction of tornado axis of translation, number and location of missiles, and size of target area. The results of the calculations are shown to depend upon the parameters: CDA/m, where CD = drag coefficient, A = projected area, m = mass of missiles, and the ratio, k, between the minimum aerodynamic force required to cause missile take-off, and the weight of the missile

Probabilistic methodology for turbine missile risk analysis

International Nuclear Information System (INIS)

Twisdale, L.A.; Dunn, W.L.; Frank, R.A.

1984-01-01

A methodology has been developed for estimation of the probabilities of turbine-generated missile damage to nuclear power plant structures and systems. Mathematical models of the missile generation, transport, and impact events have been developed and sequenced to form an integrated turbine missile simulation methodology. Probabilistic Monte Carlo techniques are used to estimate the plant impact and damage probabilities. The methodology has been coded in the TURMIS computer code to facilitate numerical analysis and plant-specific turbine missile probability assessments. Sensitivity analyses have been performed on both the individual models and the integrated methodology, and probabilities have been estimated for a hypothetical nuclear power plant case study. (orig.)

Aircraft gas turbines

Energy Technology Data Exchange (ETDEWEB)

Arai, M [Kawasaki Heavy Industries Ltd., Kobe (Japan)

1995-03-01

Recently the international relationship has been playing an important role in the research, development and production of the aircraft gas turbine. The YSX, which is supposed to be the 100-seat class commercial aircraft, has been planned by Japan Aircraft Development (JADC) as an international cooperative project. Recently many western aeroengine companies have offered the collaboration of small turbofan engines which would be installed on YSX to Japanese aeroengine companies (IHI, KHI and MHI). The YSX is powered by 16,000-20,000 1bs thrust class engines. As for medium turbofan engine (V2500), the V 2500 family of 22,000 to 30,000 1bs thrust has been developed since 1983 through international collaboration by seven aeroengine companies in five nations. In this paper, the recent Japan`s activities of the research, development and production with viewing the world-wide movement, are described. 6 figs.

Civilian casualties of Iraqi ballistic missile attack to

Directory of Open Access Journals (Sweden)

Khaji Ali

2012-06-01

Full Text Available 【Abstract】Objective: To determine the pattern of causalities of Iraqi ballistic missile attacks on Tehran, the capital of Iran, during Iraq-Iran war. Methods: Data were extracted from the Army Staff Headquarters based on daily reports of Iranian army units during the war. Results: During 52 days, Tehran was stroked by 118 Al-Hussein missiles (a modified version of Scud missile. Eighty-six missiles landed in populated areas. During Iraqi missile attacks, 422 civilians died and 1 579 injured (4.9 deaths and 18.3 injuries per missile. During 52 days, 8.1 of the civilians died and 30.4 injured daily. Of the cases that died, 101 persons (24% were excluded due to the lack of information. Among the remainders, 179 (55.8% were male and 142 (44.2% were female. The mean age of the victims was 25.3 years±19.9 years. Our results show that the high accuracy of modified Scud missiles landed in crowded ar-eas is the major cause of high mortality in Tehran. The pres-ence of suitable warning system and shelters could reduce civilian casualties. Conclusion: The awareness and readiness of civilian defense forces, rescue services and all medical facilities for dealing with mass casualties caused by ballistic missile at-tacks are necessary. Key words: Mortality; War; Mass casualty incidents; Wounds and injuries

Aircraft engine sensor fault diagnostics using an on-line OBEM update method.

Directory of Open Access Journals (Sweden)

Xiaofeng Liu

Full Text Available This paper proposed a method to update the on-line health reference baseline of the On-Board Engine Model (OBEM to maintain the effectiveness of an in-flight aircraft sensor Fault Detection and Isolation (FDI system, in which a Hybrid Kalman Filter (HKF was incorporated. Generated from a rapid in-flight engine degradation, a large health condition mismatch between the engine and the OBEM can corrupt the performance of the FDI. Therefore, it is necessary to update the OBEM online when a rapid degradation occurs, but the FDI system will lose estimation accuracy if the estimation and update are running simultaneously. To solve this problem, the health reference baseline for a nonlinear OBEM was updated using the proposed channel controller method. Simulations based on the turbojet engine Linear-Parameter Varying (LPV model demonstrated the effectiveness of the proposed FDI system in the presence of substantial degradation, and the channel controller can ensure that the update process finishes without interference from a single sensor fault.

77 FR 70114 - Airworthiness Directives; Cessna Aircraft Company Airplanes

Science.gov (United States)

2012-11-23

... Aircraft Company Service Bulletin SB04-28-03, dated August 30, 2004, and Engine Fuel Return System... Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 2820, Aircraft Fuel... Modification Do not incorporate Cessna Aircraft Company Engine Fuel Return System Modification Kit MK 172-28-01...

The Challenge of Small Satellite Systems to the Space Security Environment

Science.gov (United States)

2012-03-01

Space, 1945–1995, (New York: Dodd, Mead & Company, Inc . 1984), 142. 40 Moltz, The Politics of Space Security, 93. 41William E. Burrows, Deep Black...Experimental World Circling Spaceship,” Report No. SE: 11827, Douglas Aircraft Company, Inc ., Santa Monica Plant Engineering Division, Contract WBB-038... Nike Zeus nuclear missile as a means to track and intercept targeted adversarial satellites. The commonality of antiballistic missile (ABM) and ASAT

Propulsion controlled aircraft computer

Science.gov (United States)

Cogan, Bruce R. (Inventor)

2010-01-01

A low-cost, easily retrofit Propulsion Controlled Aircraft (PCA) system for use on a wide range of commercial and military aircraft consists of an propulsion controlled aircraft computer that reads in aircraft data including aircraft state, pilot commands and other related data, calculates aircraft throttle position for a given maneuver commanded by the pilot, and then displays both current and calculated throttle position on a cockpit display to show the pilot where to move throttles to achieve the commanded maneuver, or is automatically sent digitally to command the engines directly.

The Cooperative Ballistic Missile Defence Game

NARCIS (Netherlands)

Evers, L.; Barros, A.I.; Monsuur, H.

2013-01-01

The increasing proliferation of ballistic missiles and weapons of mass destruction poses new risks worldwide. For a threatened nation and given the characteristics of this threat a layered ballistic missile defence system strategy appears to be the preferred solution. However, such a strategy

40 CFR 87.6 - Aircraft safety.

Science.gov (United States)

2010-07-01

... 40 Protection of Environment 20 2010-07-01 2010-07-01 false Aircraft safety. 87.6 Section 87.6... POLLUTION FROM AIRCRAFT AND AIRCRAFT ENGINES General Provisions § 87.6 Aircraft safety. The provisions of... met within the specified time without creating a safety hazard. ...

Prevention of heavy missiles during severe PWR accidents

International Nuclear Information System (INIS)

Krieg, R.

1994-01-01

For future pressurized water reactors, which should be designed against core melt down accidents, missiles generated inside the containment present a severe problem for its integrity. The masses and geometries of the missiles as well as their velocities may vary to a great extend. Therefore, a reliable proof of the containment integrity is very difficult. To overcome this problem the potential sources of missiles are discussed. In section 5 it is concluded that the generation of heavy missiles must be prevented. Steam explosions must not damage the reactor vessel head. Thus fragments of the head cannot become missiles endangering the containment shell. Furthermore, during a melt-through failure of the reactor vessel under high pressure the resulting forces must not catapult the whole vessel against the containment shell. Only missiles caused by hydrogen explosions might be tolerable, but shielding structures which protect the containment shell might be required. Here further investigations are necessary. Finally, measures are described showing that the generation of heavy missiles can indeed be prevented. In section 6 investigations are explained which will confirm the strength of the reactor vessel head. In section 7 a device is discussed keeping the fragments of a failing reactor vessel at its place. (author). 12 refs., 8 figs

The impact of the fuel chemical composition on volatile organic compounds emitted by an in-service aircraft gas turbine engine

Science.gov (United States)

Setyan, A.; Kuo, Y. Y.; Brem, B.; Durdina, L.; Gerecke, A. C.; Heeb, N. V.; Haag, R.; Wang, J.

2017-12-01

Aircraft emissions received increased attention recently because of the steady growth of aviation transport in the last decades. Aircraft engines substantially contribute to emissions of particulate matter and gaseous pollutants in the upper and lower troposphere. Among all the pollutants emitted by aircrafts, volatile organic compounds (VOCs) are particularly important because they are mainly emitted at ground level, posing a serious health risk for people living or working near airports. A series of measurements was performed at the aircraft engine testing facility of SR Technics (Zürich airport, Switzerland). Exhausts from an in-service turbofan engine were sampled at the engine exit plane by a multi-point sampling probe. A wide range of instruments was connected to the common sampling line to determine physico-chemical characteristics of non-volatile particulate matter and gaseous pollutants. Conventional Jet A-1 fuel was used as the base fuel, and measurements were performed with the base fuel doped with two different mixtures of aromatic compounds (Solvesso 150 and naphthalene-depleted Solvesso 150) and an alternative fuel (hydro-processed esters and fatty acids [HEFA] jet fuel). During this presentation, we will show results obtained for VOCs. These compounds were sampled with 3 different adsorbing cartridges, and analyzed by thermal desorption gas chromatography/mass spectrometry (TD-GC/MS, for Tenax TA and Carboxen 569) and by ultra-performance liquid chromatography/ mass spectrometry (UPLC/MS, for DNPH). The total VOC concentration was also measured with a flame ionization detector (FID). In addition, fuel samples were also analyzed by GC/MS, and their chemical compositions were compared to the VOCs emitted via engine exhaust. Total VOCs concentrations were highest at ground idle (>200 ppm C at 4-7% thrust), and substantially lower at high thrust (engine were mainly constituted of alkanes, oxygenated compounds, and aromatics. More than 50 % of the

Barrier design for tornado-generated missiles

International Nuclear Information System (INIS)

Kar, A.K.

1977-01-01

Nuclear power plant facilities and many other structures need protection against missiles generated by tornados and explosions. The missile impacts result in both local and overall effects on barriers or targets. The local effects are characterized by penetration, perforation and backface spalling or scabbing of the target material. The overall effects of missile impact on structural stability are commonly evaluated in terms of the flexural and shear behaviour of the target. Empirical formulas are presented to determine the local effects on concrete and steel barriers. Procedures are given for determining the design loads for overall effects. Design methods are described. (Auth.)

Barrier design for tornado-generated missiles

International Nuclear Information System (INIS)

Kar, A.K.

1977-01-01

Nuclear powerplant facilities and many other structures need protection against missiles generated by tornadoes and explosions. The missile impacts result in both local and overall effects on barriers or targets. The local effects are characterized by penetration, perforation, and backface spalling or scabbing of the target material. The overall effects of missile impact on structural stability are commonly evaluated in terms of the flexural and shear behavior of the target. Empirical formulas are presented to determine the local effects on concrete and steel barriers. Procedures are given for determining the design loads for overall effects. Design methods are described

Probabilistic risk assessment of aircraft impact on a spent nuclear fuel dry storage

Energy Technology Data Exchange (ETDEWEB)

Almomani, Belal, E-mail: balmomani@kaist.ac.kr [Department of Nuclear and Quantum Engineering, Korea Advanced Institute of Science and Technology, 291 Daehak-ro, Yuseong-gu, Daejeon 305-701 (Korea, Republic of); Lee, Sanghoon, E-mail: shlee1222@kmu.ac.kr [Department of Mechanical and Automotive Engineering, Keimyung University, Dalgubeol-daero 1095, Dalseo-gu, Daegu (Korea, Republic of); Jang, Dongchan, E-mail: dongchan.jang@kaist.ac.kr [Department of Nuclear and Quantum Engineering, Korea Advanced Institute of Science and Technology, 291 Daehak-ro, Yuseong-gu, Daejeon 305-701 (Korea, Republic of); Kang, Hyun Gook, E-mail: kangh6@rpi.edu [Department of Mechanical, Aerospace and Nuclear Engineering, Rensselaer Polytechnic Institute, Troy, NY 12180 (United States)

2017-01-15

Highlights: • A new risk assessment frame is proposed for aircraft impact into an interim dry storage. • It uses event tree analysis, response-structural analysis, consequence analysis, and Monte Carlo simulation. • A case study of the proposed procedure is presented to illustrate the methodology’s application. - Abstract: This paper proposes a systematic risk evaluation framework for one of the most significant impact events on an interim dry storage facility, an aircraft crash, by using a probabilistic approach. A realistic case study that includes a specific cask model and selected impact conditions is performed to demonstrate the practical applicability of the proposed framework. An event tree analysis of an occurred aircraft crash that defines a set of impact conditions and storage cask response is constructed. The Monte-Carlo simulation is employed for the probabilistic approach in consideration of sources of uncertainty associated with the impact loads onto the internal storage casks. The parameters for representing uncertainties that are managed probabilistically include the aircraft impact velocity, the compressive strength of the reinforced concrete wall, the missile shape factor, and the facility wall thickness. Failure probabilities of the impacted wall and a single storage cask under direct mechanical impact load caused by the aircraft crash are estimated. A finite element analysis is applied to simulate the postulated direct engine impact load onto the cask body, and a source term analysis for associated releases of radioactive materials as well as an off-site consequence analysis are performed. Finally, conditional risk contribution calculations are represented by an event tree model. Case study results indicate that no severe risk is presented, as the radiological consequences do not exceed regulatory exposure limits to the public. This risk model can be used with any other representative detailed parameters and reference design concepts for

Large eddy simulation of air pollution produced by aircraft engine emissions inside the airport

Energy Technology Data Exchange (ETDEWEB)

Synylo, Kateryna [National Aviation University (Ukraine)], email: synylo@nau.edu.ua

2011-07-01

With the increase of air traffic movement, air pollution from airport emissions has become an important concern. In the past, various research has been undertaken on the impact of aircraft engines on the upper troposphere and lower stratosphere, however the impact that emissions have on airports themselves is not taken into account by the most frequently used monitoring software programs. The aim of this paper is to present the use of a CFD simulation to determine the dynamic and fluid mechanics characteristics of aircraft emissions near the ground. The CFD simulation was carried out using Fluent 6.3 software and the effects of counter-rotating vortices and wind conditions on fulfilled gases jet. It was found that numerical simulation is able to resolve difficult equations and provide realistic results. This study demonstrated that the use of CFD computation could be used to improve local air quality modeling and assessment of the impact of aircraft emissions at airports.

Pipe missile impact experiments on concrete models

International Nuclear Information System (INIS)

McHugh, S.; Gupta, Y.; Seaman, L.

1981-06-01

The experiments described in this study are a part of SRI studies for EPRI on the local response of reinforced concrete panels to missile impacts. The objectives of this task were to determine the feasibility of using scale model tests to reproduce the impact response of reinforced concrete panels observed in full-scale tests with pipe missiles and to evaluate the effect of concrete strength on the impact response. The experimental approach consisted of replica scaling: the missile and target materials were similar to those used in the full-scale tests, with all dimensions scaled by 5/32. Four criteria were selected for comparing the scaled and full-scale test results: frontface penetration, backface scabbing threshold, internal cracking in the panel, and missile deformation

Methodology to estimate particulate matter emissions from certified commercial aircraft engines.

Science.gov (United States)

Wayson, Roger L; Fleming, Gregg G; Lovinelli, Ralph

2009-01-01

Today, about one-fourth of U.S. commercial service airports, including 41 of the busiest 50, are either in nonattainment or maintenance areas per the National Ambient Air Quality Standards. U.S. aviation activity is forecasted to triple by 2025, while at the same time, the U.S. Environmental Protection Agency (EPA) is evaluating stricter particulate matter (PM) standards on the basis of documented human health and welfare impacts. Stricter federal standards are expected to impede capacity and limit aviation growth if regulatory mandated emission reductions occur as for other non-aviation sources (i.e., automobiles, power plants, etc.). In addition, strong interest exists as to the role aviation emissions play in air quality and climate change issues. These reasons underpin the need to quantify and understand PM emissions from certified commercial aircraft engines, which has led to the need for a methodology to predict these emissions. Standardized sampling techniques to measure volatile and nonvolatile PM emissions from aircraft engines do not exist. As such, a first-order approximation (FOA) was derived to fill this need based on available information. FOA1.0 only allowed prediction of nonvolatile PM. FOA2.0 was a change to include volatile PM emissions on the basis of the ratio of nonvolatile to volatile emissions. Recent collaborative efforts by industry (manufacturers and airlines), research establishments, and regulators have begun to provide further insight into the estimation of the PM emissions. The resultant PM measurement datasets are being analyzed to refine sampling techniques and progress towards standardized PM measurements. These preliminary measurement datasets also support the continued refinement of the FOA methodology. FOA3.0 disaggregated the prediction techniques to allow for independent prediction of nonvolatile and volatile emissions on a more theoretical basis. The Committee for Aviation Environmental Protection of the International Civil

Time-to-impact estimation in passive missile warning systems

Science.gov (United States)

Şahıngıl, Mehmet Cihan

2017-05-01

A missile warning system can detect the incoming missile threat(s) and automatically cue the other Electronic Attack (EA) systems in the suit, such as Directed Infrared Counter Measure (DIRCM) system and/or Counter Measure Dispensing System (CMDS). Most missile warning systems are currently based on passive sensor technology operating in either Solar Blind Ultraviolet (SBUV) or Midwave Infrared (MWIR) bands on which there is an intensive emission from the exhaust plume of the threatening missile. Although passive missile warning systems have some clear advantages over pulse-Doppler radar (PDR) based active missile warning systems, they show poorer performance in terms of time-to-impact (TTI) estimation which is critical for optimizing the countermeasures and also "passive kill assessment". In this paper, we consider this problem, namely, TTI estimation from passive measurements and present a TTI estimation scheme which can be used in passive missile warning systems. Our problem formulation is based on Extended Kalman Filter (EKF). The algorithm uses the area parameter of the threat plume which is derived from the used image frame.

Unmanned Aerial Aircraft Systems for transportation engineering: Current practice and future challenges

Directory of Open Access Journals (Sweden)

Emmanouil N. Barmpounakis

2016-10-01

Full Text Available Acquiring and processing video streams from static cameras has been proposed as one of the most efficient tools for visualizing and gathering traffic information. With the latest advances in technology and visual media, combined with the increased needs in dealing with congestion more effectively and directly, the use of Unmanned Aerial Aircraft Systems (UAS has emerged in the field of traffic engineering. In this paper, we review studies and applications that incorporate UAS in transportation research and practice with the aim to set the grounds from the proper understanding and implementation of UAS related surveillance systems in transportation and traffic engineering. The studies reviewed are categorized in different transportation engineering areas. Additional significant applications from other research fields are also referenced to identify other promising applications. Finally, issues and emerging challenges in both a conceptual and methodological level are revealed and discussed.

Air-sampling inlet contamination by aircraft emissions on the NASA CV-990 aircraft

Science.gov (United States)

Condon, E. P.; Vedder, J. F.

1984-01-01

Results of an experimental investigation of the contamination of air sampling inlets by aircraft emissions from the NASA CV-990 research aircraft are presented. This four-engine jet aircraft is a NASA facility used for many different atmospheric and meteorological experiments, as well as for developing spacecraft instrumentation for remote measurements. Our investigations were performed to provide information on which to base the selection of sampling locations for a series of multi-instrument missions for measuring tropospheric trace gases. The major source of contamination is the exhaust from the jet engines, which generate many of the same gases that are of interest in atmospheric chemistry, as well as other gases that may interfere with sampling measurements. The engine exhaust contains these gases in mixing ratios many orders of magnitude greater than those that occur in the clean atmosphere which the missions seek to quantify. Pressurized samples of air were collected simultaneously from a scoop located forward of the engines to represent clean air and from other multiport scoops at various aft positions on the aircraft. The air samples were analyzed in the laboratory by gas chromatography for carbon monoxide, an abundant combustion by-product. Data are presented for various scoop locations under various flight conditions.

33 CFR 334.1440 - Pacific Ocean at Kwajalein Atoll, Marshall Islands; missile testing area.

Science.gov (United States)

2010-07-01

... 33 Navigation and Navigable Waters 3 2010-07-01 2010-07-01 false Pacific Ocean at Kwajalein Atoll, Marshall Islands; missile testing area. 334.1440 Section 334.1440 Navigation and Navigable Waters CORPS OF ENGINEERS, DEPARTMENT OF THE ARMY, DEPARTMENT OF DEFENSE DANGER ZONE AND RESTRICTED AREA REGULATIONS § 334.1440 Pacific Ocean at Kwajalein...

The science, technology, and politics of ballistic missile defense

Science.gov (United States)

Coyle, Philip E.

2014-05-01

America's missile defense systems are deployed at home and abroad. This includes the Groundbased Missile Defense (GMD) system in Alaska and California, the Phased Adaptive Approach in Europe (EPAA), and regional systems in the Middle East and Asia. Unfortunately these systems lack workable architectures, and many of the required elements either don't work or are missing. Major review and reconsideration is needed of all elements of these systems. GMD performance in tests has gotten worse with time, when it ought to be getting better. A lack of political support is not to blame as the DoD spends about 10 billion per year, and proposes to add about 5 billion over the next five years. Russia objects to the EPAA as a threat to its ICBM forces, and to the extensive deployment of U.S. military forces in countries such as Poland, the Czech Republic and Romania, once part of the Soviet Union. Going forward the U.S. should keep working with Russia whose cooperation will be key to diplomatic gains in the Middle East and elsewhere. Meanwhile, America's missile defenses face an enduring set of issues, especially target discrimination in the face of attacks designed to overwhelm the defenses, stage separation debris, chaff, decoys, and stealth. Dealing with target discrimination while also replacing, upgrading, or adding to the many elements of U.S. missiles defenses presents daunting budget priorities. A new look at the threat is warranted, and whether the U.S. needs to consider every nation that possesses even short-range missiles a threat to America. The proliferation of missiles of all sizes around the world is a growing problem, but expecting U.S. missile defenses to deal with all those missiles everywhere is unrealistic, and U.S. missile defenses, effective or not, are justifying more and more offensive missiles.

The science, technology, and politics of ballistic missile defense

International Nuclear Information System (INIS)

Coyle, Philip E.

2014-01-01

America's missile defense systems are deployed at home and abroad. This includes the Groundbased Missile Defense (GMD) system in Alaska and California, the Phased Adaptive Approach in Europe (EPAA), and regional systems in the Middle East and Asia. Unfortunately these systems lack workable architectures, and many of the required elements either don't work or are missing. Major review and reconsideration is needed of all elements of these systems. GMD performance in tests has gotten worse with time, when it ought to be getting better. A lack of political support is not to blame as the DoD spends about $10 billion per year, and proposes to add about $5 billion over the next five years. Russia objects to the EPAA as a threat to its ICBM forces, and to the extensive deployment of U.S. military forces in countries such as Poland, the Czech Republic and Romania, once part of the Soviet Union. Going forward the U.S. should keep working with Russia whose cooperation will be key to diplomatic gains in the Middle East and elsewhere. Meanwhile, America's missile defenses face an enduring set of issues, especially target discrimination in the face of attacks designed to overwhelm the defenses, stage separation debris, chaff, decoys, and stealth. Dealing with target discrimination while also replacing, upgrading, or adding to the many elements of U.S. missiles defenses presents daunting budget priorities. A new look at the threat is warranted, and whether the U.S. needs to consider every nation that possesses even short-range missiles a threat to America. The proliferation of missiles of all sizes around the world is a growing problem, but expecting U.S. missile defenses to deal with all those missiles everywhere is unrealistic, and U.S. missile defenses, effective or not, are justifying more and more offensive missiles

The science, technology, and politics of ballistic missile defense

Energy Technology Data Exchange (ETDEWEB)

Coyle, Philip E. [Center for Arms Control and Non-Proliferation, Washington, DC (United States)

2014-05-09

America's missile defense systems are deployed at home and abroad. This includes the Groundbased Missile Defense (GMD) system in Alaska and California, the Phased Adaptive Approach in Europe (EPAA), and regional systems in the Middle East and Asia. Unfortunately these systems lack workable architectures, and many of the required elements either don't work or are missing. Major review and reconsideration is needed of all elements of these systems. GMD performance in tests has gotten worse with time, when it ought to be getting better. A lack of political support is not to blame as the DoD spends about $10 billion per year, and proposes to add about $5 billion over the next five years. Russia objects to the EPAA as a threat to its ICBM forces, and to the extensive deployment of U.S. military forces in countries such as Poland, the Czech Republic and Romania, once part of the Soviet Union. Going forward the U.S. should keep working with Russia whose cooperation will be key to diplomatic gains in the Middle East and elsewhere. Meanwhile, America's missile defenses face an enduring set of issues, especially target discrimination in the face of attacks designed to overwhelm the defenses, stage separation debris, chaff, decoys, and stealth. Dealing with target discrimination while also replacing, upgrading, or adding to the many elements of U.S. missiles defenses presents daunting budget priorities. A new look at the threat is warranted, and whether the U.S. needs to consider every nation that possesses even short-range missiles a threat to America. The proliferation of missiles of all sizes around the world is a growing problem, but expecting U.S. missile defenses to deal with all those missiles everywhere is unrealistic, and U.S. missile defenses, effective or not, are justifying more and more offensive missiles.

76 FR 9963 - Airworthiness Directives; Thielert Aircraft Engines GmbH Models TAE 125-02-99 and TAE 125-02-114...

Science.gov (United States)

2011-02-23

... Airworthiness Directives; Thielert Aircraft Engines GmbH Models TAE 125-02-99 and TAE 125-02-114 Reciprocating... TAE 125-02-99 and TAE 125-02-114 reciprocating engines installed in, but not limited to, Cessna 172... occurs later. Repetitive Replacements of Timing Chains for All TAE 125-02-99 and TAE 125-02-114 Engines...

MD-11 PCA - View of aircraft on ramp

Science.gov (United States)

1995-01-01

This McDonnell Douglas MD-11 is taxiing to a position on the flightline at NASA's Dryden Flight Research Center, Edwards, California, following its completion of the first and second landings ever performed by a transport aircraft under engine power only (on Aug. 29, 1995). The milestone flight, with NASA research pilot and former astronaut Gordon Fullerton at the controls, was part of a NASA project to develop a computer-assisted engine control system that enables a pilot to land a plane safely when its normal control surfaces are disabled. The Propulsion-Controlled Aircraft (PCA) system uses standard autopilot controls already present in the cockpit, together with the new programming in the aircraft's flight control computers. The PCA concept is simple. For pitch control, the program increases thrust to climb and reduces thrust to descend. To turn right, the autopilot increases the left engine thrust while decreasing the right engine thrust. The initial Propulsion-Controlled Aircraft studies by NASA were carried out at Dryden with a modified twin-engine F-15 research aircraft.

Numerical simulation of tornado-borne missile impact

International Nuclear Information System (INIS)

Tu, D.K.; Murray, R.C.

1977-01-01

The feasibility of using a finite element procedure to examine the impact phenomenon of a tornado-borne missile impinging on a reinforced concrete barrier was assessed. The major emphasis of this study was to simulate the impact of a nondeformable missile. Several series of simulations were run, using an 8-in.-dia steel slug as the impacting missile. The numerical results were then compared with experimental field tests and empirical formulas. The work is in support of tornado design practices for fuel reprocessing and fuel fabrication plants

A Dynamic Model for the Evaluation of Aircraft Engine Icing Detection and Control-Based Mitigation Strategies

Science.gov (United States)

Simon, Donald L.; Rinehart, Aidan W.; Jones, Scott M.

2017-01-01

Aircraft flying in regions of high ice crystal concentrations are susceptible to the buildup of ice within the compression system of their gas turbine engines. This ice buildup can restrict engine airflow and cause an uncommanded loss of thrust, also known as engine rollback, which poses a potential safety hazard. The aviation community is conducting research to understand this phenomena, and to identify avoidance and mitigation strategies to address the concern. To support this research, a dynamic turbofan engine model has been created to enable the development and evaluation of engine icing detection and control-based mitigation strategies. This model captures the dynamic engine response due to high ice water ingestion and the buildup of ice blockage in the engines low pressure compressor. It includes a fuel control system allowing engine closed-loop control effects during engine icing events to be emulated. The model also includes bleed air valve and horsepower extraction actuators that, when modulated, change overall engine operating performance. This system-level model has been developed and compared against test data acquired from an aircraft turbofan engine undergoing engine icing studies in an altitude test facility and also against outputs from the manufacturers customer deck. This paper will describe the model and show results of its dynamic response under open-loop and closed-loop control operating scenarios in the presence of ice blockage buildup compared against engine test cell data. Planned follow-on use of the model for the development and evaluation of icing detection and control-based mitigation strategies will also be discussed. The intent is to combine the model and control mitigation logic with an engine icing risk calculation tool capable of predicting the risk of engine icing based on current operating conditions. Upon detection of an operating region of risk for engine icing events, the control mitigation logic will seek to change the

Dynamic Response Analysis of Storage Cask Lid Structure Subjected to Lateral Impact Load of Aircraft Engine Crash

International Nuclear Information System (INIS)

Almomania, Belal; Kang, Hyun Gook; Lee, Sanghoon

2015-01-01

Several numerical methods and tests have been carried out to measure the capability of storage cask to withstand extreme impact loads. Testing methods are often constrained by cost, and difficulty in preparation for several impact conditions with different applied loads, and areas of impact. Instead, analytic method is an acceptable process that can easily apply different impact conditions for the evaluation of cask integrity. The aircraft engine impact is considered as one of the most critical impact accidents on the storage cask that significantly affects onto the lid closure system and may cause a considerable release of radioactive materials. This paper presents a method for evaluating the dynamic responses of one upper metal cask lid closure without impact limiters subjected to lateral impact of an aircraft engine with respect to variation of the impact velocity. An assessment method to predict damage response due to the lateral engine impact onto metal storage cask has been studied by using computer code LS-DYNA. The dynamic behavior of the lid movements was successfully calculated by utilizing a simplified finite element cask model, which showed a good agreement with the previous research. The simulation analyses results showed that no significant plastic deformation for bolts, lid, and the cask body. In this study, the lid opening and sliding displacements are considered as the major factors in initiating the leakage path. This analysis may be useful for evaluating the instantaneous leakage rates in a connection with the sliding and opening displacements between the lid and the flange to ensure that the radiological consequences caused by an aircraft engine crash accident during the storage phase are within the permissible level

Dynamic Response Analysis of Storage Cask Lid Structure Subjected to Lateral Impact Load of Aircraft Engine Crash

Energy Technology Data Exchange (ETDEWEB)

Almomania, Belal; Kang, Hyun Gook [KAIST, Daejeon (Korea, Republic of); Lee, Sanghoon [Keimyung Univ., Daegu (Korea, Republic of)

2015-10-15

Several numerical methods and tests have been carried out to measure the capability of storage cask to withstand extreme impact loads. Testing methods are often constrained by cost, and difficulty in preparation for several impact conditions with different applied loads, and areas of impact. Instead, analytic method is an acceptable process that can easily apply different impact conditions for the evaluation of cask integrity. The aircraft engine impact is considered as one of the most critical impact accidents on the storage cask that significantly affects onto the lid closure system and may cause a considerable release of radioactive materials. This paper presents a method for evaluating the dynamic responses of one upper metal cask lid closure without impact limiters subjected to lateral impact of an aircraft engine with respect to variation of the impact velocity. An assessment method to predict damage response due to the lateral engine impact onto metal storage cask has been studied by using computer code LS-DYNA. The dynamic behavior of the lid movements was successfully calculated by utilizing a simplified finite element cask model, which showed a good agreement with the previous research. The simulation analyses results showed that no significant plastic deformation for bolts, lid, and the cask body. In this study, the lid opening and sliding displacements are considered as the major factors in initiating the leakage path. This analysis may be useful for evaluating the instantaneous leakage rates in a connection with the sliding and opening displacements between the lid and the flange to ensure that the radiological consequences caused by an aircraft engine crash accident during the storage phase are within the permissible level.

CAD system of design and engineering provision of die forming of compressor blades for aircraft engines

Science.gov (United States)

Khaimovich, I. N.

2017-10-01

The articles provides the calculation algorithms for blank design and die forming fitting to produce the compressor blades for aircraft engines. The design system proposed in the article allows generating drafts of trimming and reducing dies automatically, leading to significant reduction of work preparation time. The detailed analysis of the blade structural elements features was carried out, the taken limitations and technological solutions allowed forming generalized algorithms of forming parting stamp face over the entire circuit of the engraving for different configurations of die forgings. The author worked out the algorithms and programs to calculate three dimensional point locations describing the configuration of die cavity. As a result the author obtained the generic mathematical model of final die block in the form of three-dimensional array of base points. This model is the base for creation of engineering documentation of technological equipment and means of its control.

A Simple Two Aircraft Conflict Resolution Algorithm

Science.gov (United States)

Chatterji, Gano B.

2006-01-01

Conflict detection and resolution methods are crucial for distributed air-ground traffic management in which the crew in, the cockpit, dispatchers in operation control centers sad and traffic controllers in the ground-based air traffic management facilities share information and participate in the traffic flow and traffic control functions. This paper describes a conflict detection, and a conflict resolution method. The conflict detection method predicts the minimum separation and the time-to-go to the closest point of approach by assuming that both the aircraft will continue to fly at their current speeds along their current headings. The conflict resolution method described here is motivated by the proportional navigation algorithm, which is often used for missile guidance during the terminal phase. It generates speed and heading commands to rotate the line-of-sight either clockwise or counter-clockwise for conflict resolution. Once the aircraft achieve a positive range-rate and no further conflict is predicted, the algorithm generates heading commands to turn back the aircraft to their nominal trajectories. The speed commands are set to the optimal pre-resolution speeds. Six numerical examples are presented to demonstrate the conflict detection, and the conflict resolution methods.

Investigation of a Verification and Validation Tool with a Turbofan Aircraft Engine Application

Science.gov (United States)

Uth, Peter; Narang-Siddarth, Anshu; Wong, Edmond

2018-01-01

The development of more advanced control architectures for turbofan aircraft engines can yield gains in performance and efficiency over the lifetime of an engine. However, the implementation of these increasingly complex controllers is contingent on their ability to provide safe, reliable engine operation. Therefore, having the means to verify the safety of new control algorithms is crucial. As a step towards this goal, CoCoSim, a publicly available verification tool for Simulink, is used to analyze C-MAPSS40k, a 40,000 lbf class turbo-fan engine model developed at NASA for testing new control algorithms. Due to current limitations of the verification software, several modifications are made to C-MAPSS40k to achieve compatibility with CoCoSim. Some of these modifications sacrifice fidelity to the original model. Several safety and performance requirements typical for turbofan engines are identified and constructed into a verification framework. Preliminary results using an industry standard baseline controller for these requirements are presented. While verification capabilities are demonstrated, a truly comprehensive analysis will require further development of the verification tool.

A Model-Based Anomaly Detection Approach for Analyzing Streaming Aircraft Engine Measurement Data

Science.gov (United States)

Simon, Donald L.; Rinehart, Aidan Walker

2015-01-01

This paper presents a model-based anomaly detection architecture designed for analyzing streaming transient aircraft engine measurement data. The technique calculates and monitors residuals between sensed engine outputs and model predicted outputs for anomaly detection purposes. Pivotal to the performance of this technique is the ability to construct a model that accurately reflects the nominal operating performance of the engine. The dynamic model applied in the architecture is a piecewise linear design comprising steady-state trim points and dynamic state space matrices. A simple curve-fitting technique for updating the model trim point information based on steadystate information extracted from available nominal engine measurement data is presented. Results from the application of the model-based approach for processing actual engine test data are shown. These include both nominal fault-free test case data and seeded fault test case data. The results indicate that the updates applied to improve the model trim point information also improve anomaly detection performance. Recommendations for follow-on enhancements to the technique are also presented and discussed.

Report of the Air-to-Air Missile System Capability Review. July-November 1968. Volume 2. Appendices

Science.gov (United States)

1969-01-01

however, effective 4o., human engineering can reduce a safety problem considerably. Much of the needed safety can be designed into the system, but...built-in test equipment for which the trend is toward highly automiated , rapid verification of the performance of the weapon control system. These...44 6 6 dE .. W E. All ag .ted areas such as training and readiness procedures, predicted • . missile envelopes, training aids, human engineering

Concept definition and aerodynamic technology studies for single-engine V/STOL fighter/attack aircraft

Science.gov (United States)

Nelms, W. P.; Durston, D. A.

1981-01-01

The results obtained in the early stages of a research program to develop aerodynamic technology for single-engine V/STOL fighter/attack aircraft projected for the post-1990 period are summarized. This program includes industry studies jointly sponsored by NASA and the Navy. Four contractors have identified promising concepts featuring a variety of approaches for providing propulsive lift. Vertical takeoff gross weights range from about 10,000 to 13,600 kg (22,000 to 30,000 lb). The aircraft have supersonic capability, are highly maneuverable, and have significant short takeoff overload capability. The contractors have estimated the aerodynamics and identified aerodynamic uncertainties associated with their concepts. Wind-tunnel research programs will be formulated to investigate these uncertainties. A description of the concepts is emphasized.

MODELING THE FLIGHT TRAJECTORY OF OPERATIONAL-TACTICAL BALLISTIC MISSILES

Directory of Open Access Journals (Sweden)

I. V. Filipchenko

2018-01-01

Full Text Available The article gives the basic approaches to updating the systems of combat operations modeling in the part of enemy missile attack simulation taking into account the possibility of tactical ballistic missile maneuvering during the flight. The results of simulation of combat tactical missile defense operations are given. 

The Threat from European Missile Defence System to Russian National Security

Directory of Open Access Journals (Sweden)

Alexey I. Podberezkin

2014-01-01

Full Text Available The article analyses the political and military aspects of progress in the dialogue between Russia and the U.S./NATO on cooperation in missile defense; investigates the past experiences and current state of cooperation between Russia and the Alliance on missile defense issues; examines the technical features of American missile defence systems today; finds a solution to question whether or not the European Missile Defence Program actually threatens Russia's nuclear deterrent and strategic stability in general; identifies both potential benefits and possible losses for Russia stemming from the development of cooperation with the United States and NATO in countering ballistic missile threats, or from refusal to have such cooperation. Evidently, the initiative of creation of a missile defense in Europe surely belongs to the USA. Washington has enormous technological, financial, economic, military and institutional capabilities in the field of a missile defense, exceeding by far other NATO member-states. In February 2010, the President of the United States B. Obama adopted a project "European Phased Adaptive Approach" (EPAA as an alternative to G. Bush's global strategic missile defense plan. The first two stages of the Phased Adaptive Approach are focused on creating a system capable of intercepting small, medium and intermediate-range ballistic missiles. The possibility of intercepting long-range missiles is postponed to the third (2018 and forth phases (2020. Moscow finds especially troublesome the third and the fourth phases of Washington's project of creating a European segment of the global antiballistic missile system, considering prospective capabilities of the U.S. interceptor missiles 61 and the envisioned areas of their deployment. The U.S. counter-evidence is that phase four interceptors do not exist yet. Russia insists on getting the political and legal guarantees from the U.S. and NATO that their missile defense systems will not slash

Alternate Fuels for Use in Commercial Aircraft

Science.gov (United States)

Daggett, David L.; Hendricks, Robert C.; Walther, Rainer; Corporan, Edwin

2008-01-01

The engine and aircraft Research and Development (R&D) communities have been investigating alternative fueling in near-term, midterm, and far-term aircraft. A drop in jet fuel replacement, consisting of a kerosene (Jet-A) and synthetic fuel blend, will be possible for use in existing and near-term aircraft. Future midterm aircraft may use a biojet and synthetic fuel blend in ultra-efficient airplane designs. Future far-term engines and aircraft in 50-plus years may be specifically designed to use a low- or zero-carbon fuel. Synthetic jet fuels from coal, natural gas, or other hydrocarbon feedstocks are very similar in performance to conventional jet fuel, yet the additional CO2 produced during the manufacturing needs to be permanently sequestered. Biojet fuels need to be developed specifically for jet aircraft without displacing food production. Envisioned as midterm aircraft fuel, if the performance and cost liabilities can be overcome, biofuel blends with synthetic jet or Jet-A fuels have near-term potential in terms of global climatic concerns. Long-term solutions address dramatic emissions reductions through use of alternate aircraft fuels such as liquid hydrogen or liquid methane. Either of these new aircraft fuels will require an enormous change in infrastructure and thus engine and airplane design. Life-cycle environmental questions need to be addressed.

Aircraft Control Using Engine Thrust: A History of Learning TOC Real-Time

Science.gov (United States)

Cole, Jennifer H.; Batteas, Frank; Fullerton, Gordon

2006-01-01

A history of learning the operation of Throttles Only Control (TOC) to control an aircraft in real time using engine thrust is shown. The topics include: 1) Past TOC Accidents/Incidents; 2) 1972: DC-10 American Airlines; 3) May 1974: USAF B-52H; 4) April 1975: USAF C-5A; 5) April 1975: USAF C-5A; 6) 1981: USAF B-52G; 7) August 1985: JAL 123 B-747; 8) JAL 123 Survivor Story; 9) JAL 123 Investigation Findings; 10) July 1989: UAL 232 DC-10; 11) UAL 232 DC-10; 12) Eastwind 517 B-737; 13) November 2003: DHL A-300; 14) Historically, TOC has saved lives; 15) Automated Throttles-Only Control; 16) PCA Project; 17) Propulsion-Controlled Aircraft; 18) MD-11 PCA System and Flight Test Envelope; 19) MD-11 Simulation, PCA ILS-Soupled Landing Dispersion; 20) Throttles-Only Pitch and Roll Control Power; 21) PCA in Commercial Fleet; 22) Fall 2005: PCAR Project; 23) PCAR Background - TOC; and 24) PCAR Background - TOC.

Damage evaluation of 500 MWe Indian Pressurized Heavy Water Reactor nuclear containment for aircraft impact

Energy Technology Data Exchange (ETDEWEB)

Kukreja, Mukesh [Reactor Safety Division, Bhabha Atomic Research Centre, Trombay, Mumbai 400085 (India)]. E-mail: mrkukreja@yahoo.com

2005-08-01

Safety assessment of Indian nuclear containments has been carried out for aircraft impact. The loading time history for Boeing and Airbus categories of aircrafts is generated based on the principle of momentum transfer of crushable aircrafts. The case studies include the analysis of BWR Mark III containment as a benchmark problem and analyses of Pressurised Heavy Water Reactor containment (inner and outer containment) for impulsive loading due to aircraft impact. Initially, the load is applied on outer containment wall model and subsequently the load is transferred to inner containment after the local perforation of the outer containment wall is noticed in the transient simulation. The analysis methodology evolved in the present work would be useful for studying the behavior of double containment walls and multi barrier structural configurations for aircraft impact with higher energies. The present analysis illustrates that with the provision of double containments for Indian nuclear power plants, adequate reserve strength is available for the case of an extremely low probability event of missile impact generated due to the commercial aircrafts operated in India.

Damage evaluation of 500 MWe Indian Pressurized Heavy Water Reactor nuclear containment for aircraft impact

International Nuclear Information System (INIS)

Kukreja, Mukesh

2005-01-01

Safety assessment of Indian nuclear containments has been carried out for aircraft impact. The loading time history for Boeing and Airbus categories of aircrafts is generated based on the principle of momentum transfer of crushable aircrafts. The case studies include the analysis of BWR Mark III containment as a benchmark problem and analyses of Pressurised Heavy Water Reactor containment (inner and outer containment) for impulsive loading due to aircraft impact. Initially, the load is applied on outer containment wall model and subsequently the load is transferred to inner containment after the local perforation of the outer containment wall is noticed in the transient simulation. The analysis methodology evolved in the present work would be useful for studying the behavior of double containment walls and multi barrier structural configurations for aircraft impact with higher energies. The present analysis illustrates that with the provision of double containments for Indian nuclear power plants, adequate reserve strength is available for the case of an extremely low probability event of missile impact generated due to the commercial aircrafts operated in India

Mathematical model of an indirect action fuel flow controller for aircraft jet engines

Science.gov (United States)

Tudosie, Alexandru-Nicolae

2017-06-01

The paper deals with a fuel mass flow rate controller with indirect action for aircraft jet engines. The author has identified fuel controller's main parts and its operation mode, then, based on these observations, one has determined motion equations of each main part, which have built system's non-linear mathematical model. In order to realize a better study this model was linearised (using the finite differences method) and then adimensionalized. Based on this new form of the mathematical model, after applying Laplace transformation, the embedded system (controller+engine) was described by the block diagram with transfer functions. Some Simulink-Matlab simulations were performed, concerning system's time behavior for step input, which lead to some useful conclusions and extension possibilities.

The probability of a tornado missile hitting a target

International Nuclear Information System (INIS)

Goodman, J.; Koch, J.E.

1983-01-01

It is shown that tornado missile transportation is a diffusion Markovian process. Therefore, the Green's function method is applied for the estimation of the probability of hitting a unit target area. This propability is expressed through a joint density of tornado intensity and path area, a probability of tornado missile injection and a tornado missile height distribution. (orig.)

2015 Assessment of the Ballistic Missile Defense System (BMDS)

Science.gov (United States)

2016-04-01

Director, Operational Test and Evaluation 2015 Assessment of the Ballistic Missile Defense System (BMDS...Evaluation (DOT&E) as they pertain to the Ballistic Missile Defense System (BMDS). Congress specified these requirements in the fiscal year 2002 (FY02...systems are the Ground-based Midcourse Defense (GMD), Aegis Ballistic Missile Defense (Aegis BMD), Terminal High-Altitude Area Defense (THAAD), and

Active Combustion Control for Aircraft Gas-Turbine Engines-Experimental Results for an Advanced, Low-Emissions Combustor Prototype

Science.gov (United States)

DeLaat, John C.; Kopasakis, George; Saus, Joseph R.; Chang, Clarence T.; Wey, Changlie

2012-01-01

Lean combustion concepts for aircraft engine combustors are prone to combustion instabilities. Mitigation of instabilities is an enabling technology for these low-emissions combustors. NASA Glenn Research Center s prior activity has demonstrated active control to suppress a high-frequency combustion instability in a combustor rig designed to emulate an actual aircraft engine instability experience with a conventional, rich-front-end combustor. The current effort is developing further understanding of the problem specifically as applied to future lean-burning, very low-emissions combustors. A prototype advanced, low-emissions aircraft engine combustor with a combustion instability has been identified and previous work has characterized the dynamic behavior of that combustor prototype. The combustor exhibits thermoacoustic instabilities that are related to increasing fuel flow and that potentially prevent full-power operation. A simplified, non-linear oscillator model and a more physics-based sectored 1-D dynamic model have been developed to capture the combustor prototype s instability behavior. Utilizing these models, the NASA Adaptive Sliding Phasor Average Control (ASPAC) instability control method has been updated for the low-emissions combustor prototype. Active combustion instability suppression using the ASPAC control method has been demonstrated experimentally with this combustor prototype in a NASA combustion test cell operating at engine pressures, temperatures, and flows. A high-frequency fuel valve was utilized to perturb the combustor fuel flow. Successful instability suppression was shown using a dynamic pressure sensor in the combustor for controller feedback. Instability control was also shown with a pressure feedback sensor in the lower temperature region upstream of the combustor. It was also demonstrated that the controller can prevent the instability from occurring while combustor operation was transitioning from a stable, low-power condition to

Experimental investigation and modeling of an aircraft Otto engine operating with gasoline and heavier fuels

Science.gov (United States)

Saldivar Olague, Jose

A Continental "O-200" aircraft Otto-cycle engine has been modified to burn diesel fuel. Algebraic models of the different processes of the cycle were developed from basic principles applied to a real engine, and utilized in an algorithm for the simulation of engine performance. The simulation provides a means to investigate the performance of the modified version of the Continental engine for a wide range of operating parameters. The main goals of this study are to increase the range of a particular aircraft by reducing the specific fuel consumption of the engine, and to show that such an engine can burn heavier fuels (such as diesel, kerosene, and jet fuel) instead of gasoline. Such heavier fuels are much less flammable during handling operations making them safer than aviation gasoline and very attractive for use in flight operations from naval vessels. The cycle uses an electric spark to ignite the heavier fuel at low to moderate compression ratios, The stratified charge combustion process is utilized in a pre-chamber where the spray injection of the fuel occurs at a moderate pressure of 1200 psi (8.3 MPa). One advantage of fuel injection into the combustion chamber instead of into the intake port, is that the air-to-fuel ratio can be widely varied---in contrast to the narrower limits of the premixed combustion case used in gasoline engines---in order to obtain very lean combustion. Another benefit is that higher compression ratios can be attained in the modified cycle with heavier fuels. The combination of injection into the chamber for lean combustion, and higher compression ratios allow to limit the peak pressure in the cylinder, and to avoid engine damage. Such high-compression ratios are characteristic of Diesel engines and lead to increase in thermal efficiency without pre-ignition problems. In this experimental investigation, operations with diesel fuel have shown that considerable improvements in the fuel efficiency are possible. The results of

MD-11 PCA - Closeup view of aircraft on ramp

Science.gov (United States)

1995-01-01

This McDonnell Douglas MD-11 has taxied to a position on the flightline at NASA's Dryden Flight Research Center, Edwards, California, following its completion of the first and second landings ever performed by a transport aircraft under engine power only (on Aug. 29, 1995). The milestone flight, with NASA research pilot and former astronaut Gordon Fullerton at the controls, was part of a NASA project to develop a computer-assisted engine control system that enables a pilot to land a plane safely when its normal control surfaces are disabled. The Propulsion-Controlled Aircraft (PCA) system uses standard autopilot controls already present in the cockpit, together with the new programming in the aircraft's flight control computers. The PCA concept is simple. For pitch control, the program increases thrust to climb and reduces thrust to descend. To turn right, the autopilot increases the left engine thrust while decreasing the right engine thrust. The initial Propulsion-Controlled Aircraft studies by NASA were carried out at Dryden with a modified twin-engine F-15 research aircraft.

Small transport aircraft technology

Science.gov (United States)

Williams, L. J.

1983-01-01

Information on commuter airline trends and aircraft developments is provided to upgrade the preliminary findings of a NASA-formed small transport aircraft technology (STAT) team, established to determine whether the agency's research and development programs could help commuter aircraft manufacturers solve technical problems related to passenger acceptance and use of 19- to 50-passenger aircraft. The results and conclusions of the full set of completed STAT studies are presented. These studies were performed by five airplane manufacturers, five engine manufacturers, and two propeller manufacturers. Those portions of NASA's overall aeronautics research and development programs which are applicable to commuter aircraft design are summarized. Areas of technology that might beneficially be expanded or initiated to aid the US commuter aircraft manufacturers in the evolution of improved aircraft for the market are suggested.

Determination of tricresyl phosphate air contamination in aircraft.

Science.gov (United States)

Denola, G; Hanhela, P J; Mazurek, W

2011-08-01

Monitoring of tricresyl phosphate (TCP) contamination of cockpit air was undertaken in three types of military aircraft [fighter trainer (FT), fighter bomber (FB), and cargo transport (CT) aircraft]. The aircraft had a previous history of pilot complaints about cockpit air contamination suspected to originate from the engine bleed air supply through the entry of aircraft turbine engine oil (ATO) into the engine compressor. Air samples were collected in flight and on the ground during engine runs using sorbent tubes packed with Porapak Q and cellulose filters. A total of 78 air samples were analysed, from 46 different aircraft, and 48 samples were found to be below the limit of detection. Nine incidents of smoke/odour were identified during the study. The concentrations of toxic o-cresyl phosphate isomers were below the level of detection in all samples. The highest total TCP concentration was 51.3 μg m(-3), while most were generally found to be contamination of cabin/cockpit air has been the subject of much concern in aviation, quantitative data are sparse.

Automation of reverse engineering process in aircraft modeling and related optimization problems

Science.gov (United States)

Li, W.; Swetits, J.

1994-01-01

During the year of 1994, the engineering problems in aircraft modeling were studied. The initial concern was to obtain a surface model with desirable geometric characteristics. Much of the effort during the first half of the year was to find an efficient way of solving a computationally difficult optimization model. Since the smoothing technique in the proposal 'Surface Modeling and Optimization Studies of Aerodynamic Configurations' requires solutions of a sequence of large-scale quadratic programming problems, it is important to design algorithms that can solve each quadratic program in a few interactions. This research led to three papers by Dr. W. Li, which were submitted to SIAM Journal on Optimization and Mathematical Programming. Two of these papers have been accepted for publication. Even though significant progress has been made during this phase of research and computation times was reduced from 30 min. to 2 min. for a sample problem, it was not good enough for on-line processing of digitized data points. After discussion with Dr. Robert E. Smith Jr., it was decided not to enforce shape constraints in order in order to simplify the model. As a consequence, P. Dierckx's nonparametric spline fitting approach was adopted, where one has only one control parameter for the fitting process - the error tolerance. At the same time the surface modeling software developed by Imageware was tested. Research indicated a substantially improved fitting of digitalized data points can be achieved if a proper parameterization of the spline surface is chosen. A winning strategy is to incorporate Dierckx's surface fitting with a natural parameterization for aircraft parts. The report consists of 4 chapters. Chapter 1 provides an overview of reverse engineering related to aircraft modeling and some preliminary findings of the effort in the second half of the year. Chapters 2-4 are the research results by Dr. W. Li on penalty functions and conjugate gradient methods for

China Sanctions for Missile Proliferation: A Bureaucratic Compromise

National Research Council Canada - National Science Library

St. Amand, Gerard A

1994-01-01

On 12 August 26, 1993, the State Department announced that the United States would impose sanctions against China for transferring missile technology to Pakistan in violation of the Missile Technology Control Regime (MTCR...

Propulsion Study for Small Transport Aircraft Technology (STAT)

Science.gov (United States)

Gill, J. C.; Earle, R. V.; Staton, D. V.; Stolp, P. C.; Huelster, D. S.; Zolezzi, B. A.

1980-01-01

Propulsion requirements were determined for 0.5 and 0.7 Mach aircraft. Sensitivity studies were conducted on both these aircraft to determine parametrically the influence of propulsion characteristics on aircraft size and direct operating cost (DOC). Candidate technology elements and design features were identified and parametric studies conducted to select the STAT advanced engine cycle. Trade off studies were conducted to determine those advanced technologies and design features that would offer a reduction in DOC for operation of the STAT engines. These features were incorporated in the two STAT engines. A benefit assessment was conducted comparing the STAT engines to current technology engines of the same power and to 1985 derivatives of the current technology engines. Research and development programs were recommended as part of an overall technology development plan to ensure that full commercial development of the STAT engines could be initiated in 1988.

The proliferation of ballistic missiles: an aggravating factor of crises

International Nuclear Information System (INIS)

Rousset, Valery

2015-01-01

After a brief recall of the history of the development of ballistic missiles from World War II, the author discusses the various uses of these missiles, on the one hand by major powers, and on the other hand by other countries like Israel, Pakistan and India, and also Egypt and Iraq. He recalls the uses of these missiles during regional conflicts (Scuds by Iraq) and then discusses the issue of proliferation of ballistic missiles. He notices that most of these weapons are present in the arsenal of major powers under the form of intercontinental missiles, intermediate range weapons or theatre weapons. On the Third World side, proliferation concerns short- and medium-range missiles produced from technology transfers or national programmes. Mobile systems are now present in all conflicts (notably Libya, Syria) and are now based on more advanced technologies for propellers as well as for control and guidance systems. In the last part, the author discusses the perspectives associated with these missiles which are a strong offensive weapon, and are also modernised to carry nuclear warheads or multiple warheads. These evolutions could put the western superiority into question again

75 FR 43156 - Federal Advisory Committee; Missile Defense Advisory Committee

Science.gov (United States)

2010-07-23

... DEPARTMENT OF DEFENSE Office of the Secretary Federal Advisory Committee; Missile Defense Advisory Committee AGENCY: Missile Defense Agency (MDA), DoD. ACTION: Notice of closed meeting. SUMMARY: Under the... Defense announces that the Missile Defense Advisory Committee will meet on August 4 and 5, 2010, in...

Multi-Mode Electric Actuator Dynamic Modelling for Missile Fin Control

Directory of Open Access Journals (Sweden)

Bhimashankar Gurav

2017-06-01

Full Text Available Linear first/second order fin direct current (DC actuator model approximations for missile applications are currently limited to angular position and angular velocity state variables. Furthermore, existing literature with detailed DC motor models is decoupled from the application of interest: tail controller missile lateral acceleration (LATAX performance. This paper aims to integrate a generic DC fin actuator model with dual-mode feedforward and feedback control for tail-controlled missiles in conjunction with the autopilot system design. Moreover, the characteristics of the actuator torque information in relation to the aerodynamic fin loading for given missile trim velocities are also provided. The novelty of this paper is the integration of the missile LATAX autopilot states and actuator states including the motor torque, position and angular velocity. The advantage of such an approach is the parametric analysis and suitability of the fin actuator in relation to the missile lateral acceleration dynamic behaviour.

Weight Assessment for Fuselage Shielding on Aircraft With Open-Rotor Engines and Composite Blade Loss

Science.gov (United States)

Carney, Kelly; Pereira, Michael; Kohlman, Lee; Goldberg, Robert; Envia, Edmane; Lawrence, Charles; Roberts, Gary; Emmerling, William

2013-01-01

The Federal Aviation Administration (FAA) has been engaged in discussions with airframe and engine manufacturers concerning regulations that would apply to new technology fuel efficient "openrotor" engines. Existing regulations for the engines and airframe did not envision features of these engines that include eliminating the fan blade containment systems and including two rows of counter-rotating blades. Damage to the airframe from a failed blade could potentially be catastrophic. Therefore the feasibility of using aircraft fuselage shielding was investigated. In order to establish the feasibility of this shielding, a study was conducted to provide an estimate for the fuselage shielding weight required to provide protection from an open-rotor blade loss. This estimate was generated using a two-step procedure. First, a trajectory analysis was performed to determine the blade orientation and velocity at the point of impact with the fuselage. The trajectory analysis also showed that a blade dispersion angle of 3deg bounded the probable dispersion pattern and so was used for the weight estimate. Next, a finite element impact analysis was performed to determine the required shielding thickness to prevent fuselage penetration. The impact analysis was conducted using an FAA-provided composite blade geometry. The fuselage geometry was based on a medium-sized passenger composite airframe. In the analysis, both the blade and fuselage were assumed to be constructed from a T700S/PR520 triaxially-braided composite architecture. Sufficient test data on T700S/PR520 is available to enable reliable analysis, and also demonstrate its good impact resistance properties. This system was also used in modeling the surrogate blade. The estimated additional weight required for fuselage shielding for a wing- mounted counterrotating open-rotor blade is 236 lb per aircraft. This estimate is based on the shielding material serving the dual use of shielding and fuselage structure. If the

Hybrid PSO–SVM-based method for forecasting of the remaining useful life for aircraft engines and evaluation of its reliability

International Nuclear Information System (INIS)

García Nieto, P.J.; García-Gonzalo, E.; Sánchez Lasheras, F.; Cos Juez, F.J. de

2015-01-01

The present paper describes a hybrid PSO–SVM-based model for the prediction of the remaining useful life of aircraft engines. The proposed hybrid model combines support vector machines (SVMs), which have been successfully adopted for regression problems, with the particle swarm optimization (PSO) technique. This optimization technique involves kernel parameter setting in the SVM training procedure, which significantly influences the regression accuracy. However, its use in reliability applications has not been yet widely explored. Bearing this in mind, remaining useful life values have been predicted here by using the hybrid PSO–SVM-based model from the remaining measured parameters (input variables) for aircraft engines with success. A coefficient of determination equal to 0.9034 was obtained when this hybrid PSO–RBF–SVM-based model was applied to experimental data. The agreement of this model with experimental data confirmed its good performance. One of the main advantages of this predictive model is that it does not require information about the previous operation states of the engine. Finally, the main conclusions of this study are exposed. - Highlights: • A hybrid PSO–SVM-based model is built as a predictive model of the RUL values for aircraft engines. • The remaining physical–chemical variables in this process are studied in depth. • The obtained regression accuracy of our method is about 95%. • The results show that PSO–SVM-based model can assist in the diagnosis of the RUL values with accuracy

NPS Faculty, Students Develop Strategic Missile Defense Tool

OpenAIRE

Dionne, Patrick

2017-01-01

News Stories Archive In May 2017, the United States successfully intercepted an intercontinental ballistic missile in the first-ever test of the U.S.'s long-range, anti-missile capabilities. While impactful, it is just th...

Propulsion systems from takeoff to high-speed flight

Science.gov (United States)

Billig, F. S.

Potential applications for missiles and aircraft requiring highly efficient engines serve as the basis for discussing new propulsion concepts and novel combinations of existing cycles. Comparisons are made between rocket and airbreathing powered missiles for anti-ballistic and surface-to-air missions. The properties of cryogenic hydrogen are presented to explain the mechanics and limitations of liquid air cycles. Conceptual vehicle designs of a transatmospheric accelerator are introduced to permit examination of the factors that guide the choice of the optimal propulsion system.

Analysis of the engine fragment threat and the crush environment for small packages carried on U.S. commercial jet aircraft

International Nuclear Information System (INIS)

Hartman, W.F.; McClure, J.D.; von Riesemann, W.A.

1978-01-01

The results of two separate analyses are reported. The engine fragment analysis determined the probability of a small package being in the path of a fragment from a failure in a gas turbine engine. The calculated values show that, depending on aircraft type, the incidence rate varies by approximately an order of magnitude from a high of about once per 5 million flights to a low of nearly once every 40 million package flights for a flight of five hours' duration. The analysis of the crush environment consisted of an examination of two principal crush modes, i.e., vertical and longitudinal crush. The vertical crush mode was examined by formulating a structural model of the cargo deck beams of the aircraft. The longitudinal crush mode was studied by using dynamic models of the aircraft cargo and the radioactive material package (RAM). The results of the analysis of these crush modes provided the basis for the formulation of a 310 kN/(70,000 lb) crush test to simulate vertical crush. The longitudinal crush analysis indicated that it was possible, under infrequently occurring conditions, to produce extremely large crush forces and hence it was recommended that RAM packages be located in the aft end of aircraft cargo compartments to minimize the effects of longitudinal crush

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...

Influence Of Aircraft Engine Exhaust Emissions At A Global Level And Preventive Measures

Directory of Open Access Journals (Sweden)

Jasna Golubić

2004-07-01

Full Text Available The work considers the differences in the aircraft engine exhaustemissions, as well as the impact of the emissions on theenvironment depending on several factors. These include theage of the engine, i. e. technical refinement, engine operating regimesat different thrusts during time periods: takeoff, climb,approach, etc. Also, the exhaust emissions do not have thesame influence on different atmospheric layers. The pollutantsemitted at higher altitudes during cruising have become agreater problem, although the volume of pollutants is smaller,due to the chemical complexity and sensitivity of these layers ascompared to the lower layers of atmosphere. One of the reasonswhy these problems have long remained outside the focus of interestof the environmentalists is that the air transport of goodsand people is performed at high altitudes, so that the pollutionof atmosphere does not present a direct threat to anyone, sincethe environment is being polluted at a global level and thereforeis more difficult to notice at the local level.

Performance optimization of a Two-Stroke supercharged diesel engine for aircraft propulsion

International Nuclear Information System (INIS)

Carlucci, Antonio Paolo; Ficarella, Antonio; Trullo, Gianluca

2016-01-01

Highlights: • A Two-Stroke diesel engine for aircraft propulsion was modeled with a 0D/1D approach. • The results of the 0D/1D model are compared with those resulting from a 3D model. • The effect of several design and thermodynamic parameters have been analyzed. • Guidelines for the optimization of engine performance are provided. - Abstract: In Two-Stroke engines, the cylinder filling efficiency is antithetical to the cylinder scavenging efficiency; moreover, both of them are influenced by geometric and thermodynamic parameters characterizing the design and operation of both the engine and the related supercharging system. Aim of this work is to provide several guidelines about the definition of design and operation parameters for a Two-Stroke two banks Uniflow diesel engine, supercharged with two sequential turbochargers and an aftercooler per bank, with the goal of either increasing the engine brake power at take-off or decreasing the engine fuel consumption in cruise conditions. The engine has been modeled with a 0D/1D modeling approach. Then, the model capability in describing the effect of several parameters on engine performance has been assessed comparing the results of 3D simulations with those of 0D/1D model. The validated 0D/1D model has been used to simulate the engine behavior varying several design and operation engine parameters (exhaust valves opening and closing angles and maximum valve lift, scavenging ports opening angle, distance between bottom edge of the scavenging ports and bottom dead center, area of the single scavenging port and number of ports, engine volumetric compression ratio, low and high pressure compressor pressure ratios, air/fuel ratio) on a wide range of possible values. The parameters most influencing the engine performance are then recognized and their effect on engine thermodynamic behavior is discussed. Finally, the system configurations leading to best engine power at sea level and lowest fuel consumption in cruise

AUTOMATIC CONTROL SYSTEM FOR REGULATED HIGH TEMPERATURE MAIN COMBUSTION CHAMBER OF MANEUVERABLE AIRCRAFT MULTIMODE GAS TURBINE ENGINE

Directory of Open Access Journals (Sweden)

T. V. Gras’Ko

2014-01-01

Full Text Available The paper describes choosing and substantiating the control laws, forming the appearance the automatic control system for regulated high temperature main combustion chamber of maneuverable aircraft multimode gas turbine engine aimed at sustainable and effective functioning of main combustion chamber within a broad operation range.

The Best Aircraft for Close Air Support in the Twenty First Century

Science.gov (United States)

2016-09-01

movement of those forces.”8 In addition to CAS, the Air Force em - ploys its aircraft to perform a myriad of roles during combat operations, such as offen...distance to bombing ranges, and so forth.14 Once these figures are accumulated for each major com- mand’s fleet, the second step is developing a CPFH...the GBU-39 small diameter bomb and the AGM-176 Griffin missile, it is still in operational test and development.26 The new squadron (replacement

Surface modeling method for aircraft engine blades by using speckle patterns based on the virtual stereo vision system

Science.gov (United States)

Yu, Zhijing; Ma, Kai; Wang, Zhijun; Wu, Jun; Wang, Tao; Zhuge, Jingchang

2018-03-01

A blade is one of the most important components of an aircraft engine. Due to its high manufacturing costs, it is indispensable to come up with methods for repairing damaged blades. In order to obtain a surface model of the blades, this paper proposes a modeling method by using speckle patterns based on the virtual stereo vision system. Firstly, blades are sprayed evenly creating random speckle patterns and point clouds from blade surfaces can be calculated by using speckle patterns based on the virtual stereo vision system. Secondly, boundary points are obtained in the way of varied step lengths according to curvature and are fitted to get a blade surface envelope with a cubic B-spline curve. Finally, the surface model of blades is established with the envelope curves and the point clouds. Experimental results show that the surface model of aircraft engine blades is fair and accurate.

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.

Mission Analysis and Aircraft Sizing of a Hybrid-Electric Regional Aircraft

Science.gov (United States)

Antcliff, Kevin R.; Guynn, Mark D.; Marien, Ty V.; Wells, Douglas P.; Schneider, Steven J.; Tong, Michael T.

2016-01-01

The purpose of this study was to explore advanced airframe and propulsion technologies for a small regional transport aircraft concept (approximately 50 passengers), with the goal of creating a conceptual design that delivers significant cost and performance advantages over current aircraft in that class. In turn, this could encourage airlines to open up new markets, reestablish service at smaller airports, and increase mobility and connectivity for all passengers. To meet these study goals, hybrid-electric propulsion was analyzed as the primary enabling technology. The advanced regional aircraft is analyzed with four levels of electrification, 0 percent electric with 100 percent conventional, 25 percent electric with 75 percent conventional, 50 percent electric with 50 percent conventional, and 75 percent electric with 25 percent conventional for comparison purposes. Engine models were developed to represent projected future turboprop engine performance with advanced technology and estimates of the engine weights and flowpath dimensions were developed. A low-order multi-disciplinary optimization (MDO) environment was created that could capture the unique features of parallel hybrid-electric aircraft. It is determined that at the size and range of the advanced turboprop: The battery specific energy must be 750 watt-hours per kilogram or greater for the total energy to be less than for a conventional aircraft. A hybrid vehicle would likely not be economically feasible with a battery specific energy of 500 or 750 watt-hours per kilogram based on the higher gross weight, operating empty weight, and energy costs compared to a conventional turboprop. The battery specific energy would need to reach 1000 watt-hours per kilogram by 2030 to make the electrification of its propulsion an economically feasible option. A shorter range and/or an altered propulsion-airframe integration could provide more favorable results.

Aircraft crash protection from a military engineering point of view

International Nuclear Information System (INIS)

Lynch, J.P.

1975-01-01

The general problem is to investigate the situation of an aircraft crash on a reactor building. One aspect of the problem is to determine if the structural conditions required to protect the environment against the results of an impact at the center of a 10 m by 10 m reinforced concrete wall slab are reasonable. This paper discusses the dynamic structural response problem, using the analytical methods developed for military structures designed to resist blast loading. The military protection problem is quite similar to reactor protection in that extensive analysis is required to define the threat or loading conditions. The post-dynamic-loading structural requirements must also be defined, since every possible source of resistance is used to obtain a structure which protects against the stated threat at the lowest cost. Such a structural design contains the lowest possible factor of safety, using reasonable analytical techniques, and is more properly called collapse design. If more protection is provided than required, the cost will be greater than necessary. An aircraft jet engine impact is selected as the loading condition for the protection requirements of the reactor wall panel. Analytical investigation of the impact indicates that the load function can be reasonably well approximated by the half sine wave pressure-time curve. Thus, the maximum pressure and duration of the half sine pressure pulse completely define the load-time history. (orig./HP) [de

77 FR 34357 - Missile Defense Advisory Committee; Notice of Closed Meeting

Science.gov (United States)

2012-06-11

... DEPARTMENT OF DEFENSE Office of the Secretary Missile Defense Advisory Committee; Notice of Closed Meeting AGENCY: Missile Defense Agency (MDA), Department of Defense. ACTION: Notice of closed meeting... Missile Defense Advisory Committee will take place. DATES: Tuesday, June 12, 2012 through Wednesday, June...

75 FR 77849 - Closed Meeting of the Missile Defense Advisory Committee

Science.gov (United States)

2010-12-14

... DEPARTMENT OF DEFENSE Office of the Secretary Closed Meeting of the Missile Defense Advisory Committee AGENCY: Department of Defense; Missile Defense Agency (MDA). ACTION: Notice. SUMMARY: Under the... Defense announces that the following Federal advisory committee meeting of the Missile Defense Advisory...

75 FR 77848 - Closed Meeting of the Missile Defense Advisory Committee

Science.gov (United States)

2010-12-14

... DEPARTMENT OF DEFENSE Office of the Secretary Closed Meeting of the Missile Defense Advisory Committee AGENCY: Department of Defense; Missile Defense Agency (MDA). ACTION: Notice. SUMMARY: Under the... Defense announces that the following Federal advisory committee meeting of the Missile Defense Advisory...

76 FR 71556 - Missile Defense Advisory Committee; Notice of Closed Meeting

Science.gov (United States)

2011-11-18

... DEPARTMENT OF DEFENSE Office of the Secretary Missile Defense Advisory Committee; Notice of Closed Meeting AGENCY: Missile Defense Agency (MDA), Department of Defense. ACTION: Notice of closed meeting... Missile Defense Advisory Committee will take place. DATES: Tuesday, December 13, 2011 through Wednesday...

76 FR 45783 - Missile Defense Advisory Committee; Notice of Closed Meeting

Science.gov (United States)

2011-08-01

... DEPARTMENT OF DEFENSE Office of the Secretary Missile Defense Advisory Committee; Notice of Closed Meeting AGENCY: Department of Defense; Missile Defense Agency (MDA). ACTION: Notice of closed meeting... Missile Defense Advisory Committee will take place. DATES: Tuesday, August 16, 2011 through Thursday...

Design trade-offs for homing missiles

Science.gov (United States)

Spencer, Allen; Moore, William

1992-05-01

Major design considerations, trade-offs and technology issues for future hypervelocity, anti-missile interceptors are presented in an overview format. Two classes of interceptors are considered: a low altitude interceptor using an active radar seeker for defense against tactical ballistic missiles (TBMs) and a higher altitude interceptor using a passive infra-red seeker for defense against ICBMs. Considerations are presented in the areas of mission requirements, seeker selection, aerodynamic and aerothermal environments, control systems, and guidance performance.

Conditional probability of the tornado missile impact given a tornado occurrence

International Nuclear Information System (INIS)

Goodman, J.; Koch, J.E.

1982-01-01

Using an approach based on statistical mechanics, an expression for the probability of the first missile strike is developed. The expression depends on two generic parameters (injection probability eta(F) and height distribution psi(Z,F)), which are developed in this study, and one plant specific parameter (number of potential missiles N/sub p/). The expression for the joint probability of simultaneous impact of muitiple targets is also developed. This espression is applicable to calculation of the probability of common cause failure due to tornado missiles. It is shown that the probability of the first missile strike can be determined using a uniform missile distribution model. It is also shown that the conditional probability of the second strike, given the first, is underestimated by the uniform model. The probability of the second strike is greatly increased if the missiles are in clusters large enough to cover both targets

Full-scale Tornado-missile impact tests

International Nuclear Information System (INIS)

1976-04-01

Initial tests with four types of hypothetical tornado-borne missiles impacting reinforced concrete panels have been completed. Panel thicknesses are typical of walls in nuclear power facilities. In the seven tests, the missiles were rocket propelled to velocities currently postulated as being attainable by debris in tornadoes. The objective of the 18-test program is to ascertain the vulnerability of test panels to penetration and backface scabbing. The four missile types being tested are: a 1500-pound 35-foot long utility pole, an 8-pound 1-inch Grade 60 reinforcing bar, a 78-pound 3-inch Schedule 40 pipe, and a 743-pound 12-inch Schedule 40 pipe. The test panels are 12, 18, and 24 inches thick with 15 by 15 foot free spans. They were constructed to current minimum ACI standards: 3000 psi design strength (actual strength about 3600 psi) and 0.2 percent reinforcing steel area each way, each face (actual area is about 0.27 percent with bars on 12-inch centers). The 12-inch pipe has been identified as the critical missile for design of nuclear facility walls under currently specified impact conditions. The utility poles splintered upon impact causing virtually no impact damage, and the 3-inch pipe and 1-inch rebar were comparatively ineffectual because of their light weight

A Risk Management Architecture for Emergency Integrated Aircraft Control

Science.gov (United States)

McGlynn, Gregory E.; Litt, Jonathan S.; Lemon, Kimberly A.; Csank, Jeffrey T.

2011-01-01

Enhanced engine operation--operation that is beyond normal limits--has the potential to improve the adaptability and safety of aircraft in emergency situations. Intelligent use of enhanced engine operation to improve the handling qualities of the aircraft requires sophisticated risk estimation techniques and a risk management system that spans the flight and propulsion controllers. In this paper, an architecture that weighs the risks of the emergency and of possible engine performance enhancements to reduce overall risk to the aircraft is described. Two examples of emergency situations are presented to demonstrate the interaction between the flight and propulsion controllers to facilitate the enhanced operation.

Hyperheat: a thermal signature model for super- and hypersonic missiles

Science.gov (United States)

van Binsbergen, S. A.; van Zelderen, B.; Veraar, R. G.; Bouquet, F.; Halswijk, W. H. C.; Schleijpen, H. M. A.

2017-10-01

In performance prediction of IR sensor systems for missile detection, apart from the sensor specifications, target signatures are essential variables. Very often, for velocities up to Mach 2-2.5, a simple model based on the aerodynamic heating of a perfect gas was used to calculate the temperatures of missile targets. This typically results in an overestimate of the target temperature with correspondingly large infrared signatures and detection ranges. Especially for even higher velocities, this approach is no longer accurate. Alternatives like CFD calculations typically require more complex sets of inputs and significantly more computing power. The MATLAB code Hyperheat was developed to calculate the time-resolved skin temperature of axisymmetric high speed missiles during flight, taking into account the behaviour of non-perfect gas and proper heat transfer to the missile surface. Allowing for variations in parameters like missile shape, altitude, atmospheric profile, angle of attack, flight duration and super- and hypersonic velocities up to Mach 30 enables more accurate calculations of the actual target temperature. The model calculates a map of the skin temperature of the missile, which is updated over the flight time of the missile. The sets of skin temperature maps are calculated within minutes, even for >100 km trajectories, and can be easily converted in thermal infrared signatures for further processing. This paper discusses the approach taken in Hyperheat. Then, the thermal signature of a set of typical missile threats is calculated using both the simple aerodynamic heating model and the Hyperheat code. The respective infrared signatures are compared, as well as the difference in the corresponding calculated detection ranges.

Exposure assessment of JAVELIN missile combustion products

Science.gov (United States)

Lundy, Donald O.; Langford, Roland E.

1994-02-01

Characterization and analysis of combustion products resulting from firing the JAVELIN missile were performed. Of those combustion products analyzed, it was determined that airborne lead concentrations exceeded the OSHA PEL of 50 micrograms each time the missile was fired while in the enclosure. Since the OSHA PEL standard is based upon a continuous rather than a short-term exposures blood lead concentrations were sought to ascertain the relationship between a short duration airborne exposure and its physiological effect on the body. Blood lead levels were taken on 49 test subjects prior to various JAVELIN missile test firings. Of those 49, 21 were outfitted With personal sampling equipment to determine airborne concentrations at the Assistant Gunner and Gunner positions. Periodic blood sampling after a single exposure showed an average increase of 2.27 micrograms/dL for all test subjects. Recommendations were made to consider changes in the positioning of the enclosure inhabitants to minimize airborne lead concentrations, to limit the number of missiles fired (situation dependent), and replacement of the lead B-resorcyolate with a non-lead containing burn rate modifier for the launch motor.

Guidance Optimization for Tactical Homing Missiles and Air Defense Systems

Directory of Open Access Journals (Sweden)

Yunes Sh. ALQUDSI

2018-03-01

Full Text Available The aim of this paper is to develop a functional approach to optimize the engagement effectiveness of the tactical homing missiles and air defense systems by utilizing the differential geometric concepts. In this paper the engagement geometry of the interceptor and the target is developed and expressed in differential geometric terms in order to demonstrate the possibilities of the impact triangles and specify the earliest interception based on the direct intercept geometry. Optimizing the missile heading angle and suitable missile velocity against the target velocity is then examined to achieve minimum missile latax, minimum time-to-go (time-to-hit and minimum appropriate missile velocity that is guaranteed a quick and precise interception for the given target. The study terminates with different scenarios of engagement optimization with two-dimensional simulation to demonstrate the applicability of the DG approach and to show its properties.

Evaluating missile fuels

Energy Technology Data Exchange (ETDEWEB)

Osmont, Antoine; Goekalp, Iskender [Laboratoire de Combustion et Systemes Reactifs (LCSR), CNRS, 1C, Orleans (France); Catoire, Laurent [University of Orleans, BP6749, 45067 Orleans (France); Laboratoire de Combustion et Systemes Reactifs (LCSR), CNRS, 1C, Orleans (France)

2006-10-15

This paper presents simple and relatively efficient methods to estimate some physical and chemical properties of polycyclic alkanes. These properties are melting point, normal boiling point, standard enthalpy of vaporization at 298 K, standard enthalpy of formation at 298 K, standard enthalpy of combustion at 298 K, density (specific gravity) and flash point. These methods are validated, despite the scarcity of experimental data, with several tens of polycyclic alkanes. Then the methods are used to estimate properties of some polycyclic alkanes, which are currently in use as missile fuels: JP-10, RJ-4 and RJ-5. Estimates and experimental data are found in good agreement for these fuels. This methodology is then used to evaluate missile fuel candidates to be used pure or as additive to JP-10 or to blends such as RJ-6. Several compounds are probably of interest for this task and their advantages and drawbacks are discussed. (Abstract Copyright [2006], Wiley Periodicals, Inc.)

Report to NASA Committee on Aircraft Operating Problems Relative to Aviation Safety Engineering and Research Activities

Science.gov (United States)

1963-01-01

The following report highlights some of the work accomplished by the Aviation Safety Engineering and Research Division of the Flight Safety Foundations since the last report to the NASA Committee on Aircraft Operating Problems on 22 May 1963. The information presented is in summary form. Additional details may be provided upon request of the reports themselves may be obtained from AvSER.

Analytical modeling of the structureborne noise path on a small twin-engine aircraft

Science.gov (United States)

Cole, J. E., III; Stokes, A. Westagard; Garrelick, J. M.; Martini, K. F.

1988-01-01

The structureborne noise path of a six passenger twin-engine aircraft is analyzed. Models of the wing and fuselage structures as well as the interior acoustic space of the cabin are developed and used to evaluate sensitivity to structural and acoustic parameters. Different modeling approaches are used to examine aspects of the structureborne path. These approaches are guided by a number of considerations including the geometry of the structures, the frequency range of interest, and the tractability of the computations. Results of these approaches are compared with experimental data.

Differences in Characteristics of Aviation Accidents During 1993-2012 Based on Aircraft Type

Science.gov (United States)

Evans, Joni K.

2015-01-01

Civilian aircraft are available in a variety of sizes, engine types, construction materials and instrumentation complexity. For the analysis reported here, eleven aircraft categories were developed based mostly on aircraft size and engine type, and these categories were applied to twenty consecutive years of civil aviation accidents. Differences in various factors were examined among these aircraft types, including accident severity, pilot characteristics and accident occurrence categories. In general, regional jets and very light sport aircraft had the lowest rates of adverse outcomes (injuries, fatal accidents, aircraft destruction, major accidents), while aircraft with twin (piston) engines or with a single (piston) engine and retractable landing gear carried the highest incidence of adverse outcomes. The accident categories of abnormal runway contact, runway excursions and non-powerplant system/component failures occur frequently within all but two or three aircraft types. In contrast, ground collisions, loss of control - on ground/water and powerplant system/component failure occur frequently within only one or two aircraft types. Although accidents in larger aircraft tend to have less severe outcomes, adverse outcome rates also differ among accident categories. It may be that the type of accident has as much or more influence on the outcome as the type of aircraft.

Acquisition: Acquisition of Targets at the Missile Defense Agency

National Research Council Canada - National Science Library

Ugone, Mary L; Meling, John E; James, Harold C; Haynes, Christine L; Heller, Brad M; Pomietto, Kenneth M; Bobbio, Jaime; Chang, Bill; Pugh, Jacqueline

2005-01-01

Who Should Read This Report and Why? Missile Defense Agency program managers who are responsible for the acquisition and management of targets used to test the Ballistic Missile Defense System should be interested in this report...

Space-based ballistic-missile defense

International Nuclear Information System (INIS)

Bethe, H.A.; Garwin, R.L.; Gottfried, K.; Kendall, H.W.

1984-01-01

This article, based on a forthcoming book by the Union for Concerned Scientists, focuses on the technical aspects of the issue of space-based ballistic-missile defense. After analysis, the authors conclude that the questionable performance of the proposed defense, the ease with which it could be overwhelmed or circumvented, and its potential as an antisatellite system would cause grievous damage to the security of the US if the Strategic Defense Initiative were to be pursued. The path toward greater security lies in quite another direction, they feel. Although research on ballistic-missile defense should continue at the traditional level of expenditure and within the constraints of the ABM Treaty, every effort should be made to negotiate a bilateral ban on the testing and use of space weapons. The authors think it is essential that such an agreement cover all altitudes, because a ban on high-altitude antisatellite weapons alone would not viable if directed energy weapons were developed for ballistic-missile defense. Further, the Star Wars program, unlikely ever to protect the entire nation against a nuclear attack, would nonetheless trigger a major expansion of the arms race

Development of Advanced Carbon Face Seals for Aircraft Engines

Science.gov (United States)

Falaleev, S. V.; Bondarchuk, P. V.; Tisarev, A. Yu

2018-01-01

Modern aircraft gas turbine engines require the development of seals which can operate for a long time with low leakages. The basic type of seals applied for gas turbine engine rotor supports is face seal. To meet the modern requirements of reliability, leak-tightness and weight, low-leakage gas-static and hydrodynamic seals have to be developed. Dry gas seals use both gas-static and hydrodynamic principles. In dry gas seals microgrooves are often used, which ensure the reverse injection of leakages in the sealed cavity. Authors have developed a calculation technique including the concept of coupled hydrodynamic, thermal and structural calculations. This technique allows to calculate the seal performance taking into account the forces of inertia, rupture of the lubricant layer and the real form of the gap. Authors have compared the efficiency of seals with different forms of microgrooves. Results of calculations show that seal with rectangular form of microgrooves has a little gap leading to both the contact of seal surfaces and the wear. Reversible microgrooves have a higher oil mass flow rate, whereas HST micro-grooves have good performance, but they are difficult to produce. Spiral microgrooves have both an acceptable leakages and a high stiffness of liquid layer that is important in terms of ensuring of sealing performance at vibration conditions. Therefore, the spiral grooves were chosen for the developed seal. Based on calculation results, geometric dimensions were chosen to ensure the reliability of the seal operation by creating a guaranteed liquid film, which eliminates the wear of the sealing surfaces. Seals designed were tested both at the test rig and in the engine.

76 FR 16736 - Closed Meeting of the Missile Defense Advisory Committee

Science.gov (United States)

2011-03-25

... DEPARTMENT OF DEFENSE Office of the Secretary Closed Meeting of the Missile Defense Advisory Committee AGENCY: Missile Defense Agency (MDA), DoD. ACTION: Notice of closed meeting. SUMMARY: Under the...: Missile Defense Advisory Committee. Dates of Meeting: Thursday, March 24, 2011. Times: 8 a.m. to 5:30 p.m...

Exergo-Economic Analysis of an Experimental Aircraft Turboprop Engine Under Low Torque Condition

Science.gov (United States)

Atilgan, Ramazan; Turan, Onder; Aydin, Hakan

Exergo-economic analysis is an unique combination of exergy analysis and cost analysis conducted at the component level. In exergo-economic analysis, cost of each exergy stream is determined. Inlet and outlet exergy streams of the each component are associated to a monetary cost. This is essential to detect cost-ineffective processes and identify technical options which could improve the cost effectiveness of the overall energy system. In this study, exergo-economic analysis is applied to an aircraft turboprop engine. Analysis is based on experimental values at low torque condition (240 N m). Main components of investigated turboprop engine are the compressor, the combustor, the gas generator turbine, the free power turbine and the exhaust. Cost balance equations have been formed for all components individually and exergo-economic parameters including cost rates and unit exergy costs have been calculated for each component.

An improved particle filtering algorithm for aircraft engine gas-path fault diagnosis

Directory of Open Access Journals (Sweden)

Qihang Wang

2016-07-01

Full Text Available In this article, an improved particle filter with electromagnetism-like mechanism algorithm is proposed for aircraft engine gas-path component abrupt fault diagnosis. In order to avoid the particle degeneracy and sample impoverishment of normal particle filter, the electromagnetism-like mechanism optimization algorithm is introduced into resampling procedure, which adjusts the position of the particles through simulating attraction–repulsion mechanism between charged particles of the electromagnetism theory. The improved particle filter can solve the particle degradation problem and ensure the diversity of the particle set. Meanwhile, it enhances the ability of tracking abrupt fault due to considering the latest measurement information. Comparison of the proposed method with three different filter algorithms is carried out on a univariate nonstationary growth model. Simulations on a turbofan engine model indicate that compared to the normal particle filter, the improved particle filter can ensure the completion of the fault diagnosis within less sampling period and the root mean square error of parameters estimation is reduced.

The Aircraft Industry

National Research Council Canada - National Science Library

Fitzgerald, Tim; Baiche, Noureddine; Brewer, Mike; Collins, Al; Knapp, Kathy; Kott, Marilyn; McGill, Duncan; Mensah, Dunstan; Neighbors, Mark; Reardon, Dee

2005-01-01

.... As the airline companies prepare to buy new Boeing and Airbus passenger jets, they remain under intense pressure to cut costs in order to remain profitable, forcing aircraft and engine manufacturers...

Internal Shear Forging Processes for Missile Primary Structures.

Science.gov (United States)

1981-07-20

Growth in Shear Forming," Trans. ASME, J. Eng. ind., Vol. 90, 1968, pp. 63-70. 1 28. H. J. Dreikandt, "Untersuchung Uber das DrUckwalzen zylindrisher...10 US Army Missile Command ATTN: DRSMI-RLM Redstone Arsenal, AL 35809 Comma nder 12 US Army Missile Command + camera-ready master ATTN: DRDMI- EAT

Sensor Selection for Aircraft Engine Performance Estimation and Gas Path Fault Diagnostics

Science.gov (United States)

Simon, Donald L.; Rinehart, Aidan W.

2016-01-01

This paper presents analytical techniques for aiding system designers in making aircraft engine health management sensor selection decisions. The presented techniques, which are based on linear estimation and probability theory, are tailored for gas turbine engine performance estimation and gas path fault diagnostics applications. They enable quantification of the performance estimation and diagnostic accuracy offered by different candidate sensor suites. For performance estimation, sensor selection metrics are presented for two types of estimators including a Kalman filter and a maximum a posteriori estimator. For each type of performance estimator, sensor selection is based on minimizing the theoretical sum of squared estimation errors in health parameters representing performance deterioration in the major rotating modules of the engine. For gas path fault diagnostics, the sensor selection metric is set up to maximize correct classification rate for a diagnostic strategy that performs fault classification by identifying the fault type that most closely matches the observed measurement signature in a weighted least squares sense. Results from the application of the sensor selection metrics to a linear engine model are presented and discussed. Given a baseline sensor suite and a candidate list of optional sensors, an exhaustive search is performed to determine the optimal sensor suites for performance estimation and fault diagnostics. For any given sensor suite, Monte Carlo simulation results are found to exhibit good agreement with theoretical predictions of estimation and diagnostic accuracies.

Application of Pontryagin’s Minimum Principle in Optimum Time of Missile Manoeuvring

Directory of Open Access Journals (Sweden)

Sari Cahyaningtias

2016-11-01

Full Text Available Missile is a guided weapon and designed to protect outermost island from a thread of other country. It, commonly, is used as self defense. This research presented surface-to-surface missile in final dive manoeuvre for fixed target. Furthermore, it was proposed manoeuvring based on unmanned aerial vehicle (UAV, autopilot system, which needs accuration and minimum both time and thrust of missile while attacking object. This paper introduced pontryagin’s Minimum Principle, which is useable to solve the problem. The numerical solution showed that trajectory of the missile is split it up in three sub-intervals; flight, climbing, and diving. The numerical simulation showed that the missile must climb in order to satisfy the final dive condition and the optimum time of a missile depend on initial condition of the altitude and the terminal velocity

Analysis of the development of missile-borne IR imaging detecting technologies

Science.gov (United States)

Fan, Jinxiang; Wang, Feng

2017-10-01

Today's infrared imaging guiding missiles are facing many challenges. With the development of targets' stealth, new-style IR countermeasures and penetrating technologies as well as the complexity of the operational environments, infrared imaging guiding missiles must meet the higher requirements of efficient target detection, capability of anti-interference and anti-jamming and the operational adaptability in complex, dynamic operating environments. Missileborne infrared imaging detecting systems are constrained by practical considerations like cost, size, weight and power (SWaP), and lifecycle requirements. Future-generation infrared imaging guiding missiles need to be resilient to changing operating environments and capable of doing more with fewer resources. Advanced IR imaging detecting and information exploring technologies are the key technologies that affect the future direction of IR imaging guidance missiles. Infrared imaging detecting and information exploring technologies research will support the development of more robust and efficient missile-borne infrared imaging detecting systems. Novelty IR imaging technologies, such as Infrared adaptive spectral imaging, are the key to effectively detect, recognize and track target under the complicated operating and countermeasures environments. Innovative information exploring techniques for the information of target, background and countermeasures provided by the detection system is the base for missile to recognize target and counter interference, jamming and countermeasure. Modular hardware and software development is the enabler for implementing multi-purpose, multi-function solutions. Uncooled IRFPA detectors and High-operating temperature IRFPA detectors as well as commercial-off-the-shelf (COTS) technology will support the implementing of low-cost infrared imaging guiding missiles. In this paper, the current status and features of missile-borne IR imaging detecting technologies are summarized. The key

Model-Based Control of a Nonlinear Aircraft Engine Simulation using an Optimal Tuner Kalman Filter Approach

Science.gov (United States)

Connolly, Joseph W.; Csank, Jeffrey Thomas; Chicatelli, Amy; Kilver, Jacob

2013-01-01

This paper covers the development of a model-based engine control (MBEC) methodology featuring a self tuning on-board model applied to an aircraft turbofan engine simulation. Here, the Commercial Modular Aero-Propulsion System Simulation 40,000 (CMAPSS40k) serves as the MBEC application engine. CMAPSS40k is capable of modeling realistic engine performance, allowing for a verification of the MBEC over a wide range of operating points. The on-board model is a piece-wise linear model derived from CMAPSS40k and updated using an optimal tuner Kalman Filter (OTKF) estimation routine, which enables the on-board model to self-tune to account for engine performance variations. The focus here is on developing a methodology for MBEC with direct control of estimated parameters of interest such as thrust and stall margins. Investigations using the MBEC to provide a stall margin limit for the controller protection logic are presented that could provide benefits over a simple acceleration schedule that is currently used in traditional engine control architectures.

A summary of computational experience at GE Aircraft Engines for complex turbulent flows in gas turbines

Science.gov (United States)

Zerkle, Ronald D.; Prakash, Chander

1995-01-01

This viewgraph presentation summarizes some CFD experience at GE Aircraft Engines for flows in the primary gaspath of a gas turbine engine and in turbine blade cooling passages. It is concluded that application of the standard k-epsilon turbulence model with wall functions is not adequate for accurate CFD simulation of aerodynamic performance and heat transfer in the primary gas path of a gas turbine engine. New models are required in the near-wall region which include more physics than wall functions. The two-layer modeling approach appears attractive because of its computational complexity. In addition, improved CFD simulation of film cooling and turbine blade internal cooling passages will require anisotropic turbulence models. New turbulence models must be practical in order to have a significant impact on the engine design process. A coordinated turbulence modeling effort between NASA centers would be beneficial to the gas turbine industry.

MODELING OF THE FUNCTIONING UNITS OF FUEL SYSTEM OF GAS TURBINE ENGINE AIRCRAFT IN VIEW OF AVIATION FUEL QUALITY CHANGES

OpenAIRE

I. I. Zavyalik; V. S. Oleshko; V. M. Samoylenko; E. V. Fetisov

2016-01-01

The article describes the developed modeling system in MATLAB Simulink which allows to simulate, explore and pre- dict the technical condition of the units of the aircraft gas turbine engine fuel system depending on aviation fuel quality changes.

Energy Conversion and Storage Requirements for Hybrid Electric Aircraft

Science.gov (United States)

Misra, Ajay

2016-01-01

Among various options for reducing greenhouse gases in future large commercial aircraft, hybrid electric option holds significant promise. In the hybrid electric aircraft concept, gas turbine engine is used in combination with an energy storage system to drive the fan that propels the aircraft, with gas turbine engine being used for certain segments of the flight cycle and energy storage system being used for other segments. The paper will provide an overview of various energy conversion and storage options for hybrid electric aircraft. Such options may include fuel cells, batteries, super capacitors, multifunctional structures with energy storage capability, thermoelectric, thermionic or a combination of any of these options. The energy conversion and storage requirements for hybrid electric aircraft will be presented. The role of materials in energy conversion and storage systems for hybrid electric aircraft will be discussed.

Information Management Principles Applied to the Ballistic Missile Defense System

National Research Council Canada - National Science Library

Koehler, John M

2007-01-01

.... Similarly several military systems with the single mission of missile defense have evolved in service stovepipes, and are now being integrated into a national and global missile defense architecture...

Thermal design of linear induction and synchronous motor for electromagnetic launch of civil aircraft

OpenAIRE

Bertola, Luca; Cox, Tom; Wheeler, Patrick; Garvey, Seamus D.; Morvan, Herve

2017-01-01

The engine size of modern passenger transport aircraft is principally determined by take-off conditions, since initial acceleration requires maximum engine power. An elec¬tromagnetic launch (EML) system could provide some or all of the energy required at takeoff so that the aircraft engine power requirement and fuel consumption may be significantly reduced. So far, EML for aircraft has been adopted only for military applications to replace steam catapults on the deck of aircraft carriers. Thi...

14 CFR 43.7 - Persons authorized to approve aircraft, airframes, aircraft engines, propellers, appliances, or...

Science.gov (United States)

2010-01-01

... data approved by the Administrator. (e) The holder of an air carrier operating certificate or an... holder of a repairman certificate (light-sport aircraft) with a maintenance rating may approve an aircraft issued a special airworthiness certificate in light-sport category for return to service, as...

78 FR 60656 - Airworthiness Directives; Sikorsky Aircraft Corporation Helicopters

Science.gov (United States)

2013-10-02

... Airworthiness Directives; Sikorsky Aircraft Corporation Helicopters AGENCY: Federal Aviation Administration (FAA... Aircraft Corporation (Sikorsky) Model S-92A helicopters to require modifying the No. 1 engine forward... Sikorsky Aircraft Corporation, Attn: Manager, Commercial Technical Support, mailstop s581a, 6900 Main...

NDT applications in the aircraft industry

International Nuclear Information System (INIS)

Aguilar, E.C.

1994-01-01

Non-destructive testing (NDT) in the aircraft industry is used primarily to detect process defects in the manufacturing stage and failure defects in the in-service stage. Inspection techniques such as X- or gamma ray radiography are used for examination. Eddy current and ultrasonic are applied for examination, fluorescent penetrant and magnetic particles are applied for examination of aircraft and engine. With the wide scope of application, this paper discussed one type of NDT that is much used in aircraft being the latest technique in aircraft manufacturing. 1 fig

Development process of muzzle flows including a gun-launched missile

Directory of Open Access Journals (Sweden)

Zhuo Changfei

2015-04-01

Full Text Available Numerical investigations on the launch process of a gun-launched missile from the muzzle of a cannon to the free-flight stage have been performed in this paper. The dynamic overlapped grids approach are applied to dealing with the problems of a moving gun-launched missile. The high-resolution upwind scheme (AUSMPW+ and the detailed reaction kinetics model are adopted to solve the chemical non-equilibrium Euler equations for dynamic grids. The development process and flow field structure of muzzle flows including a gun-launched missile are discussed in detail. This present numerical study confirms that complicated transient phenomena exist in the shortly launching stages when the gun-launched missile moves from the muzzle of a cannon to the free-flight stage. The propellant gas flows, the initial environmental ambient air flows and the moving missile mutually couple and interact. A complete structure of flow field is formed at the launching stages, including the blast wave, base shock, reflected shock, incident shock, shear layer, primary vortex ring and triple point.

MODELING OF THE FUNCTIONING UNITS OF FUEL SYSTEM OF GAS TURBINE ENGINE AIRCRAFT IN VIEW OF AVIATION FUEL QUALITY CHANGES

Directory of Open Access Journals (Sweden)

I. I. Zavyalik

2016-01-01

Full Text Available The article describes the developed modeling system in MATLAB Simulink which allows to simulate, explore and pre- dict the technical condition of the units of the aircraft gas turbine engine fuel system depending on aviation fuel quality changes.

Modeling and conduct of turbine missile concrete impact experiments

International Nuclear Information System (INIS)

Woodfin, R.L.

1981-01-01

The overall objective of the subject experiments was to provide full scale data on the response of reinforced concrete containment walls to impact and penetration by postulated turbine-produced missiles. These data can be used to validate analytical or scale modeling methods and to assess the applicability of current design formulas to penetration by large, irregularly shaped missiles. These data and results will be used in providing more realistic estimates of turbine missile damage probability in nuclear power plants with a non-peninsula arrangement. This paper describes the derivation of the test matrix and the method of conducting the experiments. (orig./HP)

Analysis of Aircraft Crash Accident for WETF

International Nuclear Information System (INIS)

Jordan, Hans

2001-01-01

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

The behavior of reinforced concrete barriers subjected to the impact of tornado generated deformable missiles

International Nuclear Information System (INIS)

McMahon, P.M.; Meyers, B.L.; Buchert, K.P.

1977-01-01

The paper presents a general model for the evaluation of local effects damage including, penetration and backface spalling, of reinforced concrete barriers subjected to the impact of deformable tornado generated missiles. The model is based on an approximte force time history which assumes: 1) the initial penetration of the missile occurs without significant deformation of the missile if the strength of the missile is greater than that of the barrier. This portion of the time history is represented by a linear and finite rise time; 2) wrinkling or collapse of the missile occurs when the critical stress of the missile is exceeded. This portion of the time histroy is represented by a constant force-time relationship, although a decreaseing force might be more accurate; 3) while the missile is penetrating and wrinkling both elastic and plastic stress waves are developed in the missile, and compressive and shear stress waves are generated in he target. When the shear waves reach the backface of the slab, doagonal cracks initiating at the end of the penetrating missile are formed. These cracks propagate to the backface reinforcing where splitting cracks are formed. Finally, yield hinge lines form in the plane of reinforcing; 4) repenetration of the missile occurs after the wrinkling has caused a change in missile cross section. This repenetration results from moving the failure cone described in three above, and is also represented by the costant force time history. Using the assumptions, relationships for the penetration depth of the missile the wrinkling length of the missile, the critical missile stress, the time history of the impact and the spalling of the target are developed. (Auth.)

Cooperative Monitoring Center Occasional Paper/9: De-Alerting Strategic Ballistic Missiles

Energy Technology Data Exchange (ETDEWEB)

Connell, Leonard W.; Edenburn, Michael W.; Fraley, Stanley K.; Trost, Lawrence C.

1999-03-01

This paper presents a framework for evaluating the technical merits of strategic ballistic missile de-alerting measures, and it uses the framework to evaluate a variety of possible measures for silo-based, land-mobile, and submarine-based missiles. De-alerting measures are defined for the purpose of this paper as reversible actions taken to increase the time or effort required to launch a strategic ballistic missile. The paper does not assess the desirability of pursuing a de-alerting program. Such an assessment is highly context dependent. The paper postulates that if de-alerting is desirable and is used as an arms control mechanism, de-alerting measures should satisfy specific cirteria relating to force security, practicality, effectiveness, significant delay, and verifiability. Silo-launched missiles lend themselves most readily to de-alerting verification, because communications necessary for monitoring do not increase the vulnerabilty of the weapons by a significant amount. Land-mobile missile de-alerting measures would be more challenging to verify, because monitoring measures that disclose the launcher's location would potentially increase their vulnerability. Submarine-launched missile de-alerting measures would be extremely challlenging if not impossible to monitor without increasing the submarine's vulnerability.

Design of DOE facilities for wind-generated missiles

International Nuclear Information System (INIS)

Kuilanoff, G.; Drake, R.M.

1991-01-01

This paper presents criteria and procedures for the design of structures and components for wind-generated missiles. Methods for determining missile-induced loading, calculated structural response, performance requirements, and design considerations are covered. The presented criteria is applicable to Safety-Related concrete buildings as a whole and to all their exposed external components including walls, roofs, and supporting structural systems and elements

Application of a Complex Lead Compensator for a Laser Guided Missile

Science.gov (United States)

Akhila, M. R.; Gopika, S.; Abraham, R. J.

2013-01-01

This paper discusses the application of a lead compensator with complex pole and complex zero for a missile. It is compared with a lead compensator with real pole and real zero. A typical laser guided missile control system is considered for the performance comparison of both the compensators. Simulation studies carried out with MATLAB brings out the scope of using complex compensator in missile guided systems.

Comprehensive analysis of transport aircraft flight performance

Science.gov (United States)

Filippone, Antonio

2008-04-01

This paper reviews the state-of-the art in comprehensive performance codes for fixed-wing aircraft. The importance of system analysis in flight performance is discussed. The paper highlights the role of aerodynamics, propulsion, flight mechanics, aeroacoustics, flight operation, numerical optimisation, stochastic methods and numerical analysis. The latter discipline is used to investigate the sensitivities of the sub-systems to uncertainties in critical state parameters or functional parameters. The paper discusses critically the data used for performance analysis, and the areas where progress is required. Comprehensive analysis codes can be used for mission fuel planning, envelope exploration, competition analysis, a wide variety of environmental studies, marketing analysis, aircraft certification and conceptual aircraft design. A comprehensive program that uses the multi-disciplinary approach for transport aircraft is presented. The model includes a geometry deck, a separate engine input deck with the main parameters, a database of engine performance from an independent simulation, and an operational deck. The comprehensive code has modules for deriving the geometry from bitmap files, an aerodynamics model for all flight conditions, a flight mechanics model for flight envelopes and mission analysis, an aircraft noise model and engine emissions. The model is validated at different levels. Validation of the aerodynamic model is done against the scale models DLR-F4 and F6. A general model analysis and flight envelope exploration are shown for the Boeing B-777-300 with GE-90 turbofan engines with intermediate passenger capacity (394 passengers in 2 classes). Validation of the flight model is done by sensitivity analysis on the wetted area (or profile drag), on the specific air range, the brake-release gross weight and the aircraft noise. A variety of results is shown, including specific air range charts, take-off weight-altitude charts, payload-range performance

The Apache Longbow-Hellfire Missile Test at Yuma Proving Ground: Ecological Risk Assessment for Missile Firing

International Nuclear Information System (INIS)

Jones, Daniel Steven; Efroymson, Rebecca Ann; Hargrove, William Walter; Suter, Glenn; Pater, Larry

2008-01-01

A multiple stressor risk assessment was conducted at Yuma Proving Ground, Arizona, as a demonstration of the Military Ecological Risk Assessment Framework. The focus was a testing program at Cibola Range, which involved an Apache Longbow helicopter firing Hellfire missiles at moving targets, M60-A1 tanks. This paper describes the ecological risk assessment for the missile launch and detonation. The primary stressor associated with this activity was sound. Other minor stressors included the detonation impact, shrapnel, and fire. Exposure to desert mule deer (Odocoileus hemionus crooki) was quantified using the Army sound contour program BNOISE2, as well as distances from the explosion to deer. Few effects data were available from related studies. Exposure-response models for the characterization of effects consisted of human 'disturbance' and hearing damage thresholds in units of C-weighted decibels (sound exposure level) and a distance-based No Observed Adverse Effects Level for moose and cannonfire. The risk characterization used a weight-of-evidence approach and concluded that risk to mule deer behavior from the missile firing was likely for a negligible number of deer, but that no risk to mule deer abundance and reproduction is expected

Safety analysis of dual purpose metal cask subjected to impulsive loads due to aircraft engine crash

International Nuclear Information System (INIS)

Shirai, Koji; Namba, Kosuke; Saegusa, Toshiari

2009-01-01

In Japan, the first Interim Storage Facility of spent nuclear fuel away from reactor site is being planned to start its commercial operation around 2010, in use of dual-purpose metal cask in the northern part of Main Japan Island. Business License Examination for safety design approval has started since March, 2007. To demonstrate the more scientific and rational performance of safety regulation activities on each phase for the first license procedure, CREPEI has executed demonstration tests with full scale casks, such as drop tests onto real targets without impact limiters and seismic tests subjected to strong earthquake motions. Moreover, it is important to develop the knowledge for the inherent security of metal casks under extreme mechanical-impact conditions, especially for increasing interest since the terrorist attacks from 11th September 2001. This paper presents dynamic mechanical behavior of the metal cask lid closure system caused by direct aircraft engine crash and describes calculated results (especially, leak tightness based on relative dynamic displacements between metallic seals). Firstly, the local penetration damage of the interim storage facility building by a big passenger aircraft engine research (diameter 2.7m, length 4.3m, weight 4.4ton, impact velocity 90m/s) has been examined. The reduced velocity is calculated by the local damage formula for concrete structure with its thickness of 70cm. The load vs. time function for this reduced velocity (60m/s) is estimated by the impact analysis using Finite Element code LS-DYNA with the full scale engine model onto a hypothetically rigid target. Secondly, as the most critical scenarios for the metal cask, two impact scenarios (horizontal impact hitting the cask and vertical impact onto the lid metallic seal system) are chosen. To consider the geometry of all bolts for two lids, the gasket reaction forces and the inner pressure of the cask cavity, the detailed three dimensional FEM models are developed

Safety Analysis of Dual Purpose Metal Cask Subjected to Impulsive Loads due to Aircraft Engine Crash

Science.gov (United States)

Shirai, Koji; Namba, Kosuke; Saegusa, Toshiari

In Japan, the first Interim Storage Facility of spent nuclear fuel away from reactor site is being planned to start its commercial operation around 2010, in use of dual-purpose metal cask in the northern part of Main Japan Island. Business License Examination for safety design approval has started since March, 2007. To demonstrate the more scientific and rational performance of safety regulation activities on each phase for the first license procedure, CREPEI has executed demonstration tests with full scale casks, such as drop tests onto real targets without impact limiters(1) and seismic tests subjected to strong earthquake motions(2). Moreover, it is important to develop the knowledge for the inherent security of metal casks under extreme mechanical-impact conditions, especially for increasing interest since the terrorist attacks from 11th September 2001(3)-(6). This paper presents dynamic mechanical behavior of the metal cask lid closure system caused by direct aircraft engine crash and describes calculated results (especially, leak tightness based on relative dynamic displacements between metallic seals). Firstly, the local penetration damage of the interim storage facility building by a big passenger aircraft engine crash (diameter 2.7m, length 4.3m, weight 4.4ton, impact velocity 90m/s) has been examined. The reduced velocity is calculated by the local damage formula for concrete structure with its thickness of 70cm. The load vs. time function for this reduced velocity (60m/s) is estimated by the impact analysis using Finite Element code LS-DYNA with the full scale engine model onto a hypothetically rigid target. Secondly, as the most critical scenarios for the metal cask, two impact scenarios (horizontal impact hitting the cask and vertical impact onto the lid metallic seal system) are chosen. To consider the geometry of all bolts for two lids, the gasket reaction forces and the inner pressure of the cask cavity, the detailed three dimensional FEM models are

Compact, Lightweight, Ceramic Matrix Composite (CMC) Based Acoustic Liners for Reducing Subsonic Jet Aircraft Engine Noise

Science.gov (United States)

Kiser, J. Douglas; Grady, Joseph E.; Miller, Christopher J.; Hultgren, Lennart S.; Jones, Michael G.

2016-01-01

Recent developments have reduced fan and jet noise contributions to overall subsonic aircraft jet-engine noise. Now, aircraft designers are turning their attention toward reducing engine core noise. The NASA Glenn Research Center and NASA Langley Research Center have teamed to investigate the development of a compact, lightweight acoustic liner based on oxide/oxide ceramic matrix composite (CMC) materials. The NASA team has built upon an existing oxide/oxide CMC sandwich structure concept that provides monotonal noise reduction. Oxide/oxide composites have good high temperature strength and oxidation resistance, which could allow them to perform as core liners at temperatures up to 1000C (1832F), and even higher depending on the selection of the composite constituents. NASA has initiated the evaluation of CMC-based liners that use cells of different lengths (variable-depth channels) or effective lengths to achieve broadband noise reduction. Reducing the overall liner thickness is also a major goal, to minimize the volume occupied by the liner. As a first step toward demonstrating the feasibility of our concepts, an oxide/oxide CMC acoustic testing article with different channel lengths was tested. Our approach, summary of test results, current status, and goals for the future are reported.

The systems engineering overview and process (from the Systems Engineering Management Guide, 1990)

Science.gov (United States)

1993-01-01

The past several decades have seen the rise of large, highly interactive systems that are on the forward edge of technology. As a result of this growth and the increased usage of digital systems (computers and software), the concept of systems engineering has gained increasing attention. Some of this attention is no doubt due to large program failures which possibly could have been avoided, or at least mitigated, through the use of systems engineering principles. The complexity of modern day weapon systems requires conscious application of systems engineering concepts to ensure producible, operable and supportable systems that satisfy mission requirements. Although many authors have traced the roots of systems engineering to earlier dates, the initial formalization of the systems engineering process for military development began to surface in the mid-1950s on the ballistic missile programs. These early ballistic missile development programs marked the emergence of engineering discipline 'specialists' which has since continued to grow. Each of these specialties not only has a need to take data from the overall development process, but also to supply data, in the form of requirements and analysis results, to the process. A number of technical instructions, military standards and specifications, and manuals were developed as a result of these development programs. In particular, MILSTD-499 was issued in 1969 to assist both government and contractor personnel in defining the systems engineering effort in support of defense acquisition programs. This standard was updated to MIL-STD499A in 1974, and formed the foundation for current application of systems engineering principles to military development programs.

FY 1998 Report on technical results. Part 2 of 2. Research and development of supersonic transportation aircraft propulsion systems (Development of methane-fueled aircraft engines); 1998 nendo choonsoku yusokiyo suishin system no kenkyu kaihatsu seika hokokusho. 2/2. Methane nenryo kokukiyo engine no kaihatsu

Energy Technology Data Exchange (ETDEWEB)

NONE

1999-09-01

The research and development project is conducted for (1) ramjet systems, (2) high-performance turbojet systems, (3) instrumentation/control systems and (4) total systems, in order to develop methane-fueled supersonic transportation aircraft engines, and the intended targets are achieved. This project has ended with preparation of the overall plans of the target engine. Described herein is the R and D of the combined cycle engine, following the results described in Part 1 of 2. This program includes designs and development of (1) the turbojet engine, and (2) combined cycle engine. The item (1) includes studies on cycles, preparation of the overall plans and studies on the systems, and the item (2) includes the designs, ground and altitudes function tests, and ground noise tests. (NEDO)

14 CFR 33.21 - Engine cooling.

Science.gov (United States)

2010-01-01

... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Engine cooling. 33.21 Section 33.21 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION AIRCRAFT AIRWORTHINESS STANDARDS: AIRCRAFT ENGINES Design and Construction; General § 33.21 Engine cooling. Engine design and...

Commercial Aircraft Airframe Fuel Systems Survey and Analysis.

Science.gov (United States)

1982-07-01

Type of Report end Period Covered Ag Sponsorin ncy Na.e and Address FINAL REPORT U.S. DEPARTMENT OF TRANSPORTATION October, 1980 - June, 1982 FEDERAL...Philadelphia, Pennsylvania Weybridge, Surry England KT130SF Mr. Roy Riseley Mr. William Miles de Havilland Aircraft Cessna Aircraft Company Garratt Blvd. Wallace...Guido F. Pesotti Mr. Frank C. Davis Technical Director Engineering Specialist Empresa Brasileira Aeronautica, S.A. Garrett Turbine Engine Company

77 FR 50054 - Airworthiness Directives; Cessna Aircraft Company Airplanes

Science.gov (United States)

2012-08-20

... Aircraft Company Service Bulletin SB04-28-03, dated August 30, 2004, and Engine Fuel Return System... Transport Association (ATA) of America Code 2820, Aircraft Fuel Distribution System. (e) Unsafe Condition... Fuel Return System Modification Do not install Cessna Aircraft Company Service Bulletin SB 04- 28-03...

Census U.S. Civil Aircraft Calendar Year 1993

Science.gov (United States)

1993-12-31

Rotorcraft Single-Engine Mufi -Engine Multi-Engine MultI-Engm Region Total 2-Engine Single 2-Engine Single 2-Engine Other 1-3 4+ 3+ Engine 3+ Engine 3...REGION OF AIRCRAFT OWNER AS OF DECEMBER 31, 1993 P4so Turboprop Turbojet Rotoi:raf Sngle-Engie Mult-Engmn Mufi -Engiee Multi-Engine Reinr o• 2-E~nine Sigl

Essentials of aircraft armaments

CERN Document Server

Kaushik, Mrinal

2017-01-01

This book aims to provide a complete exposure about armaments from their design to launch from the combat aircraft. The book details modern ammunition and their tactical roles in warfare. The proposed book discusses aerodynamics, propulsion, structural as well as navigation, control, and guidance of aircraft armament. It also introduces the various types of ammunition developed by different countries and their changing trends. The book imparts knowledge in the field of design, and development of aircraft armaments to aerospace engineers and covers the role of the United Nations in peacekeeping and disarmament. The book will be very useful to researchers, students, and professionals working in design and manufacturing of aircraft armaments. The book will also serve air force and naval aspirants, and those interested in working on defence research and developments organizations. .

Modelling of plume chemistry of high flying aircraft with H2 combustion engines

International Nuclear Information System (INIS)

Weibring, G.; Zellner, R.

1993-01-01

Emissions from hydrogen fueled aircraft engines include large concentrations of radicals such as NO, OH, O and H. We describe the result of modelling studies in which the evolution of the radical chemistry in an expanding and cooling plume for three different mixing velocities is evaluated. The simulations were made for hydrogen combustion engines at an altitude of 26 km. For the fastest mixing conditions, the radical concentrations decrease only because of dilution with the ambient air, since the time for chemical reaction is too short. With lower mixing velocities, however, larger chemical conversions were determined. For the slowest mixing conditions the unburned hydrogen is converted into water. As a consequence the radicals O and OH increase considerably around 1400 K. The only exception being NO, for which no chemical change during the expansion is found. The concentrations of the reservoir molecules like H 2 O 2 , N 2 O 5 or HNO 3 have been calculated to remain relatively small. (orig.)

Full-scale tornado-missile impact tests. Interim report

International Nuclear Information System (INIS)

Stephenson, A.E.

1976-04-01

Seven completed initial tests are described with 4 types of hypothetical tornado-borne missiles (impacting reinforced concrete panels that are typical of walls in nuclear power facilities). The missiles were rocket propelled to velocities currently postulated as being attainable by debris in tornadoes. (1500-pound 35-foot long utility pole; 8-pound 1-inch Grade 60 reinforcing bar; 78-pound 3-inch Schedule 40 pipe; and 743-pound 12-inch Schedule 40 pipe;) The results show that a minimum thickness of 24 inches is sufficient to prevent backface scabbing from normal impacts of currently postulated tornado missiles and that existing power plant walls are adequate for the most severe conditions currently postulated by regulatory agencies. This report gives selected detailed data on the tests completed thus far, including strain, panel velocity, and reaction histories

The Development of the US National Missile Defense and its Impact on the International Security

Directory of Open Access Journals (Sweden)

J. Yu. Parshkova

2015-01-01

Full Text Available The article reflects the US officials' point of view on the development of its national missile defense. The major threat to international security is the proliferation of ballistic missiles and weapons of mass destruction. The United States and the former Soviet Union made huge efforts to reduce and limit offensive arms. However, presently the proliferation of ballistic missiles spreads all over the world, especially in the Middle East, because of the ballistic missile technology falling into the hands of hostile non-state groups. Missile defenses can provide a permanent presence in a region and discourage adversaries from believing they can use ballistic missiles to coerce or intimidate the U.S. or its allies. With the possible attack regional missile defense systems will be promptly mobilized to enhance an effective deterrent. The ultimate goal of such large-scale missile defense deployment is to convince the adversaries that the use of ballistic missiles is useless in military terms and that any attack on the United States and its allies is doomed to failure. The United States has missile defense cooperative programs with a number of allies, including United Kingdom, Japan, Australia, Israel, Denmark, Germany, Netherlands, Czech Republic, Poland, Italy and many others. The Missile Defense Agency also actively participates in NATO activities to maximize opportunities to develop an integrated NATO ballistic missile defense capability. The initiative of the development of US BMD naturally belongs to the United States. That country has enormous technological, financial, economic, military and institutional capabilities, exceeding by far those of the other NATO members combined.

75 FR 52732 - Renewal of Department of Defense Federal Advisory Committee; Missile Defense Advisory Committee

Science.gov (United States)

2010-08-27

... Committee; Missile Defense Advisory Committee AGENCY: Department of Defense (DoD). ACTION: Renewal of..., the Department of Defense gives notice that it is renewing the charter for the Missile Defense... Director, Missile Defense Agency, independent advice and recommendations on all matters relating to missile...

Combining effect of optimized axial compressor variable guide vanes and bleed air on the thermodynamic performance of aircraft engine system

International Nuclear Information System (INIS)

Kim, Sangjo; Son, Changmin; Kim, Kuisoon

2017-01-01

Aim of this work is to provide evidence of the effectiveness of combined use of the variable guide vanes (VGVs) and bleed air on the thermodynamic performance of aircraft engine system. This paper performed the comparative study to evaluate the overall thermal performance of an aircraft engine with optimized VGVs and bleed air, separately or simultaneously. The low-bypass ratio turbofan engine has been modeled with a 0D/1D modeling approach. The genetic algorithm is employed to find the optimum schedule of VGVs and bleed air. There are four types of design variables: (1) the inlet guide vane (IGV) angle, (2) the IGV and 1st stator vane (SV) angles, (3) bleed air mass flow rate at the exit of the axial compressor, and (4) both type 2 and type 3. The optimization is conducted with surge margin constraints of more than 10% and 15% in the axial compressor. The results show that the additional use of the bleed air increases the efficiency of the compressors. Overall, the percentage reductions of the total fuel consumption for the engine with the IGV, 1st SV and bleed air schedule is 1.63% for 15% surge margin constraints when compared with the engine with the IGV schedule. - Highlights: • The effect of combined use of variable guide vanes and bleed air is evaluated. • The genetic algorithm is employed to find the optimum setting angle and bleed air. • A low bypass ratio mixed turbofan engine is analyzed for optimization. • Additional use of the bleed air shows improved overall performance of the engine.

Achievement report on research and development in the Sunshine Project in fiscal 1976. Comprehensive discussion on hydrogen utilizing subsystems and research on peripheral technologies (Research for aircraft engines); 1976 nendo suiso riyo subsystem no sogoteki kento to shuhen gijutsu ni kansuru kenkyu seika hokokusho. Koku engine ni kansuru kenkyu

Energy Technology Data Exchange (ETDEWEB)

NONE

1977-05-01

With an objective to utilize hydrogen fuel in aircraft engines, a conceptual design survey was carried out on medium size transport aircraft. Large size long-distance aircraft and SST loaded with a great amount of fuel have the jet fuel (JP) increase take-off weight, affecting largely the selection of wing area and engine thrust. If the hydrogen fuel can be liquefied, large reduction can be achieved and the economic effect can be increased. However, for short-distance transport aircraft, the fuel weight ratio is small, where no large advantage is anticipated even if hydrogen is liquefied. Nevertheless, considering oil depletion in the future, a conceptual design was performed on the YX2688 short-medium distance aircraft being discussed of development. Even the short-medium distance aircraft that can be developed and commercialized as civilian use aircraft has a number of common points with large aircraft development, such as hydrogen fuel using technologies and safety. Although the advantage of using liquefied hydrogen as fuel may of course be smaller in the short-medium distance aircraft than in larger aircraft, the trend of using hydrogen fuel is historical necessity, whose development plans should be moved forward. (NEDO)

Environmental compatibility of CRYOPLANE the cryogenic-fuel aircraft

Energy Technology Data Exchange (ETDEWEB)

Klug, H.G. [Daimler Benz Aerospace Airbus, Hamburg (Germany)

1997-12-31

`CRYOPLANE` is the project name for an aircraft powered by cryogenic fuel, either liquid natural gas (LNG, mainly consisting of methane) or liquid hydrogen (LH{sub 2}). Emission of CO{sub 2}, unburnt hydrocarbons, soot and sulfur will be completely avoided by hydrogen combustion: LH{sub 2} is an extremely pure liquid. Emission of water as a primary combustion product is increased by a factor of 2.6. Exhaust gases behind hydrogen engines contain more water than behind kerosene engines, and hence can form contrails under a wider range of atmospheric conditions. Liquid hydrogen fueled aircraft promise big advantages relative to kerosene aircraft in terms of environmental compatibility. (R.P.)

Environmental compatibility of CRYOPLANE the cryogenic-fuel aircraft

Energy Technology Data Exchange (ETDEWEB)

Klug, H G [Daimler Benz Aerospace Airbus, Hamburg (Germany)

1998-12-31

`CRYOPLANE` is the project name for an aircraft powered by cryogenic fuel, either liquid natural gas (LNG, mainly consisting of methane) or liquid hydrogen (LH{sub 2}). Emission of CO{sub 2}, unburnt hydrocarbons, soot and sulfur will be completely avoided by hydrogen combustion: LH{sub 2} is an extremely pure liquid. Emission of water as a primary combustion product is increased by a factor of 2.6. Exhaust gases behind hydrogen engines contain more water than behind kerosene engines, and hence can form contrails under a wider range of atmospheric conditions. Liquid hydrogen fueled aircraft promise big advantages relative to kerosene aircraft in terms of environmental compatibility. (R.P.)

Windmilling of turbofan engine; calculation of performance characteristics of a turbofan engine under windmilling

NARCIS (Netherlands)

Ramanathan, A.

2014-01-01

The turbofan is a type of air breathing jet engine that finds wide use in aircraft propulsion. During the normal operation of a turbofan engine installed in aircraft, the combustor is supplied with fuel, flow to the combustor is cut off and the engine runs under so called Windmilling conditions

Combat aircraft noise

Science.gov (United States)

Sgarbozza, M.; Depitre, A.

1992-04-01

A discussion of the characteristics and the noise levels of combat aircraft and of a transport aircraft in taking off and landing are presented. Some methods of noise reduction are discussed, including the following: operational anti-noise procedures; and concepts of future engines (silent post-combustion and variable cycle). Some measurement results concerning the noise generated in flight at great speeds and low altitude will also be examined. Finally, the protection of the environment of French air bases against noise will be described and the possibilities of regulation examined.

Data Fusion for Enhanced Aircraft Engine Prognostics and Health Management

Science.gov (United States)

Volponi, Al

2005-01-01

Aircraft gas-turbine engine data is available from a variety of sources, including on-board sensor measurements, maintenance histories, and component models. An ultimate goal of Propulsion Health Management (PHM) is to maximize the amount of meaningful information that can be extracted from disparate data sources to obtain comprehensive diagnostic and prognostic knowledge regarding the health of the engine. Data fusion is the integration of data or information from multiple sources for the achievement of improved accuracy and more specific inferences than can be obtained from the use of a single sensor alone. The basic tenet underlying the data/ information fusion concept is to leverage all available information to enhance diagnostic visibility, increase diagnostic reliability and reduce the number of diagnostic false alarms. This report describes a basic PHM data fusion architecture being developed in alignment with the NASA C-17 PHM Flight Test program. The challenge of how to maximize the meaningful information extracted from disparate data sources to obtain enhanced diagnostic and prognostic information regarding the health and condition of the engine is the primary goal of this endeavor. To address this challenge, NASA Glenn Research Center, NASA Dryden Flight Research Center, and Pratt & Whitney have formed a team with several small innovative technology companies to plan and conduct a research project in the area of data fusion, as it applies to PHM. Methodologies being developed and evaluated have been drawn from a wide range of areas including artificial intelligence, pattern recognition, statistical estimation, and fuzzy logic. This report will provide a chronology and summary of the work accomplished under this research contract.

EKF-based fault detection for guided missiles flight control system

Science.gov (United States)

Feng, Gang; Yang, Zhiyong; Liu, Yongjin

2017-03-01

The guided missiles flight control system is essential for guidance accuracy and kill probability. It is complicated and fragile. Since actuator faults and sensor faults could seriously affect the security and reliability of the system, fault detection for missiles flight control system is of great significance. This paper deals with the problem of fault detection for the closed-loop nonlinear model of the guided missiles flight control system in the presence of disturbance. First, set up the fault model of flight control system, and then design the residual generation based on the extended Kalman filter (EKF) for the Eulerian-discrete fault model. After that, the Chi-square test was selected for the residual evaluation and the fault detention task for guided missiles closed-loop system was accomplished. Finally, simulation results are provided to illustrate the effectiveness of the approach proposed in the case of elevator fault separately.

The Intercontinental Ballistic Missile and Post Cold War Deterrence

Science.gov (United States)

2010-02-17

Bonnetain, Hugues and Philippe Mazzoni. " Histoire De Missiles...Le 1er GMS Du Plateau D’Albion." http://www.capcomespace.net/dossiers/espace_europeen...Mazzoni, " Histoire De Missiles...Le 1er GMS Du Plateau D’Albion," http://www.capcomespace.net/dossiers/espace_europeen/albion/; Ministère de la Défense

Advanced rotary engine studies

Science.gov (United States)

Jones, C.

1980-01-01

A review of rotary engine developments relevant to a stratified charge rotary aircraft engine is presented. Advantages in module size and weight, fuel efficiency, reliability, and multi-fuel capability are discussed along with developments in turbocharging, increased mean effective pressure, improved apex seal/trochoid wear surfacing materials, and high strength and temperature aluminum casting alloys. A carbureted prototype aircraft engine is also described.

The Secret of Guided Missile Re-Entry,

Science.gov (United States)

1986-06-25

I RD-PAI169 598 THE SECRET OF GUIDED MISSILE RE-ENTRY(U) FOREIGN / I TECHNOLOGY DIV NRIGHT-PATTERSON RFB OH J CHEN ET AL. I 25 JUN 96 FTD-ID(RS)T...TECHNOLOGY DIVISION THE SECRET OF GUIDED MISSILE RE-ENTRY by Chen Jingzhong, An Sehua J L 0 7 ’:;85’ ’ 0 *Approved for public release; Distribution...unlimite t d. :. 86 7 034.. FTD- ID(RS)T-0459-86 HUMAN TRANSLATION FTD-ID(RS)T-0459-86 25 June 1986 MICROFICHE NR: F - - 0Q 9? THE SECRET OF GUIDED

Advanced rotary engines

Science.gov (United States)

Jones, C.

1983-01-01

The broad objectives of this paper are the following: (1) to summarize the Curtiss-Wright design, development and field testing background in the area of rotary aircraft engines; (2) to briefly summarize past activity and update development work in the area of stratified charge rotary combustion engines; and (3) to discuss the development of a high-performance direct injected unthrottled stratified charge rotary combustion aircraft engine. Efficiency improvements through turbocharging are also discussed.

Distributed cooperative guidance for multiple missiles with fixed and switching communication topologies

Directory of Open Access Journals (Sweden)

Qilun ZHAO

2017-08-01

Full Text Available This study investigates cooperative guidance problems for multiple missiles with fixed and switching directed communication topologies. A two-step guidance strategy is proposed to realize the simultaneous attack. In the first step, a distributed cooperative guidance law is designed using local neighboring information for multiple missiles to achieve consensus on range-to-go and leading angle. The second step begins when the consensus of multiple missiles is realized. During the second step, multiple missiles disconnect from each other and hit the target using the proportional navigation guidance law. First, based on the local neighboring communications, a sufficient condition for multiple missiles to realize simultaneous attack with a fixed communication topology is presented, where the topology is only required to have a directed spanning tree. Then, the results are extended to the case of switching communication topologies. Finally, numerical simulations are provided to validate the theoretical results.

Aircraft/Stores Compatibility, Integration and Separation Testing (Essais de compatibilite, d’integration et de separation des emports sur aeronef)

Science.gov (United States)

2014-09-01

Interface Control Document ID Identification JMPS Joint Mission Planning System LAR Launch Acceptability Region LGB Laser Guided Bombs LOAL...Dump/unguided Cluster Bombs (CBUs); • Laser -Guided Bombs (LGBs); • Inertial-Aided Munitions (IAMs); • Air Intercept Missiles (AIMs); and • Air-to...light stores may be operated by energizing a solenoid to open the hooks. On these systems, the store falls away from the aircraft under the

Feasibility of missile guidance using MEMS-based active flow control

International Nuclear Information System (INIS)

DeChamplain, A.; Hamel, N.; Rainville, P.-A.; Gosselin, P.; Wong, F.

2002-01-01

The aim of this study was to evaluate the feasibility to control a missile or rocket by mean of an active flow control device such as MEMS (Micro Electro Mechanical Systems) in the form of a microbubble. For this simple aerodynamic form coupled to the geometry of a generic missile, different microbubble arrangements can have a very significant impact in steady operation. Using CFD, combinations of different microbubble configurations (ratio between the apparent diameter and apparent height) and positions on the surface of the missile were evaluated for their impact on overall system performance for a missile flying at Mach 2.5 at an altitude of 6 km at a zero angle of attack. From a validation study with the generic missile geometry tested experimentally, the Fluent commercial code gave an excellent accuracy of 2% for the drag coefficient. With the appropriate numerical parameters from the validation, different configurations of microbubble(s) were simulated to give only marginal changes to the coefficient of moment as compared to experimental values at an angle of attack of 14 degrees. Considering the major advantages in weight and space savings, this would certainly be a technology to implement for small changes in guidance parameters. (author)

A New Predictive Model Based on the ABC Optimized Multivariate Adaptive Regression Splines Approach for Predicting the Remaining Useful Life in Aircraft Engines

Directory of Open Access Journals (Sweden)

Paulino José García Nieto

2016-05-01

Full Text Available Remaining useful life (RUL estimation is considered as one of the most central points in the prognostics and health management (PHM. The present paper describes a nonlinear hybrid ABC–MARS-based model for the prediction of the remaining useful life of aircraft engines. Indeed, it is well-known that an accurate RUL estimation allows failure prevention in a more controllable way so that the effective maintenance can be carried out in appropriate time to correct impending faults. The proposed hybrid model combines multivariate adaptive regression splines (MARS, which have been successfully adopted for regression problems, with the artificial bee colony (ABC technique. This optimization technique involves parameter setting in the MARS training procedure, which significantly influences the regression accuracy. However, its use in reliability applications has not yet been widely explored. Bearing this in mind, remaining useful life values have been predicted here by using the hybrid ABC–MARS-based model from the remaining measured parameters (input variables for aircraft engines with success. A correlation coefficient equal to 0.92 was obtained when this hybrid ABC–MARS-based model was applied to experimental data. The agreement of this model with experimental data confirmed its good performance. The main advantage of this predictive model is that it does not require information about the previous operation states of the aircraft engine.

Potential hazard to secondary containment from HCDA-generated missiles and sodium fires

International Nuclear Information System (INIS)

Romander, C.M.

1979-02-01

The potential hazard of HCDA-generated missiles is analyzed, and the current status of the potential hazards of sodium fires is summarized. Simple analyses are performed to determine lower bounds on the HCDA energetics required to generate missiles that could reach the secondary containment structure of a 1000-MWe LMFBR. The potential missiles considered include the vessel head, components mounted on the head, and conrol rods

Aircraft engine exhaust emissions and other airport-related contributions to ambient air pollution: A review

Science.gov (United States)

Masiol, Mauro; Harrison, Roy M.

2014-10-01

Civil aviation is fast-growing (about +5% every year), mainly driven by the developing economies and globalisation. Its impact on the environment is heavily debated, particularly in relation to climate forcing attributed to emissions at cruising altitudes and the noise and the deterioration of air quality at ground-level due to airport operations. This latter environmental issue is of particular interest to the scientific community and policymakers, especially in relation to the breach of limit and target values for many air pollutants, mainly nitrogen oxides and particulate matter, near the busiest airports and the resulting consequences for public health. Despite the increased attention given to aircraft emissions at ground-level and air pollution in the vicinity of airports, many research gaps remain. Sources relevant to air quality include not only engine exhaust and non-exhaust emissions from aircraft, but also emissions from the units providing power to the aircraft on the ground, the traffic due to the airport ground service, maintenance work, heating facilities, fugitive vapours from refuelling operations, kitchens and restaurants for passengers and operators, intermodal transportation systems, and road traffic for transporting people and goods in and out to the airport. Many of these sources have received inadequate attention, despite their high potential for impact on air quality. This review aims to summarise the state-of-the-art research on aircraft and airport emissions and attempts to synthesise the results of studies that have addressed this issue. It also aims to describe the key characteristics of pollution, the impacts upon global and local air quality and to address the future potential of research by highlighting research needs.

Noise transmission through sidewall treatments applicable to twin-engine turboprop aircraft

Science.gov (United States)

Grosveld, F. W.

1983-04-01

The noise transmission loss characteristics of the sidewall treatment in the propeller plane of a twin-engine turboprop aircraft are experimentally investigated in the NASA Langley Research Center Transmission Loss Facility. The sound attenuation properties of the individual elements of this treatment are evaluated showing least noise transmission loss in the low frequencies (below 500 Hz) where the excitation levels at the propeller blade passage frequency and the first few harmonics are highest. It is shown that single and double wall resonances play an important role in the noise transmission loss values of the treatment at these low frequencies suggesting that a limp mass with a very low resonance frequency serves better as a trim panel than a trim panel having a high structural stiffness. It is indicated that the window structures might be a potential noise control problem.

Numerical simulation of tornado-borne missile impact on reinforced concrete targets

International Nuclear Information System (INIS)

Tu, D.K.; Larder, R.

1979-02-01

This study is a continuation of the Lawrence Livermore Laboratory (LLL) effort to evaluate the applicability of using the finite element procedure to numerically simulate the impact of tornado-borne missiles on reinforced concrete targets. The objective of this study is to assess the back-face scab threshold of a reinforced concrete target impacted by deformable and nondeformable missiles. Several simulations were run using slug and pipe-type impacting missiles. The numerical results were compared with full-scale experimental field tests

14 CFR 63.42 - Flight engineer certificate issued on basis of a foreign flight engineer license.

Science.gov (United States)

2010-01-01

... section, may have a flight engineer certificate issued to him for the operation of civil aircraft of U.S... engineer certificate issued under this section may act as a flight engineer of a civil aircraft of U.S... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Flight engineer certificate issued on basis...

Missile defence : An overview

NARCIS (Netherlands)

Weimar, P.W.L.

2012-01-01

At the present day, an unparalleled number of international actors, be it national governments or non-state groups, have acquired or are seeking to acquire both weapons of mass destruction and the means to deliver them. Those means of delivery can be Ballistic Missiles that can bridge vast – even

Classification of soft and hard impacts-Application to aircraft crash

International Nuclear Information System (INIS)

Koechlin, Pierre; Potapov, Serguei

2009-01-01

Before modeling an aircraft crash on a shield building of a nuclear power plant, it is very important to understand the physical phenomena and the structural behavior associated with this kind of impact. In the scientific literature, aircraft crash is classified as a soft impact, or as an impact of deformable missile. Nevertheless the existing classifications are not precise enough to be able to predict 'a priori' the structural response mode. The aim of this paper is to characterize very precisely what is a soft and a hard impact in the frame of aircraft crash on nuclear power plant. First the existing qualitative definition of soft and hard impact is quickly reviewed in order to introduce a new criterion to make a quantitative distinction between soft and hard impact. Then the experimental tests carried out during the last thirty years in the research field of aircraft crash are presented in the light of the new classification. The authors show that this characterization of soft and hard impacts has a real physical interest because it is linked to the failure mode for perforation: for soft impacts, perforation is the consequence of a shear plug breaking away and for hard impact it comes from local failure and projectile penetration. Moreover the boundary between soft and hard impact is the limit for the use of an impact force in an uncoupled computation of the impact

Full-scale impact test data for tornado-missile design of nuclear plants

International Nuclear Information System (INIS)

Stephenson, A.E.; Sliter, G.E.

1977-01-01

It is standard practice to consider the effects of low-probability impacts of tornado-borne debris (''tornado missiles'' such as utility poles and steel pipes) in the structural design of nuclear power plants in the United States. To provide data that can be used directly in the design procedure, a series of full-scale tornado-missile impact tests was performed. This paper is a brief summary of the results and conclusions from these tests. The tests consisted of reinforced concrete panels impacted by poles, pipes, and rods propelled by a rocket sled. The panels were constructed to current minimum standards and had thicknesses typical of auxiliary buildings of nuclear power plants. A specific objective was the determination of the impact velocities below which the panels do not experience backface scabbing. Another objective was to assess the adequacy of (1) conventional design formulae for penetration and scabbing and (2) conventional design methods for overall structural response. Test missiles and velocities represented those in current design standards. Missiles included utility poles, steel pipes, and steel bars. It is important to interpret the data in this paper in recognition that the test conditions represent conservative assumptions regarding maximum wind speeds, injection of the missile into the wind stream, aerodynamic trajectory, and orientation of missile at impact. Even with the severe assumptions made, the full-scale tests described demonstrate the ability of prototypical nuclear plant walls and roofs to provide adequate protection against postulated tornado-missile impact

Missile Electro-Optical Countermeasures Simulation Laboratory

Data.gov (United States)

Federal Laboratory Consortium — This laboratory comprises several hardware-in-the-loop missile flight simulations designed specifically to evaluate the effectiveness of electro-optical air defense...

Soviet debate on missile defense

Energy Technology Data Exchange (ETDEWEB)

Parrott, B.

1987-04-01

Although the Strategic Defense Initiative (SDI) is meant to cope with the danger of a Soviet nuclear attack, the recent US debate over SDI has paid surprisingly little attention to Soviet views of ballistic missile defense. Despite the existence of a substantial body of pertinent scholarship, the debate has failed to take adequate account of major changes in Soviet ballistic missile defense policy since the mid-1960s. It has also neglected the links between current Soviet military policy and broader Soviet political and economic choices. The Soviets regard SDI not as a novel undertaking to reduce the risks of nuclear war but as an extension of the geopolitical competition between the superpowers. This competition has been dominated in the 1980s, in the Soviet view, by sharply increased US assertiveness and the decline of detente. Viewing SDI as a manifestation of these general trends, Soviet decision makers find the prospect of an unregulated race in ballistic missile defenses and military space technologies deeply unsettling. The deterioration of superpower relations has raised serious doubts in Moscow about the wisdom of Soviet external policy during the 1970s and has provoked sharp internal differences over policy toward the US. Already highly suspicious of the Reagan administration, the elite is united by a general conviction that SDI is an American gambit that may ultimately undercut past Soviet strategic gains and pose a grave new threat to Soviet security. 14 references.

Real-Time Target Motion Animation for Missile Warning System Testing

Science.gov (United States)

2006-04-01

T. Perkins, R. Sundberg, J. Cordell, Z. Tun , and M. Owen, Real-time Target Motion Animation for Missile Warning System Testing, Proc. SPIE Vol 6208...Z39-18 Real-time target motion animation for missile warning system testing Timothy Perkins*a, Robert Sundberga, John Cordellb, Zaw Tunb, Mark

Lateral control strategy for a hypersonic cruise missile

Directory of Open Access Journals (Sweden)

Yonghua Fan

2017-04-01

Full Text Available Hypersonic cruise missile always adopts the configuration of waverider body with the restraint of scramjet. As a result, the lateral motion exhibits serious coupling, and the controller design of the lateral lateral system cannot be conducted separately for yaw channel and roll channel. A multiple input and multiple output optimal control method with integrators is presented to design the lateral combined control system for hypersonic cruise missile. A hypersonic cruise missile lateral model is linearized as a multiple input and multiple output plant, which is coupled by kinematics and fin deflection between yaw and roll. In lateral combined controller, the integrators are augmented, respectively, into the loop of roll angle and lateral overload to ensure that the commands are tracked with zero steady-state error. Through simulation, the proposed controller demonstrates good performance in tracking the command of roll angle and lateral overload.

Selected Aircraft Throttle Controller With Support Of Fuzzy Expert Inference System

Directory of Open Access Journals (Sweden)

Żurek Józef

2014-12-01

Full Text Available The paper describes Zlin 143Lsi aircraft engine work parameters control support method – hourly fuel flow as a main factor under consideration. The method concerns project of aircraft throttle control support system with use of fuzzy logic (fuzzy inference. The primary purpose of the system is aircraft performance optimization, reducing flight cost at the same time and support proper aircraft engine maintenance. Matlab Software and Fuzzy Logic Toolbox were used in the project. Work of the system is presented with use of twenty test samples, five of them are presented graphically. In addition, system control surface, included in the paper, supports system all work range analysis.

76 FR 14589 - Defense Federal Acquisition Regulation Supplement; Repeal of Restriction on Ballistic Missile...

Science.gov (United States)

2011-03-17

...-AH18 Defense Federal Acquisition Regulation Supplement; Repeal of Restriction on Ballistic Missile...). Section 222 repeals the restriction on purchase of Ballistic Missile Defense research, development, test... Ballistic Missile Defense research, development, test, and evaluation that was required by section 222 of...

Quiet engine program flight engine design study

Science.gov (United States)

Klapproth, J. F.; Neitzel, R. E.; Seeley, C. T.

1974-01-01

The results are presented of a preliminary flight engine design study based on the Quiet Engine Program high-bypass, low-noise turbofan engines. Engine configurations, weight, noise characteristics, and performance over a range of flight conditions typical of a subsonic transport aircraft were considered. High and low tip speed engines in various acoustically treated nacelle configurations were included.

An experimental evaluation of the performance deficit of an aircraft engine starter turbine

Science.gov (United States)

Haas, J. E.; Roelke, R. J.; Hermann, P.

1980-01-01

An experimental investigation is presented to determine the aerodynamic performance deficit of a 13.5 - centimeter-tip-diameter aircraft engine starter turbine. The two-phased evaluation comprised both the stator and the stage performance, and the experimental design is described in detail. Data obtained from the investigation of three honeycomb shrouds clearly showed that the filled honeycomb reached a total efficiency of 0.868, 8.2 points higher than the open honeycomb shroud, at design equivalent conditions of speed and blade-jet speed ratio. It was concluded that the use of an open honeycomb shroud caused the large performance deficit for the starter turbine. Further research is suggested to ascertain stator inlet boundary layer measurements.

Probabilistic analysis of turbine missile damage to nuclear power plant structures

International Nuclear Information System (INIS)

Twisdale, L.A.; Dunn, W.L.; Frank, R.A.

1983-01-01

This paper summarizes the results of the EPRI project that focused on the development of the overall probabilistic methodology to assess the risks of turbine missile induced damage to nuclear power plant structures and components. The project was structured to use the results of other EPRI projects that provided information on turbine failure and missile generation frequencies, models to predict the characteristics and exit conditions of the missiles, and experimental data for use in updating empirical impact formulas for reinforced concrete barriers. The research effort included: (1) adaptation and implementation of the missile generation probability and turbine casing impact models developed in Ref. [2]; (2) development of a methodology for the prediction of the motion of the postulated missile fragments that perforate the turbine casing; (3) development of a model using the experimental impact data to predict the effects of fragment impact on nuclear power plant barriers and components; (4) construction of a probabilistic damage assessment methodology using Monte Carlo simulation methodology; and (5) implementation of the methodology into an independent computer program (TURMIS), demonstration of its application to an example case study problem, and assessment of prediction sensitivity. (orig./RW)

Liquid Missile Fuels as Means of Chemical Terrorist Attack

International Nuclear Information System (INIS)

Superina, V.; Orehovec, Z.

2007-01-01

Modern world is faced with numerous terrorist attacks whose goals, methods and means of the conduct are various. It seems that we have entered the era when terrorism, one's own little terrorism, is the easiest and the most painless way of achieving a goal. That is why that such a situation has contributed to the necessity for strengthening individual and collective protection and safety, import and export control, control of the production and illegal sale of the potential means for delivering terrorist act. It has also contributed to the necessity for devising means of the delivery. For more than 10 years, a series of congresses on CB MTS Industry has pointed at chemicals and chemical industry as potential means and targets of terrorism. The specialization and experience of different authors in the field of the missile technology and missile fuels, especially those of Eastern origin, and the threat that was the reality of the war conflicts in 1990s was the reason for making a scientific and expert analysis of the liquid missile fuels as means of terrorism. There are not many experts in the field of NBC protection who are familiar with the toxicity and reaction of liquid missile fuels still lying discarded and unprotected in abandoned barracks all over Europe and Asia. The purpose of this paper is to draw public attention to possible different abuses of liquid missile fuels for a terrorist purpose, as well as to possible consequences and prevention measures against such abuses. (author)

Shock vibration and damage responses of primary auxiliary buildings from aircraft impact

Energy Technology Data Exchange (ETDEWEB)

Shin, Sang Shup [Korea Atomic Energy Research Institute, 1045 Daeduk-daero, Dukjin-dong, Yuseong-gu, Daejeon 305-303 (Korea, Republic of); Department of Civil and Environmental Engineering, Hanyang University, Seoul 133-791 (Korea, Republic of); Hahm, Daegi [Korea Atomic Energy Research Institute, 1045 Daeduk-daero, Dukjin-dong, Yuseong-gu, Daejeon 305-303 (Korea, Republic of); Park, Taehyo, E-mail: cepark@hanyang.ac.kr [Department of Civil and Environmental Engineering, Hanyang University, Seoul 133-791 (Korea, Republic of)

2016-12-15

Highlights: • Aircraft impact analyses of PABs were performed using both the force-time history method and missile-target interaction method. • The jet fuel was considered by using the added mass modeling method and SPH method, respectively. • The FRS and the structural integrity of the external wall of the PABs against an aircraft impact were analyzed. - Abstract: Safety assessments on nuclear power plants (NPPs) subjected to an aircraft impact (AI) caused by terrorists are pivotal focuses for amelioration of present. To date, most studies have mainly focused on structure responses and the integrity of the containment building at a nuclear island (NI) subjected to AI. However, the safety assessment of internal equipment and components by shock vibration as well as the structure damage induced by AI are also important. In this study, aircraft impact analyses (AIA) of primary auxiliary buildings (PABs) were carried out using both the force–time history method and the missile–target interaction method. For the AIA, the jet fuel was taken into account by using the added mass modeling method and the smooth particles hydrodynamics (SPH) method, respectively. In addition, the floor response spectra (FRS) and the structural integrity of the external wall of the PAB against an AI were analyzed. Finally, the difference in the FRS at the location of the components on both sides of the bay was analyzed.

Modeling Programs Increase Aircraft Design Safety

Science.gov (United States)

2012-01-01

Flutter may sound like a benign word when associated with a flag in a breeze, a butterfly, or seaweed in an ocean current. When used in the context of aerodynamics, however, it describes a highly dangerous, potentially deadly condition. Consider the case of the Lockheed L-188 Electra Turboprop, an airliner that first took to the skies in 1957. Two years later, an Electra plummeted to the ground en route from Houston to Dallas. Within another year, a second Electra crashed. In both cases, all crew and passengers died. Lockheed engineers were at a loss as to why the planes wings were tearing off in midair. For an answer, the company turned to NASA s Transonic Dynamics Tunnel (TDT) at Langley Research Center. At the time, the newly renovated wind tunnel offered engineers the capability of testing aeroelastic qualities in aircraft flying at transonic speeds near or just below the speed of sound. (Aeroelasticity is the interaction between aerodynamic forces and the structural dynamics of an aircraft or other structure.) Through round-the-clock testing in the TDT, NASA and industry researchers discovered the cause: flutter. Flutter occurs when aerodynamic forces acting on a wing cause it to vibrate. As the aircraft moves faster, certain conditions can cause that vibration to multiply and feed off itself, building to greater amplitudes until the flutter causes severe damage or even the destruction of the aircraft. Flutter can impact other structures as well. Famous film footage of the Tacoma Narrows Bridge in Washington in 1940 shows the main span of the bridge collapsing after strong winds generated powerful flutter forces. In the Electra s case, faulty engine mounts allowed a type of flutter known as whirl flutter, generated by the spinning propellers, to transfer to the wings, causing them to vibrate violently enough to tear off. Thanks to the NASA testing, Lockheed was able to correct the Electra s design flaws that led to the flutter conditions and return the

Preliminary Axial Flow Turbine Design and Off-Design Performance Analysis Methods for Rotary Wing Aircraft Engines. Part 1; Validation

Science.gov (United States)

Chen, Shu-cheng, S.

2009-01-01

For the preliminary design and the off-design performance analysis of axial flow turbines, a pair of intermediate level-of-fidelity computer codes, TD2-2 (design; reference 1) and AXOD (off-design; reference 2), are being evaluated for use in turbine design and performance prediction of the modern high performance aircraft engines. TD2-2 employs a streamline curvature method for design, while AXOD approaches the flow analysis with an equal radius-height domain decomposition strategy. Both methods resolve only the flows in the annulus region while modeling the impact introduced by the blade rows. The mathematical formulations and derivations involved in both methods are documented in references 3, 4 for TD2-2) and in reference 5 (for AXOD). The focus of this paper is to discuss the fundamental issues of applicability and compatibility of the two codes as a pair of companion pieces, to perform preliminary design and off-design analysis for modern aircraft engine turbines. Two validation cases for the design and the off-design prediction using TD2-2 and AXOD conducted on two existing high efficiency turbines, developed and tested in the NASA/GE Energy Efficient Engine (GE-E3) Program, the High Pressure Turbine (HPT; two stages, air cooled) and the Low Pressure Turbine (LPT; five stages, un-cooled), are provided in support of the analysis and discussion presented in this paper.

Tip-Clearance Measurement in the First Stage of the Compressor of an Aircraft Engine

Directory of Open Access Journals (Sweden)

Iker García

2016-11-01

Full Text Available In this article, we report the design of a reflective intensity-modulated optical fiber sensor for blade tip-clearance measurement, and the experimental results for the first stage of a compressor of an aircraft engine operating in real conditions. The tests were performed in a ground test cell, where the engine completed four cycles from idling state to takeoff and back to idling state. During these tests, the rotational speed of the compressor ranged between 7000 and 15,600 rpm. The main component of the sensor is a tetrafurcated bundle of optical fibers, with which the resulting precision of the experimental measurements was 12 µm for a measurement range from 2 to 4 mm. To get this precision the effect of temperature on the optoelectronic components of the sensor was compensated by calibrating the sensor in a climate chamber. A custom-designed MATLAB program was employed to simulate the behavior of the sensor prior to its manufacture.

The role of strategic missile defence in the global architecture de ballistic non proliferation

International Nuclear Information System (INIS)

Hautecouverture, Benjamin

2007-01-01

Whereas some think that missile defence is a proliferation agent by nature and therefore undermines the already fragile regime of ballistic non proliferation, some others think that missile defence could underpin the non proliferation regime. The author thus discusses these issues and both points of view by commenting the ambiguous discursive relationships between missile defence and arms control, and by highlighting the various roles and missions given to missile defence, notably in treaties (like the ABM treaty) and postures adopted by concerned countries

Study on combat effectiveness of air defense missile weapon system based on queuing theory

Science.gov (United States)

Zhao, Z. Q.; Hao, J. X.; Li, L. J.

2017-01-01

Queuing Theory is a method to analyze the combat effectiveness of air defense missile weapon system. The model of service probability based on the queuing theory was constructed, and applied to analyzing the combat effectiveness of "Sidewinder" and "Tor-M1" air defense missile weapon system. Finally aimed at different targets densities, the combat effectiveness of different combat units of two types' defense missile weapon system is calculated. This method can be used to analyze the usefulness of air defense missile weapon system.

Deicing System Protects General Aviation Aircraft

Science.gov (United States)

2007-01-01

Kelly Aerospace Thermal Systems LLC worked with researchers at Glenn Research Center on deicing technology with assistance from the Small Business Innovation Research (SBIR) program. Kelly Aerospace acquired Northcoast Technologies Ltd., a firm that had conducted work on a graphite foil heating element under a NASA SBIR contract and developed a lightweight, easy-to-install, reliable wing and tail deicing system. Kelly Aerospace engineers combined their experiences with those of the Northcoast engineers, leading to the certification and integration of a thermoelectric deicing system called Thermawing, a DC-powered air conditioner for single-engine aircraft called Thermacool, and high-output alternators to run them both. Thermawing, a reliable anti-icing and deicing system, allows pilots to safely fly through ice encounters and provides pilots of single-engine aircraft the heated wing technology usually reserved for larger, jet-powered craft. Thermacool, an innovative electric air conditioning system, uses a new compressor whose rotary pump design runs off an energy-efficient, brushless DC motor and allows pilots to use the air conditioner before the engine even starts

The National Research Council study: "Making sense of ballistic missile defense"

Science.gov (United States)

Wilkening, Dean A.

2014-05-01

This chapter explains and summarizes the main findings of a recent National Research Council study entitled Making Sense of Ballistic Missile Defense: An Assessment of Concepts and Systems for U.S. Boost-Phase Missile Defense in Comparison to Other Alternatives.

Replica scaling studies of hard missile impacts on reinforced concrete

International Nuclear Information System (INIS)

Barr, P.; Carter, P.G.; Howe, W.D.; Neilson, A.J.

1982-01-01

Missile and target combinations at three different liners scales have been used in an experimental assessment of the applicability of replica scaling to the dynamic behaviour of reinforced concrete structures impacted by rigid missiles. Experimental results are presented for models with relative linear scales of 1, 0.37 and 0.12. (orig.) [de

An Optimal Augmented Monotonic Tracking Controller for Aircraft Engines with Output Constraints

Directory of Open Access Journals (Sweden)

Jiakun Qin

2017-01-01

Full Text Available This paper proposes a novel min-max control scheme for aircraft engines, with the aim of transferring a set of regulated outputs between two set-points, while ensuring a set of auxiliary outputs remain within prescribed constraints. In view of this, an optimal augmented monotonic tracking controller (OAMTC is proposed, by considering a linear plant with input integration, to enhance the ability of the control system to reject uncertainty in system parameters and ensure no crossing limits. The key idea is to use the eigenvalue and eigenvector placement method and genetic algorithms to shape the output responses. The approach is validated by numerical simulation. The results show that the designed OAMTC controller can achieve a satisfactory dynamic and steady performance and keep the auxiliary outputs within constraints in the transient regime.

Estimation of nuclear power plant aircraft hazards

International Nuclear Information System (INIS)

Gottlieb, P.

1978-01-01

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

Self-pressurizing Stirling engine

Science.gov (United States)

Bennett, Charles L.

2010-10-12

A solar thermal powered aircraft powered by heat energy from the sun. A heat engine, such as a Stirling engine, is carried by the aircraft body for producing power for a propulsion mechanism, such as a propeller. The heat engine has a thermal battery in thermal contact with it so that heat is supplied from the thermal battery. A solar concentrator, such as reflective parabolic trough, is movably connected to an optically transparent section of the aircraft body for receiving and concentrating solar energy from within the aircraft. Concentrated solar energy is collected by a heat collection and transport conduit, and heat transported to the thermal battery. A solar tracker includes a heliostat for determining optimal alignment with the sun, and a drive motor actuating the solar concentrator into optimal alignment with the sun based on a determination by the heliostat.

Measuring compliance during aircraft (Component) redeliveries at KLM engineering & maintenance

NARCIS (Netherlands)

Burhani, Shahir; Verhagen, W.J.C.; Curran, Ricky

2016-01-01

Aircraft and aircraft components are redelivered to the next operator or owner during the phase-out process. During this process the operator is required by law and contract requirements to show compliance with maintenance procedures. At KLM E&M the phase-out documentation process is under

Acceleration effects on missile aerodynamics

CSIR Research Space (South Africa)

Gledhill, Irvy MA

2010-09-01

Full Text Available Practical requirements are now arising in which significant acceleration takes place during flight; 5th generation missiles, such as A-Darter, execute turns at 100 g, where g is the acceleration due to gravity, and thrust from propulsion systems may...

Multiradar tracking for theater missile defense

Science.gov (United States)

Sviestins, Egils

1995-09-01

A prototype system for tracking tactical ballistic missiles using multiple radars has been developed. The tracking is based on measurement level fusion (`true' multi-radar) tracking. Strobes from passive sensors can also be used. We describe various features of the system with some emphasis on the filtering technique. This is based on the Interacting Multiple Model framework where the states are Free Flight, Drag, Boost, and Auxiliary. Measurement error modeling includes the signal to noise ratio dependence; outliers and miscorrelations are handled in the same way. The launch point is calculated within one minute from the detection of the missile. The impact point, and its uncertainty region, is calculated continually by extrapolating the track state vector using the equations of planetary motion.

The Anti-Ballistic Missile Treaty

International Nuclear Information System (INIS)

Platt, A.

1991-01-01

This paper reports that in late May 1972 former President Richard M. Nixon went to Moscow and signed, among other documents, a Treaty to Limit Anti-Ballistic Missile (ABM) Systems. Under this agreement, both the United States and the Soviet Union made a commitment not to build nationwide ABM defenses against the other's intercontinental and submarine-launched ballistic missiles. They agreed to limit ABM deployments to a maximum of two sites, with no more than 100 launchers per site. Thirteen of the treaty's sixteen articles are intended to prevent any deviation from this. In addition, a joint Standing Consultative Commission to monitor compliance was created. National technical means --- sophisticated monitoring devices on land, sea, and in space --- were to be the primary instruments used to monitor compliance with the treaty. The ABM Treaty was signed in conjunction with an Interim Agreement to Limit Strategic Offensive Arms

Aurora Flight Sciences' Perseus B Remotely Piloted Aircraft in Flight

Science.gov (United States)

1998-01-01

A long, slender wing and a pusher propeller at the rear characterize the Perseus B remotely piloted research aircraft, seen here during a test flight in June 1998. Perseus B is a remotely piloted aircraft developed as a design-performance testbed under NASA's Environmental Research Aircraft and Sensor Technology (ERAST) project. Perseus is one of several flight vehicles involved in the ERAST project. A piston engine, propeller-powered aircraft, Perseus was designed and built by Aurora Flight Sciences Corporation, Manassas, Virginia. The objectives of Perseus B's ERAST flight tests have been to reach and maintain horizontal flight above altitudes of 60,000 feet and demonstrate the capability to fly missions lasting from 8 to 24 hours, depending on payload and altitude requirements. The Perseus B aircraft established an unofficial altitude record for a single-engine, propeller-driven, remotely piloted aircraft on June 27, 1998. It reached an altitude of 60,280 feet. In 1999, several modifications were made to the Perseus aircraft including engine, avionics, and flight-control-system improvements. These improvements were evaluated in a series of operational readiness and test missions at the Dryden Flight Research Center, Edwards, California. Perseus is a high-wing monoplane with a conventional tail design. Its narrow, straight, high-aspect-ratio wing is mounted atop the fuselage. The aircraft is pusher-designed with the propeller mounted in the rear. This design allows for interchangeable scientific-instrument payloads to be placed in the forward fuselage. The design also allows for unobstructed airflow to the sensors and other devices mounted in the payload compartment. The Perseus B that underwent test and development in 1999 was the third generation of the Perseus design, which began with the Perseus Proof-Of-Concept aircraft. Perseus was initially developed as part of NASA's Small High-Altitude Science Aircraft (SHASA) program, which later evolved into the ERAST

An Efficient Missile Loadout Planning Tool for Operational Planners

Science.gov (United States)

2017-06-01

dictionaries to access values for penalties and feasibility checks. VBA user-defined types are created to identify the base set of missions and base...Missile Defense TLAM Tomahawk Land Attack Missiles TSC Tomahawk Strike Coordinator USN United States Navy VBA Visual Basic for Applications VLP... accessible and usable form, we can start basing our loadouts on actual operational plans (OPLAN) and concept plans (CONPLAN). This will give fleet

The Aircraft Morphing Program

Science.gov (United States)

Wlezien, R. W.; Horner, G. C.; McGowan, A. R.; Padula, S. L.; Scott, M. A.; Silcox, R. J.; Simpson, J. O.

1998-01-01

In the last decade smart technologies have become enablers that cut across traditional boundaries in materials science and engineering. Here we define smart to mean embedded actuation, sensing, and control logic in a tightly coupled feedback loop. While multiple successes have been achieved in the laboratory, we have yet to see the general applicability of smart devices to real aircraft systems. The NASA Aircraft Morphing program is an attempt to couple research across a wide range of disciplines to integrate smart technologies into high payoff aircraft applications. The program bridges research in seven individual disciplines and combines the effort into activities in three primary program thrusts. System studies are used to assess the highest- payoff program objectives, and specific research activities are defined to address the technologies required for development of smart aircraft systems. In this paper we address the overall program goals and programmatic structure, and discuss the challenges associated with bringing the technologies to fruition.