WorldWideScience

Sample records for metallic fuselage panels

  1. Manufacturing scale-up of composite fuselage crown panels

    Science.gov (United States)

    Willden, Kurtis; Gessel, M.; Grant, Carroll G.; Brown, T.

    1993-01-01

    The goal of the Boeing effort under the NASA ACT program is to reduce manufacturing costs of composite fuselage structure. Materials, fabrication of complex subcomponents and assembly issues are expected to drive the costs of composite fuselage structure. Several manufacturing concepts for the crown section of the fuselage were evaluated through the efforts of a Design Build Team (DBT). A skin-stringer-frame intricate bond design that required no fasteners for the panel assembly was selected for further manufacturing demonstrations. The manufacturing processes selected for the intricate bond design include Advanced Tow Placement (ATP) for multiple skin fabrication, resin transfer molding (RTM) of fuselage frames, innovative cure tooling, and utilization of low-cost material forms. Optimization of these processes for final design/manufacturing configuration was evaluated through the fabrication of several intricate bond panels. Panels up to 7 ft. by 10 ft. in size were fabricated to simulate half scale production parts. The qualitative and quantitative results of these manufacturing demonstrations were used to assess manufacturing risks and technology readiness for production.

  2. Acoustically Tailored Composite Rotorcraft Fuselage Panels

    Science.gov (United States)

    2015-07-02

    tapering the plies to the upper and lower skins as shown in Figure 13. Figure 10. Finite element model of baseline panel. 13 Upper Skin Core Edge...through the edgeband. The peak fastener applied ultimate load in the roof panel was 4827 N (1086 Ibf), also for the jump take-off load condition. The

  3. Acoustically Tailored Composite Rotorcraft Fuselage Panels

    Science.gov (United States)

    Hambric, Stephen; Shepherd, Micah; Koudela, Kevin; Wess, Denis; Snider, Royce; May, Carl; Kendrick, Phil; Lee, Edward; Cai, Liang-Wu

    2015-01-01

    A rotorcraft roof sandwich panel has been redesigned to optimize sound power transmission loss (TL) and minimize structure-borne sound for frequencies between 1 and 4 kHz where gear meshing noise from the transmission has the most impact on speech intelligibility. The roof section, framed by a grid of ribs, was originally constructed of a single honeycomb core/composite face sheet panel. The original panel has coincidence frequencies near 700 Hz, leading to poor TL across the frequency range of 1 to 4 kHz. To quiet the panel, the cross section was split into two thinner sandwich subpanels separated by an air gap. The air gap was sized to target the fundamental mass-spring-mass resonance of the double panel system to less than 500 Hz. The panels were designed to withstand structural loading from normal rotorcraft operation, as well as 'man-on-the-roof' static loads experienced during maintenance operations. Thin layers of VHB 9469 viscoelastomer from 3M were also included in the face sheet ply layups, increasing panel damping loss factors from about 0.01 to 0.05. Measurements in the NASA SALT facility show the optimized panel provides 6-11 dB of acoustic transmission loss improvement, and 6-15 dB of structure-borne sound reduction at critical rotorcraft transmission tonal frequencies. Analytic panel TL theory simulates the measured performance quite well. Detailed finite element/boundary element modeling of the baseline panel simulates TL slightly more accurately, and also simulates structure-borne sound well.

  4. Evaluation of Pressurization Fatigue Life of 1441 Al-li Fuselage Panel

    Science.gov (United States)

    Bird, R. Keith; Dicus, Dennis I.; Fridlyander, Joseph; Davydov, Valentin

    1999-01-01

    A study was conducted to evaluate the pressurization fatigue life of fuselage panels with skins fabricated from 1441 Al-Li, an attractive new Russian alloy. The study indicated that 1441 Al-Li has several advantages over conventional aluminum fuselage skin alloy with respect to fatigue behavior. Smooth 1441 Al-Li sheet specimens exhibited a fatigue endurance limit similar to that for 1163 Al (Russian version of 2024 Al) sheet. Notched 1441 Al-Li sheet specimens exhibited greater fatigue strength and longer fatigue life than 1163 Al. In addition, Tu-204 fuselage panels fabricated by Tupolev Design Bureau using Al-Li skin and ring frames with riveted 7000-series aluminum stiffeners had longer pressurization fatigue lives than did panels constructed from conventional aluminum alloys. Taking into account the lower density of this alloy, the results suggest that 1441 Al-Li has the potential to improve fuselage performance while decreasing structural weight.

  5. Response of Composite Fuselage Sandwich Side Panels Subjected to Internal Pressure and Axial Tension

    Science.gov (United States)

    Rouse, Marshall; Ambur, Damodar R.; Dopker, Bernard; Shah, Bharat

    1998-01-01

    The results from an experimental and analytical study of two composite sandwich fuselage side panels for a transport aircraft are presented. Each panel has two window cutouts and three frames and utilizes a distinctly different structural concept. These panels have been evaluated with internal pressure loads that generate biaxial tension loading conditions. Design limit load and design ultimate load tests have been performed on both panels. One of the sandwich panels was tested with the middle frame removed to demonstrate the suitability of this two-frame design for supporting the prescribed biaxial loading conditions with twice the initial frame spacing of 20 inches. A damage tolerance study was conducted on the two-frame panel by cutting a notch in the panel that originates at the edge of a cutout and extends in the panel hoop direction through the window-belt area. This panel with a notch was tested in a combined-load condition to demonstrate the structural damage tolerance at the design limit load condition. Both the sandwich panel designs successfully satisfied all desired load requirements in the experimental part of the study, and experimental results from the two-frame panel with and without damage are fully explained by the analytical results. The results of this study suggest that there is potential for using sandwich structural concepts with greater than the usual 20-in. wide frame spacing to further reduce aircraft fuselage structural weight.

  6. Evaluation of a Composite Sandwich Fuselage Side Panel with Damage and Subjected to Internal Pressure

    Science.gov (United States)

    Rouse, Marshall; Ambur, Damodar R.; Bodine, Jerry; Dopker, Bernhard

    1997-01-01

    The results from an experimental and analytical study of a composite sandwich fuselage side panel for a transport aircraft are presented. The panel has two window cutouts and three frames, and has been evaluated with internal pressure loads that generate biaxial tension loading conditions. Design limit load and design ultimate load tests have been performed on the graphite-epoxy sandwich panel with the middle frame removed to demonstrate the suitability of this two-frame design for supporting the prescribed biaxial loading conditions with twice the initial frame spacing of 20 inches. The two-frame panel was damaged by cutting a notch that originates at the edge of a cutout and extends in the panel hoop direction through the window-belt area. This panel with a notch was tested in a combined-load condition to demonstrate the structural damage tolerance at the design limit load condition. The two panel configurations successfully satisfied all design load requirements in the experimental part of the study, and the three-frame and two-frame panel responses are fully explained by the analysis results. The results of this study suggest that there is potential for using sandwich structural concepts with greater than the usual 20-in.-wide frame spacing to further reduce aircraft fuselage structural weight.

  7. Global Cost and Weight Evaluation of Fuselage Side Panel Design Concepts

    Science.gov (United States)

    Polland, D. R.; Finn, S. R.; Griess, K. H.; Hafenrichter, J. L.; Hanson, C. T.; Ilcewicz, L. B.; Metschan, S. L.; Scholz, D. B.; Smith, P. J.

    1997-01-01

    This report documents preliminary design trades conducted under NASA contracts NAS1 18889 (Advanced Technology Composite Aircraft Structures, ATCAS) and NAS1-19349 (Task 3, Pathfinder Shell Design) for a subsonic wide body commercial aircraft fuselage side panel section utilizing composite materials. Included in this effort were (1) development of two complete design concepts, (2) generation of cost and weight estimates, (3) identification of technical issues and potential design enhancements, and (4) selection of a single design to be further developed. The first design concept featured an open-section stringer stiffened skin configuration while the second was based on honeycomb core sandwich construction. The trade study cost and weight results were generated from comprehensive assessment of each structural component comprising the fuselage side panel section from detail fabrication through airplane final assembly. Results were obtained in three phases: (1) for the baseline designs, (2) after global optimization of the designs, and (3) the results anticipated after detailed design optimization. A critical assessment of both designs was performed to determine the risk associated with each concept, that is the relative probability of achieving the cost and weight projections. Seven critical technical issues were identified as the first step towards side panel detailed design optimization.

  8. Fuselage Versus Subcomponent Panel Response Correlation Based on ABAQUS Explicit Progressive Damage Analysis Tools

    Science.gov (United States)

    Gould, Kevin E.; Satyanarayana, Arunkumar; Bogert, Philip B.

    2016-01-01

    Analysis performed in this study substantiates the need for high fidelity vehicle level progressive damage analyses (PDA) structural models for use in the verification and validation of proposed sub-scale structural models and to support required full-scale vehicle level testing. PDA results are presented that capture and correlate the responses of sub-scale 3-stringer and 7-stringer panel models and an idealized 8-ft diameter fuselage model, which provides a vehicle level environment for the 7-stringer sub-scale panel model. Two unique skin-stringer attachment assumptions are considered and correlated in the models analyzed: the TIE constraint interface versus the cohesive element (COH3D8) interface. Evaluating different interfaces allows for assessing a range of predicted damage modes, including delamination and crack propagation responses. Damage models considered in this study are the ABAQUS built-in Hashin procedure and the COmplete STress Reduction (COSTR) damage procedure implemented through a VUMAT user subroutine using the ABAQUS/Explicit code.

  9. Static and fatigue experimental tests on a full scale fuselage panel and FEM analyses

    Directory of Open Access Journals (Sweden)

    Raffaele Sepe

    2016-02-01

    Full Text Available A fatigue test on a full scale panel with complex loading condition and geometry configuration has been carried out using a triaxial test machine. The demonstrator is made up of two skins which are linked by a transversal butt-joint, parallel to the stringer direction. A fatigue load was applied in the direction normal to the longitudinal joint, while a constant load was applied in the longitudinal joint direction. The test panel was instrumented with strain gages and previously quasi-static tests were conducted to ensure a proper load transferring to the panel. In order to support the tests, geometric nonlinear shell finite element analyses were conducted to predict strain and stress distributions. The demonstrator broke up after about 177000 cycles. Subsequently, a finite element analysis (FEA was carried out in order to correlate failure events; due to the biaxial nature of the fatigue loads, Sines criterion was used. The analysis was performed taking into account the different materials by which the panel is composed. The numerical results show a good correlation with experimental data, successfully predicting failure locations on the panel.

  10. Causal feedforward control of a stochastically excited fuselage structure with active sidewall panel.

    Science.gov (United States)

    Misol, Malte; Haase, Thomas; Monner, Hans Peter; Sinapius, Michael

    2014-10-01

    This paper provides experimental results of an aircraft-relevant double panel structure mounted in a sound transmission loss facility. The primary structure of the double panel system is excited either by a stochastic point force or by a diffuse sound field synthesized in the reverberation room of the transmission loss facility. The secondary structure, which is connected to the frames of the primary structure, is augmented by actuators and sensors implementing an active feedforward control system. Special emphasis is placed on the causality of the active feedforward control system and its implications on the disturbance rejection at the error sensors. The coherence of the sensor signals is analyzed for the two different disturbance excitations. Experimental results are presented regarding the causality, coherence, and disturbance rejection of the active feedforward control system. Furthermore, the sound transmission loss of the double panel system is evaluated for different configurations of the active system. A principal result of this work is the evidence that it is possible to strongly influence the transmission of stochastic disturbance sources through double panel configurations by means of an active feedforward control system.

  11. Determination of Paris' law constants and crack length evolution via Extended and Unscented Kalman filter: An application to aircraft fuselage panels

    Science.gov (United States)

    Wang, Yiwei; Binaud, Nicolas; Gogu, Christian; Bes, Christian; Fu, Jian

    2016-12-01

    Prediction of fatigue crack length in aircraft fuselage panels is one of the key issues for aircraft structural safety since it helps prevent catastrophic failures. Accurate estimation of crack length propagation is also meaningful for helping develop aircraft maintenance strategies. Paris' law is often used to capture the dynamics of fatigue crack propagation in metallic material. However, uncertainties are often present in the crack growth model, measured crack size and pressure differential in each flight and need to be accounted for accurate prediction. The aim of this paper is to estimate the two unknown Paris' law constants m and C as well as the crack length evolution by taking into account these uncertainties. Due to the nonlinear nature of the Paris' law, we propose here an on-line estimation algorithm based on two widespread nonlinear filtering techniques, Extended Kalman filter (EKF) and Unscented Kalman filter (UKF). The numerical experiments indicate that both EKF and UKF estimated the crack length well and accurately identified the unknown parameters. Although UKF is theoretical superior to EKF, in this Paris' law application EKF is comparable in accuracy to UKF and requires less computational expense.

  12. Assessment of Damage Containment Features of a Full-Scale PRSEUS Fuselage Panel Through Test and Teardown

    Science.gov (United States)

    Bergan, Andrew C.; Bakuckas, John G., Jr.; Lovejoy, Andrew E.; Jegley, Dawn C.; Awerbuch, Jonathan; Tan, Tein-Min

    2012-01-01

    An area that shows promise in enhancing structural integrity of aircraft and aerospace structures is the integrally stitched composite technology. The most recent generation of this technology is the Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) concept developed by Boeing Research and Technology and the National Aeronautics and Space Administration. A joint test program on the assessment of damage containment capabilities of the PRSEUS concept for curved fuselage structures was conducted recently at the Federal Aviation Administration William J. Hughes Technical Center. The panel was subjected to axial tension, internal pressure, and combined axial tension and internal pressure load conditions up to fracture, with a through-the-thickness, two-bay notch severing the central stiffener. For the purpose of future progressive failure analysis development and verification, extensive post failure nondestructive and teardown inspections were conducted. Detailed inspections were performed directly ahead of the notch tip where stable damage progression was observed. These examinations showed: 1) extensive delaminations developed ahead of the notch tip, 2) the extent and location of damage, 3) the typical damage mechanisms observed in composites, and 4) the role of stitching and warp-knitting in the failure mechanisms. The objective of this paper is to provide a summary of results from these posttest inspections.

  13. Initiation and growth of multiple-site damage in the riveted lap joint of a curved stiffened fuselage panel: An experimental and analytical study

    Science.gov (United States)

    Ahmed, Abubaker Ali

    As part of the structural integrity research of the National Aging Aircraft Research Program, a comprehensive study on multiple-site damage (MSD) initiation and growth in a pristine lap-joint fuselage panel has been conducted. The curved stiffened fuselage panel was tested at the Full-Scale Aircraft Structural Test Evaluation and Research (FASTER) facility located at the Federal Aviation Administration William J. Hughes Technical Center. A strain survey test was conducted to verify proper load application. The panel was then subjected to a fatigue test with constant-amplitude cyclic loading. The applied loading spectrum included underload marker cycles so that crack growth history could be reconstructed from post-test fractographic examinations. Crack formation and growth were monitored via nondestructive and high-magnification visual inspections. Strain gage measurements recorded during the strain survey tests indicated that the inner surface of the skin along the upper rivet row of the lap joint experienced high tensile stresses due to local bending. During the fatigue loading, cracks were detected by eddy-current inspections at multiple rivet holes along the upper rivet row. Through-thickness cracks were detected visually after about 80% of the fatigue life. Once MSD cracks from two adjacent rivet holes linked up, there was a quick deterioration in the structural integrity of the lap joint. The linkup resulted in a 2.87" (72.9-mm) lead fatigue crack that rapidly propagated across 12 rivet holes and crossed over into the next skin bay, at which stage the fatigue test was terminated. A post-fatigue residual strength test was then conducted by loading the panel quasi-statically up to final failure. The panel failed catastrophically when the crack extended instantaneously across three additional bays. Post-test fractographic examinations of the fracture surfaces in the lap joint of the fuselage panel were conducted to characterize subsurface crack initiation and

  14. Double-sided laser beam welded T-joints for aluminum-lithium alloy aircraft fuselage panels: Effects of filler elements on microstructure and mechanical properties

    Science.gov (United States)

    Han, Bing; Tao, Wang; Chen, Yanbin; Li, Hao

    2017-08-01

    In the current work, T-joints consisting of 2.0 mm thick 2060-T8/2099-T83 aluminum-lithium alloys for aircraft fuselage panels have been fabricated by double-sided fiber laser beam welding with different filler wires. A new type wire CW3 (Al-6.2Cu-5.4Si) was studied and compared with conventional wire AA4047 (Al-12Si) mainly on microstructure and mechanical properties. It was found that the main combined function of Al-6.2%Cu-5.4%Si in CW3 resulted in considerable improvements especially on intergranular strength, hot cracking susceptibility and hoop tensile properties. Typical non-dendritic equiaxed zone (EQZ) was observed along welds' fusion boundary. Hot cracks and fractures during the load were always located within the EQZ, however, this typical zone could be restrained by CW3, effectively. Furthermore, changing of the main intergranular precipitated phase within the EQZ from T phase by AA4047 to T2 phase by CW3 also resulted in developments on microscopic intergranular reinforcement and macroscopic hoop tensile properties. In addition, bridging caused by richer substructure dendrites within CW3 weld's columnar zone resulted in much lower hot cracking susceptibility of the whole weld than AA4047.

  15. Behaviour of Metal Foam Sandwich Panels

    DEFF Research Database (Denmark)

    2011-01-01

    Sandwich panels as used in structures comprise of a foam core enclosed by thin high strength steel faces. This paper discusses currently design formulae of local buckling behaviour of such panels using the finite element method. Multiple wave finite element models were adopted to investigate...

  16. Behaviour of Metal Foam Sandwich Panels

    DEFF Research Database (Denmark)

    2011-01-01

    Sandwich panels as used in structures comprise of a foam core enclosed by thin high strength steel faces. This paper discusses currently design formulae of local buckling behaviour of such panels using the finite element method. Multiple wave finite element models were adopted to investigate...... and examine the adequacy of currently used approach for the design of sandwich panels. The paper presents brief details of the finite element model used including geometry, load pattern and boundary conditions. The selected model gives good agreement with experimental results from Pokharel and Mahendran (2003......). The study shows that currently available design formulae are conservative for stocky sandwich plate elements while being over-conservative for high slenderness. A unified design formula of local buckling behaviour applicable to the full range of slenderness is developed....

  17. 大型客机机舱内饰板隔声性能计算与试验%Calculation and Testing of Sound Transmission Loss for Interior Panels of Large Aircraft Fuselages

    Institute of Scientific and Technical Information of China (English)

    韩峰

    2014-01-01

    结合单层板与夹层板隔声理论,推导了应用于计算典型飞机机舱内饰板隔声量的分析方法。根据所推导的计算公式,将真实环境条件与内饰板材料参数代入其中,获得地面与飞行状态下的隔声量计算结果。与实测数据对比之后,发现在特定频率区域内饰板计算量值与趋势都与试验吻合较好,但在共振频率、吻合频率和压缩频率上,计算值与试验测量值有较大起伏。对比飞行与地面两种条件,飞机状态下的隔声量普遍大于地面状态。%Combining the acoustic theories of plain panel and sandwich panel, an analysis method to calculate sound transmission loss of interior panel of typical aircraft fuselages is provided. According to the sound transmission loss equations, the real parameters of interior panel are defined and put into calculation process. Then, the results of sound insulation in flight and ground conditions are obtained. It is found that the value and tendency of the sound insulation agree well with the measurement data from the testing in a special frequency range. However, there are somewhat large differences between them in resonance frequencies, coincidence frequencies and dilatation frequencies of the sandwich panel. The sound insulation effect in flight condition is better than that in ground condition.

  18. Combined-load buckling behavior of metal-matrix composite sandwich panels under different thermal environments

    Science.gov (United States)

    Ko, William L.; Jackson, Raymond H.

    1991-01-01

    Combined compressive and shear buckling analysis was conducted on flat rectangular sandwich panels with the consideration of transverse shear effects of the core. The sandwich panel is fabricated with titanium honeycomb core and laminated metal matrix composite face sheets. The results show that the square panel has the highest combined load buckling strength, and that the buckling strength decreases sharply with the increases of both temperature and panel aspect ratio. The effect of layup (fiber orientation) on the buckling strength of the panels was studied in detail. The metal matrix composite sandwich panel was much more efficient than the sandwich panel with nonreinforced face sheets and had the same specific weight.

  19. Al-Li Alloy 1441 for Fuselage Applications

    Science.gov (United States)

    Bird, R. K.; Dicus, D. L.; Fridlyander, J. N.; Sandler, V. S.

    2000-01-01

    A cooperative investigation was conducted to evaluate Al-Cu-Mg-Li alloy 1441 for long service life fuselage applications. Alloy 1441 is currently being used for fuselage applications on the Russian Be-103 amphibious aircraft, and is expected to be used for fuselage skin on a new Tupolev business class aircraft. Alloy 1441 is cold-rollable and has several attributes that make it attractive for fuselage skin applications. These attributes include lower density and higher specific modulus with similar strength as compared to conventional Al-Cu-Mg alloys. Cold-rolled 1441 Al-Li sheet specimens were tested at NASA Langley Research Center (LaRC) and at the All-Russia Institute of Aviation Materials (VIAM) in Russia to evaluate tensile properties, fracture toughness, impact resistance, fatigue life and fatigue crack growth rate. In addition, fuselage panels were fabricated by Tupolev Design Bureau (TDB) using 1441 skins and Al-Zn-Mg-Cu alloy stiffeners. The panels were subjected to cyclic pressurization fatigue tests at TDB and at LaRC to simulate fuselage pressurization/depressurization during aircraft service. This paper discusses the results from this investigation.

  20. Numerical simulation of heat transfer and fluid flow during double-sided laser beam welding of T-joints for aluminum aircraft fuselage panels

    Science.gov (United States)

    Yang, Zhibin; Tao, Wang; Li, Liqun; Chen, Yanbin; Shi, Chunyuan

    2017-06-01

    In comparison with conventional laser beam welding, double-sided laser beam welding has two laser heat sources simultaneously and symmetrically loaded from both sides makes it to be a more complicated coupled heat transport and fluid flow process. In this work, in order to understand the heat transfer and fluid flow, a three-dimensional model was developed and validated with the experimental results. The temperature field, fluid flow field, and keyhole characteristic were calculated using the developed model by FLUENT software. Calculated results indicated that the temperature and fluid flow fields were bilateral symmetry along the stringer center, and the molten pool maximum length was located near the keyhole intersection position. The skin side had higher temperature and faster cooling speed. Several characteristic flow patterns in the weld pool cross section, including the vortexes flows near the keyhole opening position, the convection flows above the keyhole intersection location, the regularity downward flows at the molten pool bottom. And in the lengthwise section, a distinct vortex flow below the keyhole, and the liquid metal behind the keyhole first flowed to near the molten pool maximum length location and then to the molten pool surface. Perpendicular to and along welding direction the keyhole liquid metal flowed to the weld molten pool surface and around the keyhole, respectively. The special temperature fields and fluid flow patterns were closely related to the effects of the double sides' laser energy coupling and enhancement. The calculated weld pool geometry basically in good agreement with the experimental results indicated that the developed model was validity and reasonable.

  1. Compressive and shear buckling analysis of metal matrix composite sandwich panels under different thermal environments

    Science.gov (United States)

    Ko, William L.; Jackson, Raymond H.

    1993-01-01

    Combined inplane compressive and shear buckling analysis was conducted on flat rectangular sandwich panels using the Raleigh-Ritz minimum energy method with a consideration of transverse shear effect of the sandwich core. The sandwich panels were fabricated with titanium honeycomb core and laminated metal matrix composite face sheets. The results show that slightly slender (along unidirectional compressive loading axis) rectangular sandwich panels have the most desirable stiffness-to-weight ratios for aerospace structural applications; the degradation of buckling strength of sandwich panels with rising temperature is faster in shear than in compression; and the fiber orientation of the face sheets for optimum combined-load buckling strength of sandwich panels is a strong function of both loading condition and panel aspect ratio. Under the same specific weight and panel aspect ratio, a sandwich panel with metal matrix composite face sheets has much higher buckling strength than one having monolithic face sheets.

  2. Structural analysis of Aircraft fuselage splice joint

    Science.gov (United States)

    Udaya Prakash, R.; Kumar, G. Raj; Vijayanandh, R.; Senthil Kumar, M.; Ramganesh, T.

    2016-09-01

    In Aviation sector, composite materials and its application to each component are one of the prime factors of consideration due to the high strength to weight ratio, design flexibility and non-corrosive so that the composite materials are widely used in the low weight constructions and also it can be treated as a suitable alternative to metals. The objective of this paper is to estimate and compare the suitability of a composite skin joint in an aircraft fuselage with different joints by simulating the displacement, normal stress, vonmises stress and shear stress with the help of numerical solution methods. The reference Z-stringer component of this paper is modeled by CATIA and numerical simulation is carried out by ANSYS has been used for splice joint presents in the aircraft fuselage with three combinations of joints such as riveted joint, bonded joint and hybrid joint. Nowadays the stringers are using to avoid buckling of fuselage skin, it has joined together by rivets and they are connected end to end by splice joint. Design and static analysis of three-dimensional models of joints such as bonded, riveted and hybrid are carried out and results are compared.

  3. The Effect of Metallic TPS Panel Bowing on the Surface Heating of the X-33 Vehicle

    Science.gov (United States)

    Palmer, Grant; Kontinos, Dean; Langhoff, Stephen R. (Technical Monitor)

    1997-01-01

    The thermal protection system of the windward surface of the X-33 vehicle consists of metallic honeycomb sandwich panels. Thermal gradients experienced during the descent phase of the trajectory result in a different rate of thermal expansion between the inner and outer face sheets of the metallic panels. This causes the panels to bow outward when the temperature of the outer face sheet is larger than that of the inner face sheet and inward when the temperature of the outer face sheet is less than that of he inner face sheet. This results in a quilted-type body surface. Using computational fluid dynamic analysis, this study will determine the effect the metallic TPS panel bowing has on the surface heating.

  4. POSTOP: Postbuckled open-stiffener optimum panels, user's manual

    Science.gov (United States)

    Biggers, S. B.; Dickson, J. N.

    1984-01-01

    The computer program POSTOP developed to serve as an aid in the analysis and sizing of stiffened composite panels that may be loaded in the postbuckling regime, is intended for the preliminary design of metal or composite panels with open-section stiffeners, subjected to multiple combined biaxial compression (or tension), shear and normal pressure load cases. Longitudinal compression, however, is assumed to be the dominant loading. Temperature, initial bow eccentricity and load eccentricity effects are included. The panel geometry is assumed to be repetitive over several bays in the longitudinal (stiffener) direction as well as in the transverse direction. Analytical routines are included to compute panel stiffnesses, strains, local and panel buckling loads, and skin/stiffener interface stresses. The resulting program is applicable to stiffened panels as commonly used in fuselage, wing, or empennage structures. The capabilities and limitations of the code are described. Instructions required to use the program and several example problems are included.

  5. Radiant heating tests of several liquid metal heat-pipe sandwich panels

    Science.gov (United States)

    Camarda, C. J.; Basiulis, A.

    1983-01-01

    Integral heat pipe sandwich panels, which synergistically combine the thermal efficiency of heat pipes and the structural efficiency of honeycomb sandwich construction, were conceived as a means of alleviating thermal stress problems in the Langley Scramjet Engine. Test panels which utilized two different wickable honeycomb cores, facesheets with screen mesh sintered to the internal surfaces, and a liquid metal working fluid (either sodium or potassium) were tested by radiant heating at various heat load levels. The heat pipe panels reduced maximum temperature differences by 31 percent with sodium working fluid and 45 percent with potassium working fluid. Results indicate that a heat pipe sandwich panel is a potential, simple solution to the engine thermal stress problem. Other interesting applications of the concept include: cold plates for electronic component and circuit card cooling, radiators for large space platforms, low distortion large area structures (e.g., space antennas) and laser mirrors.

  6. Analysis and Behaviour of Sandwich Panels with Profiled Metal Facings under Transverse Load

    Directory of Open Access Journals (Sweden)

    M. Budescu

    2004-01-01

    Full Text Available Sandwich panels with thin steel facings and polyurethane core combine the load-carrying capacity of metal facings and protection functions with core properties. The core separates the two facings and keeps them in a stable condition, transmits shear between external layers, provides most of the shear rigidity and occasionally makes of useful contribution to the bending stiffness of the sandwich construction as a whole [1]. An experimental program on sandwich panels has been organized to prove that the mechanical properties of core and interface satisfy the load-carrying requirements for structural sandwich panels. The analysis of sandwich panels with deep profiles facings for cladding elements, respectively the roof constructions, has been carried out according to the European design norms [1], [5].

  7. Sound transmission across lightweight all-metallic sandwich panels with corrugated cores

    Institute of Scientific and Technical Information of China (English)

    XIN Fengxian; LU Tianjian; CHEN Changqing

    2009-01-01

    The transmission of sound through all-metallic sandwich panels with corrugated cores is investigated using the space-harmonic method. The sandwich panel is modeled as two parallel panels connected by uniformly distributed translational springs and rotational springs, with the mass of the core sheets taken as lumped mass. Based on the periodicity of the panel structure, a unit cell model is developed to provide the effective translational and rotational stiffness of the core. To check the validity of the model, it is used first to study the sound insulation properties of double-panel structures with air cavity, and the analytical predictions agree well with existing experimental data. The model is then employed to quantify the influence of sound incidence angle and the inclination angle between facesheet and core sheet on sound transmission loss (STL) across sandwich panels with corrugated cores. The results show that the inclination angle has a significant effect on STL and it is possible to avoid STL dips by altering the inclination angle. Moreover, it is found that sandwich panels with corrugated cores are more suitable for the insulation of sound waves having small incidence angles.

  8. Thermomechanical response of metal foam sandwich panels for structural thermal protection systems in hypersonic vehicles

    Science.gov (United States)

    Rakow, Joseph F.

    Sandwich panels with metal foam cores are proposed for load-bearing structural components in actively cooled thermal protection systems for aerospace vehicles. Prototype acreage metal foam sandwich panels (MFSP's) are constructed and analyzed with the central goal of characterizing the thermomechanical response of the system. MFSP's are subjected to uniform temperature fields and equibiaxial loading in a novel experimental load frame. The load frame exploits the mismatch of coefficients of thermal expansion and allows for thermostructural experimentation without the endemic conflict of thermal and mechanical boundary conditions. Back-to-back strain gages and distributed thermocouples capture the in-plane response of the panels, including buckling and elastic-plastic post-buckling. The out-of-plane response is captured via moire interferometry, which provides a visualization of evolving mode shapes throughout the post-buckling regime. The experimental results agree with an analytical prediction for critical temperatures in sandwich panels based on a Rayleigh-Ritz minimization of the energy functional for a Reissner-Mindlin plate. In addition, a three-dimensional finite element model of the non-linear thermomechanical response of the panel-frame experimental system is developed and the results are shown to agree well with the experimentally identified response of MFSP's. Central to analytical and numerical characterization of MFSP's is an understanding of the response of metal foam under shear loading. The shear response of metal foam is captured experimentally, providing density-dependent relationships for material stiffness, strength, and energy absorption. Speckle photography is employed to identify microstructural size effects in the distribution of strain throughout metal foam under shear loading. In addition, a micromechanical model is established for the density-dependent shear modulus of metal foam, which allows for the coupling of cell-level imperfections

  9. Dynamic Response and Optimal Design of Curved Metallic Sandwich Panels under Blast Loading

    Directory of Open Access Journals (Sweden)

    Chang Qi

    2014-01-01

    Full Text Available It is important to understand the effect of curvature on the blast response of curved structures so as to seek the optimal configurations of such structures with improved blast resistance. In this study, the dynamic response and protective performance of a type of curved metallic sandwich panel subjected to air blast loading were examined using LS-DYNA. The numerical methods were validated using experimental data in the literature. The curved panel consisted of an aluminum alloy outer face and a rolled homogeneous armour (RHA steel inner face in addition to a closed-cell aluminum foam core. The results showed that the configuration of a “soft” outer face and a “hard” inner face worked well for the curved sandwich panel against air blast loading in terms of maximum deflection (MaxD and energy absorption. The panel curvature was found to have a monotonic effect on the specific energy absorption (SEA and a nonmonotonic effect on the MaxD of the panel. Based on artificial neural network (ANN metamodels, multiobjective optimization designs of the panel were carried out. The optimization results revealed the trade-off relationships between the blast-resistant and the lightweight objectives and showed the great use of Pareto front in such design circumstances.

  10. Dynamic response and optimal design of curved metallic sandwich panels under blast loading.

    Science.gov (United States)

    Qi, Chang; Yang, Shu; Yang, Li-Jun; Han, Shou-Hong; Lu, Zhen-Hua

    2014-01-01

    It is important to understand the effect of curvature on the blast response of curved structures so as to seek the optimal configurations of such structures with improved blast resistance. In this study, the dynamic response and protective performance of a type of curved metallic sandwich panel subjected to air blast loading were examined using LS-DYNA. The numerical methods were validated using experimental data in the literature. The curved panel consisted of an aluminum alloy outer face and a rolled homogeneous armour (RHA) steel inner face in addition to a closed-cell aluminum foam core. The results showed that the configuration of a "soft" outer face and a "hard" inner face worked well for the curved sandwich panel against air blast loading in terms of maximum deflection (MaxD) and energy absorption. The panel curvature was found to have a monotonic effect on the specific energy absorption (SEA) and a nonmonotonic effect on the MaxD of the panel. Based on artificial neural network (ANN) metamodels, multiobjective optimization designs of the panel were carried out. The optimization results revealed the trade-off relationships between the blast-resistant and the lightweight objectives and showed the great use of Pareto front in such design circumstances.

  11. Prediction of Behavior of Ceramic/Metal Composite Panels Under Two Consecutive Ballistic Impacts

    Science.gov (United States)

    Prakash, A.; Rajasankar, J.; Iyer, N. R.; Anandavalli, N.; Biswas, S. K.; Mukhopadhyay, A. K.

    2014-05-01

    This article presents a numerical investigation to predict the behavior of ceramic (Al2O3 99.5)/metal (Al5083 H116) composite panels under two consecutive high-velocity impacts of 7.62 mm sharp-nosed small projectiles. A numerical model is developed using the advanced nonlinear software AUTODYN. The aim of the study is to predict the impact behavior of ceramic/metal composite panels. The study mainly focuses on the effect of arrangement of front ceramic tiles having collinear and non-collinear joints on the impact damage pattern. The novelty of the study presented in this article is the prediction of high-velocity-impact response under two consecutive and closely spaced hits on composite panels carried out in a more realistic manner. Numerical responses, such as depth of penetration, and deformation in back plate and crack patterns, are found to match well with the experimental results. It is believed that the outcome of this study is helpful in the design of a ceramic tile joint arrangement to minimize damage in the target panel.

  12. Virtual Design Method for Controlled Failure in Foldcore Sandwich Panels

    Science.gov (United States)

    Sturm, Ralf; Fischer, S.

    2015-12-01

    For certification, novel fuselage concepts have to prove equivalent crashworthiness standards compared to the existing metal reference design. Due to the brittle failure behaviour of CFRP this requirement can only be fulfilled by a controlled progressive crash kinematics. Experiments showed that the failure of a twin-walled fuselage panel can be controlled by a local modification of the core through-thickness compression strength. For folded cores the required change in core properties can be integrated by a modification of the fold pattern. However, the complexity of folded cores requires a virtual design methodology for tailoring the fold pattern according to all static and crash relevant requirements. In this context a foldcore micromodel simulation method is presented to identify the structural response of a twin-walled fuselage panels with folded core under crash relevant loading condition. The simulations showed that a high degree of correlation is required before simulation can replace expensive testing. In the presented studies, the necessary correlation quality could only be obtained by including imperfections of the core material in the micromodel simulation approach.

  13. Effect of Acid Dissolution Conditions on Recovery of Valuable Metals from Used Plasma Display Panel Scrap

    Directory of Open Access Journals (Sweden)

    Kim Chan-Mi

    2017-06-01

    Full Text Available The objective of this particular study was to recover valuable metals from waste plasma display panels using high energy ball milling with subsequent acid dissolution. Dissolution of milled (PDP powder was studied in HCl, HNO3, and H2SO4 acidic solutions. The effects of dissolution acid, temperature, time, and PDP scrap powder to acid ratio on the leaching process were investigated and the most favorable conditions were found: (1 valuable metals (In, Ag, Mg were recovered from PDP powder in a mixture of concentrated hydrochloric acid (HCl:H2O = 50:50; (2 the optimal dissolution temperature and time for the valuable metals were found to be 60°C and 30 min, respectively; (3 the ideal PDP scrap powder to acid solution ratio was found to be 1:10. The proposed method was applied to the recovery of magnesium, silver, and indium with satisfactory results.

  14. The Theoretical Research for the Rotor/Fuselage Unsteady Aerodynamic Interaction Problem

    Directory of Open Access Journals (Sweden)

    Liu Dawei

    2016-07-01

    Full Text Available Based on coupled unsteady panel/free-wake method, a universal analysis model was established, which provides a good prediction for the rotor/fuselage unsteady aerodynamic interaction. Considering the deficiencies of the traditional time-marching rotor free-wake algorithms, notably on stability and efficiency, the CB3D algorithm with 3rd-order accuracy is proposed. For solving the problem that part of the wake vortices may penetrate the fuselage, a “material line” rectification method with 3rd-order accuracy is proposed. An analysis for the model accuracy was then conducted to validate the accuracy of the new model, and a comparison against the available experimental data is performed. The simulated results show a good agreement with these experimental data. With the new model, several simulations are conducted for the typical rotor/fuselage aerodynamic interaction, and the results are analyzed.

  15. Ultrafast Laser Engraving Method to Fabricate Gravure Plate for Printed Metal-Mesh Touch Panel

    Directory of Open Access Journals (Sweden)

    Weiyuan Chen

    2015-10-01

    Full Text Available In order to engrave gravure plate with fine lines structures, conventional art used lithography with dry/wet etching. Lithography with dry/wet etching method allows to engrave lines with smooth concave shape, but its disadvantages include difficulty in controlling aspect ratio, high and uniform in large size process, substrate material limitation due to etching solution availability, and process complexity. We developed ultra-fast laser technology to directly engrave a stainless plate, a gravure plate, to be used for fabricating 23 in. metal-mesh touch panel by gravure offset printing process. The technology employs high energy pulse to ablate materials from a substrate. Because the ultra-fast laser pulse duration is shorter than the energy dissipation time between material lattices, there is no heating issue during the ablation process. Therefore, no volcano-type protrusion on the engraved line edges occurs, leading to good printing quality. After laser engraving, we then reduce surface roughness of the gravure plate using electro-polishing process. Diamond like carbon (DLC coating layer is then added onto the surface to increase scratch resistance. We show that this procedure can fabricate gravure plate for gravure offset printing process with minimum printing linewidth 10.7 μm. A 23 in. metal-mesh pattern was printed using such gravure plate and fully functional touch panel was demonstrated in this work.

  16. Simulation of Flow around Isolated Helicopter Fuselage

    Directory of Open Access Journals (Sweden)

    Garipov A.O.

    2013-04-01

    Full Text Available Low fuselage drag has always been a key target of helicopter manufacturers. Therefore, this paper focuses on CFD predictions of the drag of several components of a typical helicopter fuselage. In the first section of the paper, validation of the obtained CFD predictions is carried out using wind tunnel measurements. The measurements were carried out at the Kazan National Research Technical University n.a. A. Tupolev. The second section of the paper is devoted to the analysis of drag contributions of several components of the ANSAT helicopter prototype fuselage using the RANS approach. For this purpose, several configurations of fuselages are considered with different levels of complexity including exhausts and skids. Depending on the complexity of the considered configuration and CFD mesh both the multi-block structured HMB solver and the unstructured commercial tool Fluent are used. Finally, the effect of an actuator disk on the predicted drag is addressed.

  17. Testing and Analysis of a Composite Non-Cylindrical Aircraft Fuselage Structure . Part II; Severe Damage

    Science.gov (United States)

    Przekop, Adam; Jegley, Dawn C.; Lovejoy, Andrew E.; Rouse, Marshall; Wu, Hsi-Yung T.

    2016-01-01

    The Environmentally Responsible Aviation Project aimed to develop aircraft technologies enabling significant fuel burn and community noise reductions. Small incremental changes to the conventional metallic alloy-based 'tube and wing' configuration were not sufficient to achieve the desired metrics. One airframe concept identified by the project as having the potential to dramatically improve aircraft performance was a composite-based hybrid wing body configuration. Such a concept, however, presented inherent challenges stemming from, among other factors, the necessity to transfer wing loads through the entire center fuselage section which accommodates a pressurized cabin confined by flat or nearly flat panels. This paper discusses a finite element analysis and the testing of a large-scale hybrid wing body center section structure developed and constructed to demonstrate that the Pultruded Rod Stitched Efficient Unitized Structure concept can meet these challenging demands of the next generation airframes. Part II of the paper considers the final test to failure of the test article in the presence of an intentionally inflicted severe discrete source damage under the wing up-bending loading condition. Finite element analysis results are compared with measurements acquired during the test and demonstrate that the hybrid wing body test article was able to redistribute and support the required design loads in a severely damaged condition.

  18. a Reciprocity Technique for the Characterisation of Sound Transmission Into Aircraft Fuselages.

    Science.gov (United States)

    Mason, James Meredith

    1990-01-01

    Available from UMI in association with The British Library. Experimental determination of the sound insulation of propfan aircraft fuselage structures is problematic. The use of full-scale flight tests to investigate and optimise sidewall design is expensive, while the use of simplified excitation tests is questionable, due to the complicated nature of propeller sound fields and their interaction with the fuselage. This thesis describes the development and evaluation of a new experimental reciprocity technique for calibrating a fuselage as a transmitter of pressure acting on the external surface to the interior: it is based upon the use of a transducer which measures the volume velocity of the vibrating fuselage surface. The data generated may be combined with any impinging sound field to obtain a prediction of cabin sound pressure level. In the first instance, the technique is validated for sound transmission through flat panels into a rigid walled box and the results presented demonstrate the validity of the approach. Tests are then conducted on a set of four quarter-scale 'green' fuselage model configurations, constructed to investigate the influence of ring frame bending-stiffness, stringers and floor on airborne sound transmission. Interior noise predictions are obtained for plane wave excitation and a representation of propeller sound field excitation. The important features relating to correct representation of the excitation field and the fuselage structure are isolated, within the scope of the models evaluated. In addition, a statistical perturbation technique is described which demonstrates confidence in the predictions. The technique is recommended for evaluation on a full size airframe.

  19. Nonlinear Finite Element Analysis of a Composite Non-Cylindrical Pressurized Aircraft Fuselage Structure

    Science.gov (United States)

    Przekop, Adam; Wu, Hsi-Yung T.; Shaw, Peter

    2014-01-01

    The Environmentally Responsible Aviation Project aims to develop aircraft technologies enabling significant fuel burn and community noise reductions. Small incremental changes to the conventional metallic alloy-based 'tube and wing' configuration are not sufficient to achieve the desired metrics. One of the airframe concepts that might dramatically improve aircraft performance is a composite-based hybrid wing body configuration. Such a concept, however, presents inherent challenges stemming from, among other factors, the necessity to transfer wing loads through the entire center fuselage section which accommodates a pressurized cabin confined by flat or nearly flat panels. This paper discusses a nonlinear finite element analysis of a large-scale test article being developed to demonstrate that the Pultruded Rod Stitched Efficient Unitized Structure concept can meet these challenging demands of the next generation airframes. There are specific reasons why geometrically nonlinear analysis may be warranted for the hybrid wing body flat panel structure. In general, for sufficiently high internal pressure and/or mechanical loading, energy related to the in-plane strain may become significant relative to the bending strain energy, particularly in thin-walled areas such as the minimum gage skin extensively used in the structure under analysis. To account for this effect, a geometrically nonlinear strain-displacement relationship is needed to properly couple large out-of-plane and in-plane deformations. Depending on the loading, this nonlinear coupling mechanism manifests itself in a distinct manner in compression- and tension-dominated sections of the structure. Under significant compression, nonlinear analysis is needed to accurately predict loss of stability and postbuckled deformation. Under significant tension, the nonlinear effects account for suppression of the out-of-plane deformation due to in-plane stretching. By comparing the present results with the previously

  20. Hybrid-Wing-Body Vehicle Composite Fuselage Analysis and Case Study

    Science.gov (United States)

    Mukhopadhyay, Vivek

    2014-01-01

    Recent progress in the structural analysis of a Hybrid Wing-Body (HWB) fuselage concept is presented with the objective of structural weight reduction under a set of critical design loads. This pressurized efficient HWB fuselage design is presently being investigated by the NASA Environmentally Responsible Aviation (ERA) project in collaboration with the Boeing Company, Huntington Beach. The Pultruded Rod-Stiffened Efficient Unitized Structure (PRSEUS) composite concept, developed at the Boeing Company, is approximately modeled for an analytical study and finite element analysis. Stiffened plate linear theories are employed for a parametric case study. Maximum deflection and stress levels are obtained with appropriate assumptions for a set of feasible stiffened panel configurations. An analytical parametric case study is presented to examine the effects of discrete stiffener spacing and skin thickness on structural weight, deflection and stress. A finite-element model (FEM) of an integrated fuselage section with bulkhead is developed for an independent assessment. Stress analysis and scenario based case studies are conducted for design improvement. The FEM model specific weight of the improved fuselage concept is computed and compared to previous studies, in order to assess the relative weight/strength advantages of this advanced composite airframe technology

  1. Active noise control in fuselage design

    NARCIS (Netherlands)

    Krakers, L.A.; Tooren, M.J.L. van; Beukers, A.; Berkhof, A.P.; Goeje, M.P. de

    2003-01-01

    To achieve comfortable noise levels inside the passenger cabin, sound damping measures have to be taken to improve the sound insulation properties of the bare airframe. Usually the sound insulation requirements of a passenger cabin are met after the mechanical design of the fuselage structure is alr

  2. A high-performance, flexible and robust metal nanotrough-embedded transparent conducting film for wearable touch screen panels

    Science.gov (United States)

    Im, Hyeon-Gyun; An, Byeong Wan; Jin, Jungho; Jang, Junho; Park, Young-Geun; Park, Jang-Ung; Bae, Byeong-Soo

    2016-02-01

    We report a high-performance, flexible and robust metal nanotrough-embedded transparent conducting hybrid film (metal nanotrough-GFRHybrimer). Using an electro-spun polymer nanofiber web as a template and vacuum-deposited gold as a conductor, a junction resistance-free continuous metal nanotrough network is formed. Subsequently, the metal nanotrough is embedded on the surface of a glass-fabric reinforced composite substrate (GFRHybrimer). The monolithic composite structure of our transparent conducting film allows simultaneously high thermal stability (24 h at 250 °C in air), a smooth surface topography (Rrms touch screen panel (TSP) is fabricated using the transparent conducting films. The flexible TSP device stably operates on the back of a human hand and on a wristband.We report a high-performance, flexible and robust metal nanotrough-embedded transparent conducting hybrid film (metal nanotrough-GFRHybrimer). Using an electro-spun polymer nanofiber web as a template and vacuum-deposited gold as a conductor, a junction resistance-free continuous metal nanotrough network is formed. Subsequently, the metal nanotrough is embedded on the surface of a glass-fabric reinforced composite substrate (GFRHybrimer). The monolithic composite structure of our transparent conducting film allows simultaneously high thermal stability (24 h at 250 °C in air), a smooth surface topography (Rrms touch screen panel (TSP) is fabricated using the transparent conducting films. The flexible TSP device stably operates on the back of a human hand and on a wristband. Electronic supplementary information (ESI) available. See DOI: 10.1039/c5nr07657a

  3. Design, fabrication and test of liquid metal heat-pipe sandwich panels

    Science.gov (United States)

    Basiulis, A.; Camarda, C. J.

    1983-01-01

    Integral heat-pipe sandwich panels, which synergistically combine the thermal efficiency of heat pipes and the structural efficiency of honeycomb sandwich panel construction, were fabricated and tested. The designs utilize two different wickable honeycomb cores, facesheets with screen mesh sintered to the internal surfaces, and potassium or sodium as the working fluid. Panels were tested by radiant heating, and the results indicate successful heat pipe operation at temperatures of approximately 922K (1200F). These panels, in addition to solving potential thermal stress problems in an Airframe-Integrated Scramjet Engine, have potential applications as cold plates for electronic component cooling, as radiators for space platforms, and as low distortion, large area structures.

  4. Transient loads identification for a standoff metallic thermal protection system panel.

    Energy Technology Data Exchange (ETDEWEB)

    Hundhausen, R. J. (Roy Jason); Adams, Douglas E.; Derriso, Mark; Kukuchek, Paul; Alloway, Richard

    2004-01-01

    Standoff thermal protection system (TPS) panels are critical structural components in future aerospace vehicles because they protect the vehicle from the hostile environment encountered during space launch and reentry. Consequently, the panels are exposed to a variety of loads including high temperature thermal stresses, thermal shock, acoustic pressure, and foreign object impacts. Transient impacts are especially detrimental because they can cause immediate and severe degradation of the panel in the form of, for example, debonding and buckling of the face sheet, cracking of the fasteners, or deformation of the standoffs. Loads identification methods for determining the magnitude and location of impact loads provide an indication of TPS components that may be more susceptible to failure. Furthermore, a historical database of impact loads encountered can be retained for use in the development of statistical models that relate impact loading to panel life. In this work, simulated inservice transient loads are identified experimentally using two methods: a physics-based approach and an inverse Frequency Response Function (FRF) approach. It is shown that by applying the inverse FRF method, the location and magnitude of these simulated impacts can be identified with a high degree of accuracy. The identified force levels vary significantly with impact location due to the differences in panel deformation at the impact site indicating that resultant damage due to impacts would vary with location as well.

  5. Testing and Analysis of a Composite Non-Cylindrical Aircraft Fuselage Structure. Part 1; Ultimate Design Loads

    Science.gov (United States)

    Przekop, Adam; Jegley, Dawn C.; Lovejoy, Andrew E.; Rouse, Marshall; Wu, Hsi-Yung T.

    2016-01-01

    The Environmentally Responsible Aviation Project aimed to develop aircraft technologies enabling significant fuel burn and community noise reductions. Small incremental changes to the conventional metallic alloy-based 'tube and wing' configuration were not sufficient to achieve the desired metrics. One airframe concept identified by the project as having the potential to dramatically improve aircraft performance was a composite-based hybrid wing body configuration. Such a concept, however, presented inherent challenges stemming from, among other factors, the necessity to transfer wing loads through the entire center fuselage section which accommodates a pressurized cabin confined by flat or nearly flat panels. This paper discusses finite element analysis and testing of a large-scale hybrid wing body center section structure developed and constructed to demonstrate that the Pultruded Rod Stitched Efficient Unitized Structure concept can meet these challenging demands of the next generation airframes. Part I of the paper considers the five most critical load conditions, which are internal pressure only and positive and negative g-loads with and without internal pressure. Analysis results are compared with measurements acquired during testing. Performance of the test article is found to be closely aligned with predictions and, consequently, able to support the hybrid wing body design loads in pristine and barely visible impact damage conditions.

  6. Human health and ecological toxicity potentials due to heavy metal content in waste electronic devices with flat panel displays.

    Science.gov (United States)

    Lim, Seong-Rin; Schoenung, Julie M

    2010-05-15

    Display devices such as cathode-ray tube (CRT) televisions and computer monitors are known to contain toxic substances and have consequently been banned from disposal in landfills in the State of California and elsewhere. New types of flat panel display (FPD) devices, millions of which are now purchased each year, also contain toxic substances, but have not previously been systematically studied and compared to assess the potential impact that could result from their ultimate disposal. In the current work, the focus is on the evaluation of end-of-life toxicity potential from the heavy metal content in select FPD devices with the intent to inform material selection and design-for-environment (DfE) decisions. Specifically, the metals antimony, arsenic, barium, beryllium, cadmium, chromium, cobalt, copper, lead, mercury, molybdenum, nickel, selenium, silver, vanadium, and zinc in plasma TVs, LCD (liquid crystal display) TVs, LCD computer monitors and laptop computers are considered. The human health and ecotoxicity potentials are evaluated through a life cycle assessment perspective by combining data on the respective heavy metal contents, the characterization factors in the U.S. EPA Tool for the Reduction and Assessment of Chemical and other environmental Impacts (TRACI), and a pathway and impact model. Principal contributors to the toxicity potentials are lead, arsenic, copper, and mercury. Although the heavy metal content in newer flat panel display devices creates less human health toxicity potential than that in CRTs, for ecological toxicity, the new devices are worse, especially because of the mercury in LCD TVs and the copper in plasma TVs.

  7. Human health and ecological toxicity potentials due to heavy metal content in waste electronic devices with flat panel displays

    Energy Technology Data Exchange (ETDEWEB)

    Lim, Seong-Rin [Department of Chemical Engineering and Materials Science, University of California, 2017 Kemper Hall, One Shields Avenue, Davis, CA 95616 (United States); Schoenung, Julie M., E-mail: jmschoenung@ucdavis.edu [Department of Chemical Engineering and Materials Science, University of California, 2017 Kemper Hall, One Shields Avenue, Davis, CA 95616 (United States)

    2010-05-15

    Display devices such as cathode-ray tube (CRT) televisions and computer monitors are known to contain toxic substances and have consequently been banned from disposal in landfills in the State of California and elsewhere. New types of flat panel display (FPD) devices, millions of which are now purchased each year, also contain toxic substances, but have not previously been systematically studied and compared to assess the potential impact that could result from their ultimate disposal. In the current work, the focus is on the evaluation of end-of-life toxicity potential from the heavy metal content in select FPD devices with the intent to inform material selection and design-for-environment (DfE) decisions. Specifically, the metals antimony, arsenic, barium, beryllium, cadmium, chromium, cobalt, copper, lead, mercury, molybdenum, nickel, selenium, silver, vanadium, and zinc in plasma TVs, LCD (liquid crystal display) TVs, LCD computer monitors and laptop computers are considered. The human health and ecotoxicity potentials are evaluated through a life cycle assessment perspective by combining data on the respective heavy metal contents, the characterization factors in the U.S. EPA Tool for the Reduction and Assessment of Chemical and other environmental Impacts (TRACI), and a pathway and impact model. Principal contributors to the toxicity potentials are lead, arsenic, copper, and mercury. Although the heavy metal content in newer flat panel display devices creates less human health toxicity potential than that in CRTs, for ecological toxicity, the new devices are worse, especially because of the mercury in LCD TVs and the copper in plasma TVs.

  8. POSTOP: Postbuckled open-stiffener optimum panels-theory and capability

    Science.gov (United States)

    Dickson, J. N.; Biggers, S. B.

    1984-01-01

    The computer program POSTOP was developed to serve as an aid in the analysis and sizing of stiffened composite panels that are loaded in the postbuckling regime. A comprehensive set of analysis routines was coupled to a widely used optimization program to produce this sizing code. POSTOP is intended for the preliminary design of metal or composite panels with open-section stiffeners, subjected to multiple combined biaxial compression (or tension), shear and normal pressure load cases. Longitudinal compression, however, is assumed to be the dominant loading. Temperature, initial bow eccentricity and load eccentricity effects are included. The panel geometry is assumed to be repetitive over several bays in the longitudinal (stiffener) direction as well as in the transverse direction. Analytical routines are included to compute panel stiffnesses, strains, local and panel buckling loads, and skin/stiffener interface stresses. The resulting program is applicable to stiffened panels as commonly used in fuselage, wing, or empennage structures. The analysis procedures and rationale for the assumptions used therein are described in detail.

  9. Transport composite fuselage technology: Impact dynamics and acoustic transmission

    Science.gov (United States)

    Jackson, A. C.; Balena, F. J.; Labarge, W. L.; Pei, G.; Pitman, W. A.; Wittlin, G.

    1986-01-01

    A program was performed to develop and demonstrate the impact dynamics and acoustic transmission technology for a composite fuselage which meets the design requirements of a 1990 large transport aircraft without substantial weight and cost penalties. The program developed the analytical methodology for the prediction of acoustic transmission behavior of advanced composite stiffened shell structures. The methodology predicted that the interior noise level in a composite fuselage due to turbulent boundary layer will be less than in a comparable aluminum fuselage. The verification of these analyses will be performed by NASA Langley Research Center using a composite fuselage shell fabricated by filament winding. The program also developed analytical methodology for the prediction of the impact dynamics behavior of lower fuselage structure constructed with composite materials. Development tests were performed to demonstrate that the composite structure designed to the same operating load requirement can have at least the same energy absorption capability as aluminum structure.

  10. Design-Oriented Analysis of Aircraft Fuselage Structures

    Science.gov (United States)

    Giles, Gary L.

    1998-01-01

    A design-oriented analysis capability for aircraft fuselage structures that utilizes equivalent plate methodology is described. This new capability is implemented as an addition to the existing wing analysis procedure in the Equivalent Laminated Plate Solution (ELAPS) computer code. The wing and fuselage analyses are combined to model entire airframes. The paper focuses on the fuselage model definition, the associated analytical formulation and the approach used to couple the wing and fuselage analyses. The modeling approach used to minimize the amount of preparation of input data by the user and to facilitate the making of design changes is described. The fuselage analysis is based on ring and shell equations but the procedure is formulated to be analogous to that used for plates in order to take advantage of the existing code in ELAPS. Connector springs are used to couple the wing and fuselage models. Typical fuselage analysis results are presented for two analytical models. Results for a ring-stiffened cylinder model are compared with results from conventional finite-element analyses to assess the accuracy of this new analysis capability. The connection of plate and ring segments is demonstrated using a second model that is representative of the wing structure for a channel-wing aircraft configuration.

  11. Analysis of Stainless Steel Sandwich Panels with a Metal Foam Core for Lightweight Fan Blade Design

    Science.gov (United States)

    Min, James B.; Ghosn, Louis J.; Lerch, Bradley A.; Raj, Sai V.; Holland, Frederic A., Jr.; Hebsur, Mohan G.

    2004-01-01

    The quest for cheap, low density and high performance materials in the design of aircraft and rotorcraft engine fan and propeller blades poses immense challenges to the materials and structural design engineers. The present study investigates the use of a sandwich foam fan blade mae up of solid face sheets and a metal foam core. The face sheets and the metal foam core material were an aerospace grade precipitation hardened 17-4 PH stainless steel with high strength and high toughness. The resulting structures possesses a high stiffness while being lighter than a similar solid construction. The material properties of 17-4 PH metal foam are reviewed briefly to describe the characteristics of sandwich structure for a fan blade application. A vibration analysis for natural frequencies and a detailed stress analysis on the 17-4 PH sandwich foam blade design for different combinations of kin thickness and core volume are presented with a comparison to a solid titanium blade.

  12. Endothelial cell activation, oxidative stress and inflammation induced by a panel of metal-based nanomaterials

    DEFF Research Database (Denmark)

    Danielsen, Pernille Høgh; Cao, Yi; Roursgaard, Martin

    2015-01-01

    The importance of composition, size, crystal structure, charge and coating of metal-based nanomaterials (NMs) were evaluated in human umbilical vein endothelial cells (HUVECs) and/or THP-1 monocytic cells. Biomarkers of oxidative stress and inflammation were assessed because they are important in...

  13. Analysis of Stainless Steel Sandwich Panels with a Metal Foam Care for Lightweight Fan Blade Design

    Science.gov (United States)

    Min, James B.; Ghosn, Louis J.; Lerch, Bradley A.; Raj, Sai V.; Holland, Frederic A., Jr.; Hebsur, Mohan G.

    2004-01-01

    The quest for cheap, low density and high performance materials in the design of aircraft and rotorcraft engine fan and propeller blades poses immense challenges to the materials and structural design engineers. Traditionally, these components have been fabricated using expensive materials such as light weight titanium alloys, polymeric composite materials and carbon-carbon composites. The present study investigates the use of P sandwich foam fan blade made up of solid face sheets and a metal foam core. The face sheets and the metal foam core material were an aerospace grade precipitation hardened 17-4 PH stainless steel with high strength and high toughness. The stiffness of the sandwich structure is increased by separating the two face sheets by a foam core. The resulting structure possesses a high stiffness while being lighter than a similar solid construction. Since the face sheets carry the applied bending loads, the sandwich architecture is a viable engineering concept. The material properties of 17-4 PH metal foam are reviewed briefly to describe the characteristics of the sandwich structure for a fan blade application. A vibration analysis for natural frequencies and P detailed stress analysis on the 17-4 PH sandwich foam blade design for different combinations of skin thickness and core volume %re presented with a comparison to a solid titanium blade.

  14. A comprehensive vibration analysis of a coupled rotor/fuselage system

    Science.gov (United States)

    Yeo, Hyeonsoo

    A comprehensive vibration analysis of a coupled rotor/fuselage system for a two-bladed teetering rotor using finite element methods in space and time is developed which incorporates consistent rotor/fuselage structural, aerodynamic, and inertial couplings and a modern free wake model. A coordinate system is developed to take into account a teetering rotor's unique characteristics, such as teetering motion and undersling. Coupled nonlinear periodic blade and fuselage equations are transformed to the modal space in the fixed frame and solved simultaneously. The elastic line and detailed 3-D NASTRAN finite element models of the AH-1G helicopter airframe from the DAMVIBS program are integrated into the elastic rotor finite element model. Analytical predictions of rotor control angles, blade loads, hub forces, and vibration are compared with AH-1G Operation Load Survey flight test data. The blade loads predicted by present analysis show generally fair agreement with the flight test data, especially blade chord bending moment estimation shows good agreement. Calculated 2/rev vertical vibration levels at pilot seat show good correlation with the flight test data both in magnitude and phase, but 4/rev vibration levels show fair correlation only in magnitude. Lateral vibration results show more disagreement than vertical vibration results. Pylon flexibility effect is essential in the two-bladed teetering rotor vibration analysis. The pylon flexibility increases the first lag frequency by about 14%, and decreases 2/rev longitudinal and lateral hub forces by more than half. Rotor/fuselage coupling reduces 2/rev vertical and lateral vibration levels by 60% to 70% and has a small effect on 4/rev vibration levels. Modeling of difficult components (secondary structures, doors/panels, etc) is essential in predicting airframe natural frequencies. Refined aerodynamics such as free wake and unsteady aerodynamics have an important role in the prediction of vibration. For example, free

  15. Design for Metal Sandwich Panel Joints%金属三明治结构连接接头的设计

    Institute of Scientific and Technical Information of China (English)

    孟凡玲; 荣翰

    2013-01-01

    金属三明治板的连接问题是应用三明治材料应解决的关键问题之一.应用大型通用有限元软件ABAQUS,针对特定尺寸的金属三明治结构,进行平行于芯板方向的纵向连接接头设计,选取外接平板和内嵌方框两种典型的接头形式,计算在施加面内载荷情况下,三明治接头的应力集中系数,得出最佳接头几何尺寸.%Metal sandwich panels,due to their excellent properties,can be used as structural elements of smooth flat ship hull like decks, walls and, in certain cases, side shells. Joints between the panels as well as those between the panels and other structures are among the more difficult problems associated with the structures. This paper presents the searching for process of optimum geometry of a panel-to-panel joint of longitudinal arrangement by means of the as-low-as possible values of geometrical stress concentration coefficients at acceptable mass and deformations of the structure.

  16. Fatigue Analysis and Design Optimization of Aircraft’s Central Fuselage

    Science.gov (United States)

    Abbishek, R.; Kumar, B. Ravi; Sankara Subramanian, H.

    2017-08-01

    The centre fuselage of an aircraft plays a very crucial role as most of the important parts such as the front fuselage, aft fuselage and the wings are connected to it. So any load applied on these parts will be transferred to the centre fuselage. Hence it was essential to study the centre fuselage briefly in order to attain high design safety. Fatigue is the process of repeated cyclic loading of a component, which leads to an early failure of the same. The sources of fatigue in an aircraft are the parts connected to it, such as the wings, and the differential pressure between the inside of the fuselage and the outside atmosphere as a result of cabin pressurization. The high pressure inside the fuselage tries to expand the fuselage, whereas the stringers and bulk head prevent it from happening. This change in pressure happens frequently and this results in the fatigue of the centre fuselage. The vibratory loads acting on the other parts are transferred to the centre fuselage, which are also major contributors to the fatigue. The centre fuselage of an aircraft was designed using Pro-E software. The standard aluminium alloy was selected for the material. The various loads acting on the centre fuselage were studied and added to the centre fuselage, along with a differential pressure in a cyclic manner.

  17. Heart rate variability and DNA methylation levels are altered after short-term metal fume exposure among occupational welders: a repeated-measures panel study

    OpenAIRE

    2014-01-01

    Background: In occupational settings, boilermakers are exposed to high levels of metallic fine particulate matter (PM2.5) generated during the welding process. The effect of welding PM2.5 on heart rate variability (HRV) has been described, but the relationship between PM2.5, DNA methylation, and HRV is not known. Methods: In this repeated-measures panel study, we recorded resting HRV and measured DNA methylation levels in transposable elements Alu and long interspersed nuclear element-1 (LINE...

  18. ANALYSIS OF THE ACOUSTIC BEHAVIOR OF MULTILAYER PANELS WITH PERFORATED SHEET METAL FAÇADE ELEMENT AS COMPARED TO THE OUTSIDE NOISE

    Directory of Open Access Journals (Sweden)

    ALINA – ELENA CRETU

    2016-06-01

    Full Text Available This project is a study about covering both structural and economical requirements in order to enhance the utility and pleasure of a perforated metal façade. Optimizes the use of the elements of the multilayer panels and are part of the facade of many buildings, based on the criterion of sound absorption of these multilayer boards which use perforated sheet mainly for esthetic reasons and thermal.

  19. Riveted Lap Joints in Aircraft Fuselage Design, Analysis and Properties

    CERN Document Server

    Skorupa, Andrzej

    2012-01-01

    Fatigue of the pressurized fuselages of transport aircraft is a significant problem all builders and users of aircraft have to cope with for reasons associated with assuring a sufficient lifetime and safety, and formulating adequate inspection procedures. These aspects are all addressed in various formal protocols for creating and maintaining airworthiness, including damage tolerance considerations. In most transport aircraft, fatigue occurs in lap joints, sometimes leading to circumstances that threaten safety in critical ways. The problem of fatigue of lap joints has been considerably enlarged by the goal of extending aircraft lifetimes. Fatigue of riveted lap joints between aluminium alloy sheets, typical of the pressurized aircraft fuselage, is the major topic of the present book. The richly illustrated and well-structured chapters treat subjects such as: structural design solutions and loading conditions for fuselage skin joints; relevance of laboratory test results for simple lap joint specimens to rive...

  20. Structural FEM analysis of the strut-to-fuselage joint of a two-seat composite aircraft

    Energy Technology Data Exchange (ETDEWEB)

    Vargas-Rojas, Erik, E-mail: erikvargasrojas@hotmail.com; Camarena-Arellano, Diego, E-mail: erikvargasrojas@hotmail.com; Hernández-Moreno, Hilario, E-mail: erikvargasrojas@hotmail.com [IPN, ESIME Ticomán, Av. Ticomán 600, Col. San José Ticomán 07340 (Mexico)

    2014-05-15

    An analysis of a strut-to-fuselage joint is realized in order to evaluate the zones with a high probability of failure by means of a safety factor. The whole section is analyzed using the Finite Element Method (FEM) so as to estimate static resistance behavior, therefore it is necessary a numerical mock-up of the section, the mechanical properties of the Carbon-Epoxy (C-Ep) material, and to evaluate the applied loads. Results of the analysis show that the zones with higher probability of failure are found around the wing strut and the fuselage joint, with a safety factor lower than expected in comparison with the average safety factor used on aircrafts built mostly with metals.

  1. Structural FEM analysis of the strut-to-fuselage joint of a two-seat composite aircraft

    Science.gov (United States)

    Vargas-Rojas, Erik; Camarena-Arellano, Diego; Hernández-Moreno, Hilario

    2014-05-01

    An analysis of a strut-to-fuselage joint is realized in order to evaluate the zones with a high probability of failure by means of a safety factor. The whole section is analyzed using the Finite Element Method (FEM) so as to estimate static resistance behavior, therefore it is necessary a numerical mock-up of the section, the mechanical properties of the Carbon-Epoxy (C-Ep) material, and to evaluate the applied loads. Results of the analysis show that the zones with higher probability of failure are found around the wing strut and the fuselage joint, with a safety factor lower than expected in comparison with the average safety factor used on aircrafts built mostly with metals.

  2. Adaptive support for aircraft panel testing: New method and its experimental verification on a beam structure

    Science.gov (United States)

    Sachau, Delf; Baschke, Manuel

    2017-04-01

    Acoustic transmissibility of aircraft panels is measured in full-scale test rigs. The panels are supported at their frames. These boundary conditions do not take into account the dynamic influence of the fuselage, which is significant in the frequency range below 300 Hz. This paper introduces a new adaptive boundary system (ABS). It combines accelerometers and electrodynamic shakers with real-time signal processing. The ABS considers the dynamic effect of the fuselage on the panel. The frames are dominating the dynamic behaviour of a fuselage in the low-frequency range. Therefore, the new method is applied to a beam representing a frame of the aircraft structure. The experimental results are evaluated and the precision of the ABS is discussed. The theoretical apparent mass representing the cut-off part of a frame is calculated and compared with the apparent mass, as provided by the ABS. It is explained how the experimental set-up limits the precision of the ABS.

  3. Sound Transmission Loss Prediction of the Composite Fuselage with Different Methods

    NARCIS (Netherlands)

    Yuan, C.; Bergsma, O.; Beukers, A.

    2012-01-01

    Increase of sound transmission loss(TL) of the fuselage is vital to build a comfortable cabin environment. In this paper, to find a convenient and accurate means for predicting the fuselage TL, the fuselage is modeled as a composite cylinder, and its TL is predicted with the analytical, the

  4. Sound Transmission Loss Prediction of the Composite Fuselage with Different Methods

    NARCIS (Netherlands)

    Yuan, C.; Bergsma, O.; Beukers, A.

    2012-01-01

    Increase of sound transmission loss(TL) of the fuselage is vital to build a comfortable cabin environment. In this paper, to find a convenient and accurate means for predicting the fuselage TL, the fuselage is modeled as a composite cylinder, and its TL is predicted with the analytical, the statisti

  5. Parametric fuselage design: Integration of mechanics and acoustic & thermal insulation

    NARCIS (Netherlands)

    Krakers, L.A.

    2009-01-01

    Designing a fuselage is a very complex process, which involves many different aspects like strength and stability, fatigue, damage tolerance, fire resistance, thermal and acoustic insulation but also inspection, maintenance, production and repair aspects. It is difficult to include all design aspect

  6. Parametric fuselage design: Integration of mechanics and acoustic & thermal insulation

    NARCIS (Netherlands)

    Krakers, L.A.

    2009-01-01

    Designing a fuselage is a very complex process, which involves many different aspects like strength and stability, fatigue, damage tolerance, fire resistance, thermal and acoustic insulation but also inspection, maintenance, production and repair aspects. It is difficult to include all design aspect

  7. 14 CFR 29.549 - Fuselage and rotor pylon structures.

    Science.gov (United States)

    2010-01-01

    ... flight conditions, must be considered. (c) Each engine mount and adjacent fuselage structure must be designed to withstand the loads occurring under accelerated flight and landing conditions, including engine torque. (d) (e) If approval for the use of 21/2-minute OEI power is requested, each engine mount...

  8. Optimization of sandwich composites fuselages under flight loads

    NARCIS (Netherlands)

    Yan, C.; Bergsma, O.; Koussios, S.; Zu, L.; Beukers, A.

    2010-01-01

    The sandwich composites fuselages appear to be a promising choice for the future aircrafts because of their structural efficiency and functional integration advantages. However, the design of sandwich composites is more complex than other structures because of many involved variables. In this paper,

  9. Investigation of the level difference between sound pressure and sound intensity in an aircraft cabin under different fuselage conditions

    Science.gov (United States)

    Atwal, M. S.; Crocker, M. J.; Heitman, K. E.

    1985-01-01

    Problems in using two-microphone sound-intensity (SI) measurements to measure structural transmission losses are investigated in experiments involving light-aircraft fuselage panels and windows. Both sound pressure (SP) and SI are measured near the passenger and door windows and panels of a single-engine aircraft and with these barriers removed, and the effect of increasing interior acoustic absorption and blocking flanking transmission paths is also tested. The results are presented graphically, and the SP measurements are used to indicate frequency ranges in which the two-microphone technique significantly underestimates SI. It is inferred that flanking paths and interior reverberation must be effectively suppressed in order to obtain accurate transmission-loss measurements.

  10. ANALYTICAL DETERMINATION OF RESIDUAL STRENGTH AND LINKUP STRENGTH FOR CURVED PANELS, WITH MULTIPLE SITE DAMAGE

    Directory of Open Access Journals (Sweden)

    Elangovan.R ,

    2011-05-01

    Full Text Available Airplane fuselage has a large number of riveted joints and is subjected to a major loading of differential internal pressure at cruise altitude and zero pressure on the ground. This constitutes one of the major load cycle on the fuselage often referred to as ground air ground (G-A-G cycle. Due to presence of large number of rivet holes, the fuselage skins have a large number of high stress locations and these are locations of potential crack initiation. Thus at the skin joints of the fuselage shell one can have a number of cracks as it ages (i.e used over a period of time. The practice in earlier time was to consider the largest sized crack and considerits acceptance or otherwise. But in fuselage panels one may have one dominate crack and number of smaller secondary cracks. The understanding the safety of a panel with multi site damages is of concern to airline operations. The present paper deals with the estimation of the strength of a flat panel with multi site damage andlead on to estimation of residual life, using fracture mechanics based approach.

  11. Damage criticality and inspection concerns of composite-metallic aircraft structures under blunt impact

    Science.gov (United States)

    Zou, D.; Haack, C.; Bishop, P.; Bezabeh, A.

    2015-04-01

    Composite aircraft structures such as fuselage and wings are subject to impact from many sources. Ground service equipment (GSE) vehicles are regarded as realistic sources of blunt impact damage, where the protective soft rubber is used. With the use of composite materials, blunt impact damage is of special interest, since potential significant structural damage may be barely visible or invisible on the structure's outer surface. Such impact can result in local or non-local damage, in terms of internal delamination in skin, interfacial delamination between stiffeners and skin, and fracture of internal reinforced component such as stringers and frames. The consequences of these events result in aircraft damage, delays, and financial cost to the industry. Therefore, it is necessary to understand the criticality of damage under this impact and provide reliable recommendations for safety and inspection technologies. This investigation concerns a composite-metallic 4-hat-stiffened and 5-frame panel, designed to represent a fuselage structure panel generic to the new generation of composite aircraft. The test fixtures were developed based on the correlation between finite element analyses of the panel model and the barrel model. Three static tests at certain amount of impact energy were performed, in order to improve the understanding of the influence of the variation in shear ties, and the added rotational stiffness. The results of this research demonstrated low velocity high mass impacts on composite aircraft fuselages beyond 82.1 kN of impact load, which may cause extensive internal structural damage without clear visual detectability on the external skin surface.

  12. A Computational Model for Rotor-Fuselage Interactional Aerodynamics

    Science.gov (United States)

    Boyd, D. Douglas, Jr.; Barnwell, Richard W.; Gorton, Susan Althoff

    2000-01-01

    A novel unsteady rotor-fuselage interactional aerodynamics model has been developed. This model loosely couples a Generalized Dynamic Wake Theory (GDWT) to a thin-layer Navier-Stokes solution procedure. This coupling is achieved using an unsteady pressure jump boundary condition in the Navier-Stokes model. The new unsteady pressure jump boundary condition models each rotor blade as a moving pressure jump which travels around the rotor azimuth and is applied between two adjacent planes in a cylindrical, non-rotating grid. Comparisons are made between measured and predicted time-averaged and time-accurate rotor inflow ratios. Additional comparisons are made between measured and predicted unsteady surface pressures on the top centerline and sides of the fuselage.

  13. National Aerospace Plane Integrated Fuselage/Cryotank Risk Reduction program

    Science.gov (United States)

    Dayton, K. E.

    1993-06-01

    The principal objectives and results of the National Aerospace Plane (NASP) Integrated Risk Reduction program are briefly reviewed. The program demonstrated the feasibility of manufacturing lightweight advanced composite materials for single-stage-to-orbit hypersonic flight vehicle applications. A series of combined load simulation tests (thermal, mechanical, and cryogenic) demonstrated proof of concept performance for an all unlined composite cryogenic fuel tank with flat end bulkheads and a high-temperature thin-shell advanced composite fuselage. Temperatures of the fuselage were as high as 1300 F, with 100 percent bending and shear loads applied to the tank while filled with 850 gallons of cryogenic fluid hydrogen (-425 F). Leak rates measured on and around the cryotank shell and bulkheads were well below acceptable levels.

  14. Automated design of minimum drag light aircraft fuselages and nacelles

    Science.gov (United States)

    Smetana, F. O.; Fox, S. R.; Karlin, B. E.

    1982-01-01

    The constrained minimization algorithm of Vanderplaats is applied to the problem of designing minimum drag faired bodies such as fuselages and nacelles. Body drag is computed by a variation of the Hess-Smith code. This variation includes a boundary layer computation. The encased payload provides arbitrary geometric constraints, specified a priori by the designer, below which the fairing cannot shrink. The optimization may include engine cooling air flows entering and exhausting through specific port locations on the body.

  15. Metabolic Panel

    Science.gov (United States)

    ... basic metabolic panel (BMP) and comprehensive metabolic panel (CMP). The BMP checks your blood sugar, calcium, and ... as creatinine to check your kidney function. The CMP includes all of those tests, as well as ...

  16. Panel Analysis

    DEFF Research Database (Denmark)

    Brænder, Morten; Andersen, Lotte Bøgh

    2014-01-01

    Based on our 2013-article, ”Does Deployment to War Affect Soldiers' Public Service Motivation – A Panel Study of Soldiers Before and After their Service in Afghanistan”, we present Panel Analysis as a methodological discipline. Panels consist of multiple units of analysis, observed at two or more...

  17. Panel Analysis

    DEFF Research Database (Denmark)

    Brænder, Morten; Andersen, Lotte Bøgh

    2014-01-01

    Based on our 2013-article, ”Does Deployment to War Affect Soldiers' Public Service Motivation – A Panel Study of Soldiers Before and After their Service in Afghanistan”, we present Panel Analysis as a methodological discipline. Panels consist of multiple units of analysis, observed at two or more...... in research settings where it is not possible to distribute units of analysis randomly or where the independent variables cannot be manipulated. The greatest disadvantage in regard to using panel studies is that data may be difficult to obtain. This is most clearly vivid in regard to the use of panel surveys...

  18. Dynamic response of a cellular metallic sandwich panel subjected to metal foam projectile impact%泡沫金属子弹撞击载荷下多孔金属夹芯板的动态响应

    Institute of Scientific and Technical Information of China (English)

    敬霖; 王志华; 宋延泽; 赵隆茂

    2011-01-01

    The plastic dynamic response of a clamped cellular metallic sandwich panel was investigated experimentally using metal foam projectile. The deformation and failure modes of the sandwich panel subjected to impact load were discussed. Experimental results showed that the sandwich panel under impact loading can fail with several modes; indentation deformation, penetration failure, core compression and core shear. Based on experiments, the corresponding finite element simulations were done using LS-DYNA software. A good agreement was obtained between the numerical and experimental results. The effects of face thickness, core thickness, relative density of core and applied impulse on the shock-resistance behaviors of the sandwich panel were studied. It was shown that the structural response of the sandwich panel is sensitive to its configuration and the permanent deflection of the back face decreases with increase in face-sheet and core thickness. The studying results were a reference for optimal design of cellular metallic sandwich structures.%应用泡沫金属子弹撞击加载的方式研究固支多孔金属夹芯板的塑性动力响应.讨论了多孔金属夹芯板在冲击载荷作用下的破坏模式.结果表明夹芯板的破坏主要表现在前面板的压痕与侵彻失效、芯层压缩和芯层剪切破坏.基于实验研究,应用LS-DYNA3D非线性动力学有限元分析软件对夹芯板动力响应进行有限元分析.数值研究结果与实验结果吻合较好.考察了加载冲量、面板厚度、芯层厚度及相对密度对多孔金属夹芯板抗撞击性能的影响.夹芯板的结构响应对其结构配置比较敏感,增加面板厚度或芯层厚度能够明显地减小后面板的挠度,提高夹芯板的抗撞击能力.研究结果对多孔金属夹芯板的优化设计具有一定的参考价值.

  19. Alleviation of fuselage form drag using vortex flows: Final report

    Energy Technology Data Exchange (ETDEWEB)

    Wortman, A.

    1987-09-15

    The concept of using vortex generators to reduce the fuselage form drag of transport aircraft combines the outflow from the plane of symmetry which is induced by the rotational component of the vortex flow with the energization of the boundary layer to reduce the momentum thickness and to delay or eliminate flow separation. This idea was first advanced by the author in 1981. Under a DOE grant, the concept was validated in wind tunnel tests of approximately 1:17 scale models of fuselages of Boeing 747 and Lockheed C-5 aircraft. The search for the minimum drag involved three vortex generator configurations with three sizes of each in six locations clustered in the aft regions of the fuselages at the beginning of the tail upsweep. The local Reynolds number, which is referred to the length of boundary layer run from the nose, was approximately 10{sup 7} so that a fully developed turbulent boundary layer was present. Vortex generator planforms ranged from swept tapered, through swept straight, to swept reverse tapered wings whose semi-spans ranged from 50% to 125% of the local boundary layer thickness. Pitch angles of the vortex generators were varied by inboard actuators under the control of an external proportional digital radio controller. It was found that certain combinations of vortex generator parameters increased drag. However, with certain configurations, locations, and pitch angles of vortex generators, the highest drag reductions were 3% for the 747 and about 6% for the C-5, thus confirming the arguments that effectiveness increases with the rate of upsweep of the tail. Greatest gains in performance are therefore expected on aft loading military transports. 10 refs., 11 figs., 1 tab.

  20. Multiscale Modeling Methods for Analysis of Failure Modes in Foldcore Sandwich Panels

    Science.gov (United States)

    Sturm, R.; Schatrow, P.; Klett, Y.

    2015-12-01

    The paper presents an homogenised core model suitable for use in the analysis of fuselage sandwich panels with folded composite cores under combined loading conditions. Within a multiscale numerical design process a failure criterion was derived for describing the macroscopic behaviour of folded cores under combined loading using a detailed foldcore micromodel. The multiscale modelling method was validated by simulation of combined compression/bending failure of foldcore sandwich panels.

  1. Cost model relationships between textile manufacturing processes and design details for transport fuselage elements

    Science.gov (United States)

    Metschan, Stephen L.; Wilden, Kurtis S.; Sharpless, Garrett C.; Andelman, Rich M.

    1993-01-01

    Textile manufacturing processes offer potential cost and weight advantages over traditional composite materials and processes for transport fuselage elements. In the current study, design cost modeling relationships between textile processes and element design details were developed. Such relationships are expected to help future aircraft designers to make timely decisions on the effect of design details and overall configurations on textile fabrication costs. The fundamental advantage of a design cost model is to insure that the element design is cost effective for the intended process. Trade studies on the effects of processing parameters also help to optimize the manufacturing steps for a particular structural element. Two methods of analyzing design detail/process cost relationships developed for the design cost model were pursued in the current study. The first makes use of existing databases and alternative cost modeling methods (e.g. detailed estimating). The second compares design cost model predictions with data collected during the fabrication of seven foot circumferential frames for ATCAS crown test panels. The process used in this case involves 2D dry braiding and resin transfer molding of curved 'J' cross section frame members having design details characteristic of the baseline ATCAS crown design.

  2. Impact resistance performance of metallic sandwich panels under low velocity impact%低速冲击下金属面夹芯板性能分析

    Institute of Scientific and Technical Information of China (English)

    王洪欣; 查晓雄; 余敏; 王锦文

    2014-01-01

    Tests,finite element simulations and theoretical analysis were performed here to study the impact resistance performance of metallic sandwich panels under low velocity impact.Firstly,the dynamic performance and damage situation of metallic sandwich panels under dropping hammer impact were analyzed with tests.Finite element method was used to simulate tests,and the applicability of finite element analysis was verified.Then,the total potential energy of the system was established with local deformation potential energy and external force work.The relationship between the concentrated force and local deformation was also obtained.The cracking impact force of the sandwich panels was obtained taking the tensile fracture of face sheets as the failure condition.Finally,the finite element model was established to calculate the cracking impact force of the panels,and the results were compared with those using the formula.It was shown that the cracking impact force of the panels increases with increase in strength and thickness of the face sheets,hammer radius and cracking strain,but hammer mass,strength and thickness of the core have little effect on the cracking impact force.%用实验、有限元及理论分析相结合方法对金属面夹芯板抗冲击性能进行研究。用实验方法研究金属面夹芯板在落锤冲击下的动力性能及破坏情况,并用有限元方法对实验进行模拟分析,验证有限元计算方法的适用性;用理论方法对夹芯板局部变形进行分析,将局部变形势能与外力功建立体系总势能,用势能驻值原理获得集中力与局部变形关系,以面板拉伸断裂为破坏条件,获得夹芯板开裂冲击力;建立有限元模型计算夹芯板开裂破坏时的冲击力,并与公式计算值比较。分析表明,夹芯板开裂冲击力随面板强度、厚度及锤头半径、开裂应变的增加而增大,落锤质量、芯材强度、芯材厚度对开裂冲击力基本无影响。

  3. Differential pulmonary and cardiac effects of pulmonary exposure to a panel of particulate matter-associated metals.

    Science.gov (United States)

    Wallenborn, J Grace; Schladweiler, Mette J; Richards, Judy H; Kodavanti, Urmila P

    2009-11-15

    Biological mechanisms underlying the association between particulate matter (PM) exposure and increased cardiovascular health effects are under investigation. Water-soluble metals reaching systemic circulation following pulmonary exposure are likely exerting a direct effect. However, it is unclear whether specific PM-associated metals may be driving this. We hypothesized that exposure to equimolar amounts of five individual PM-associated metals would cause differential pulmonary and cardiac effects. We exposed male WKY rats (14 weeks old) via a single intratracheal instillation (IT) to saline or 1 micromol/kg body weight of zinc, nickel, vanadium, copper, or iron in sulfate form. Responses were analyzed 4, 24, 48, or 96 h after exposure. Pulmonary effects were assessed by bronchoalveolar lavage fluid levels of total cells, macrophages, neutrophils, protein, albumin, and activities of lactate dehydrogenase, gamma-glutamyl transferase, and n-acetyl glucosaminidase. Copper induced earlier pulmonary injury/inflammation, while zinc and nickel produced later effects. Vanadium or iron exposure induced minimal pulmonary injury/inflammation. Zinc, nickel, or copper increased serum cholesterol, red blood cells, and white blood cells at different time points. IT of nickel and copper increased expression of metallothionein-1 (MT-1) in the lung. Zinc, nickel, vanadium, and iron increased hepatic MT-1 expression. No significant changes in zinc transporter-1 (ZnT-1) expression were noted in the lung or liver; however, zinc increased cardiac ZnT-1 at 24 h, indicating a possible zinc-specific cardiac effect. Nickel exposure induced an increase in cardiac ferritin 96 h after IT. This data set demonstrating metal-specific cardiotoxicity is important in linking metal-enriched anthropogenic PM sources with adverse health effects.

  4. Numerical Investigation of a Fuselage Boundary Layer Ingestion Propulsion Concept

    Science.gov (United States)

    Elmiligui, Alaa A.; Fredericks, William J.; Guynn, Mark D.; Campbell, Richard L.

    2013-01-01

    In the present study, a numerical assessment of the performance of fuselage boundary layer ingestion (BLI) propulsion techniques was conducted. This study is an initial investigation into coupling the aerodynamics of the fuselage with a BLI propulsion system to determine if there is sufficient potential to warrant further investigation of this concept. Numerical simulations of flow around baseline, Boundary Layer Controlled (BLC), and propelled boundary layer controlled airships were performed. Computed results showed good agreement with wind tunnel data and previous numerical studies. Numerical simulations and sensitivity analysis were then conducted on four BLI configurations. The two design variables selected for the parametric study of the new configurations were the inlet area and the inlet to exit area ratio. Current results show that BLI propulsors may offer power savings of up to 85% over the baseline configuration. These interim results include the simplifying assumption that inlet ram drag is negligible and therefore likely overstate the reduction in power. It has been found that inlet ram drag is not negligible and should be included in future analysis.

  5. A Coupled Helicopter Rotor/Fuselage Dynamics Model Using Finite Element Multi-body

    Directory of Open Access Journals (Sweden)

    Cheng Qi-you

    2016-01-01

    Full Text Available To develop a coupled rotor/flexible fuselage model for vibration reduction studies, the equation of coupled rotor-fuselage is set up based on the theory of multi-body dynamics, and the dynamic analysis model is established with the software MSC.ADMAS and MSC.NASTRAN. The frequencies and vibration acceleration responses of the system are calculated with the model of coupled rotor-fuselage, and the results are compared with those of uncoupled modeling method. Analysis results showed that compared with uncoupled model, the dynamic characteristic obtained by the model of coupled rotor-fuselage are some different. The intrinsic frequency of rotor is increased with the increase of rotational velocities. The results also show that the flying speed has obvious influence on the vibration acceleration responses of the fuselage. The vibration acceleration response in the vertical direction is much higher at the low speed and high speed flight conditions.

  6. Heavy Class Helicopter Fuselage Model Drag Reduction by Active Flow Control Systems

    Science.gov (United States)

    De Gregorio, F.

    2017-08-01

    A comprehensive experimental investigation of helicopter blunt fuselage drag reduction using active flow control is being carried out within the European Clean Sky program. The objective is to demonstrate the capability of several active flow technologies to decrease fuselage drag by alleviating the flow separation occurring in the rear area of some helicopters. The work is performed on a simplified blunt fuselage at model-scale. Two different flow control actuators are considered for evaluation: steady blowing, unsteady blowing (or pulsed jets). Laboratory tests of each individual actuator are first performed to assess their performance and properties. The fuselage model is then equipped with these actuators distributed in 3 slots located on the ramp bottom edge. This paper addresses the promising results obtained during the wind-tunnel campaign, since significant drag reductions are achieved for a wide range of fuselage angles of attack and yaw angles without detriment of the other aerodynamic characteristics.

  7. Vibration Characteristics Determined for Stainless Steel Sandwich Panels With a Metal Foam Core for Lightweight Fan Blade Design

    Science.gov (United States)

    Ghosn, Louis J.; Min, James B.; Raj, Sai V.; Lerch, Bradley A.; Holland, Frederic A., Jr.

    2004-01-01

    The goal of this project at the NASA Glenn Research Center is to provide fan materials that are safer, weigh less, and cost less than the currently used titanium alloy or polymer matrix composite fans. The proposed material system is a sandwich fan construction made up of thin solid face sheets and a lightweight metal foam core. The stiffness of the sandwich structure is increased by separating the two face sheets by the foam layer. The resulting structure has a high stiffness and lighter weight in comparison to the solid facesheet material alone. The face sheets carry the applied in-plane and bending loads (ref. 1). The metal foam core must resist the transverse shear and transverse normal loads, as well as keep the facings supported and working as a single unit. Metal foams have ranges of mechanical properties, such as light weight, impact resistance, and vibration suppression (ref. 2), which makes them more suitable for use in lightweight fan structures. Metal foams have been available for decades (refs. 3 and 4), but the difficulties in the original processes and high costs have prevented their widespread use. However, advances in production techniques and cost reduction have created a new interest in this class of materials (ref. 5). The material chosen for the face sheet and the metal foam for this study was the aerospace-grade stainless steel 17-4PH. This steel was chosen because of its attractive mechanical properties and the ease with which it can be made through the powder metallurgy process (ref. 6). The advantages of a metal foam core, in comparison to a typical honeycomb core, are material isotropy and the ease of forming complex geometries, such as fan blades. A section of a 17-4PH sandwich structure is shown in the following photograph. Part of process of designing any blade is to determine the natural frequencies of the particular blade shape. A designer needs to predict the resonance frequencies of a new blade design to properly identify a useful

  8. Technology sandwich panels with mineral wool insulation

    OpenAIRE

    Tyulenev M.; Burtzeva M.; Mednikova E.

    2016-01-01

    Sandwich panel — self–supporting structure consisting of metal cladding and thermal insulation core. As a heat–insulating core used mineral wool, foamed plastics. Production of sandwich panels with insulation mineral wool performed on modular lines for the production of aggregate or conveyer scheme. Sandwich panels are used as load–bearing elements of the facades, as well as a roof covering.

  9. Composite panel, wall assembly and components therefor

    Energy Technology Data Exchange (ETDEWEB)

    Kruger, P.J.

    1988-12-20

    This invention is concerned with improvements in wall assemblies made of a plurality of composite wall panels, such as concrete wall panels, and components and connectors for such assemblies. The invention is also concerned with a method of making such composite wall panels by molding concrete to form a concrete panel. It is particularly applicable for the provision of upstanding walls around oil tanks and hydrocarbon storage facilities, thereby to form part of a containment structure that can satisfy safety regulations for spills around such facilities. In accordance with another aspect of the invention, there is provided a composite building product comprising a concrete panel, said panel being obtained by molding a respective concrete composition. The panel has at least one metal hinge element integrally secured at a respective peripheral edge, with said metal hinge element being secured at the panel to project sufficiently therefrom so as to present a first hinge element. Several of the panels can be connected in a corral-type wall assembly in a variety of configuration. Another aspect of the invention provides, for use in a wall assembly, a portable composite panel comprising a concrete panel body, which is obtained by molding a respective concrete composition; and a frame assembly for reinforcing the peripheral edges of said concrete panel body. The frame assembly includes at least one metal member for provision of a first hing element for connecting a plurality of said panels in a corral-type wall assembly. 7 figs.

  10. Research on Application of Zinc-coated Steel Panel in Automotive Sheet Metal Parts%汽车钣金件镀锌板应用研究

    Institute of Scientific and Technical Information of China (English)

    郭青华; 陈静; 李立军

    2012-01-01

    在整车开发中,车身防锈对于整车品质和市场定位起着决定性的作用。通过对前期开发车型易锈蚀部位调查,需对车门、地板、机盖及加油口等各个组成部分进行防锈控制。文章主要针对汽车钣金件镀锌板应用进行阐述,分别从镀锌板的分类及应用、优缺点及选择确定原则3方面深入研究,并对车身易锈蚀部位进行系统分析和控制,延长钣金件使用寿命,提高整车品质。%Anti-rust of auto body plays a decisive role in automobile quality and market position in automobile development. Investigation on susceptible to rusting parts of dour, floor, hood and fuel tank cover in developed vehicles is needed to be antirust control. Aimed at the application of zinc-coated steel panel for auto sheet metal parts, from the classification and application, advantages and disadvantages, determining principle of zinc-coated steel panel is studied. Systematic analysis and control on easy to rust parts are proceeded. Service life of stamping parts is prolonged and automobile quality is improved.

  11. Panel Session

    DEFF Research Database (Denmark)

    Bertelsen, Olav Wedege

    2004-01-01

    In this panel session, four researchers will discuss the role of a theoretical foundation, in particular AT, in the design of information technology based artefacts. The general discussion will take of from a specific examination of the ActAD approach.......In this panel session, four researchers will discuss the role of a theoretical foundation, in particular AT, in the design of information technology based artefacts. The general discussion will take of from a specific examination of the ActAD approach....

  12. Distribution of Acoustic Power Spectra for an Isolated Helicopter Fuselage

    Directory of Open Access Journals (Sweden)

    Kusyumov A.N.

    2016-01-01

    Full Text Available The broadband aerodynamic noise can be studied, assuming isotropic flow, turbulence and decay. Proudman’s approach allows practical calculations of noise based on CFD solutions of RANS or URANS equations at the stage of post processing and analysis of the solution. Another aspect is the broadband acoustic spectrum and the distribution of acoustic power over a range of frequencies. The acoustic energy spectrum distribution in isotropic turbulence is non monotonic and has a maximum at a certain value of Strouhal number. In the present work the value of acoustic power peak frequency is determined using a prescribed form of acoustic energy spectrum distribution presented in papers by S. Sarkar and M. Y. Hussaini and by G. M. Lilley. CFD modelling of the flow around isolated helicopter fuselage model was considered using the HMB CFD code and the RANS equations.

  13. Drop test analysis of fuselage section of R80 commuter aircraft by using finite element method

    Science.gov (United States)

    Anggono, Agus Dwi; Ardianto, Adik Nofa Rochma Wahyu

    2017-04-01

    In commercial aerospace development, feasibility accidents design or crashworthiness is a major concern in aviation safety. Fuselage structure plays an important role in absorbing energy during an accident. The research aims are to determine drop test phenomenon on the fuselage, to investigate deformation occurred in the structure of the fuselage, and to know the influence of the airframe falls position to the stress strain which occurred in the structure of the fuselage. This research was conducted by varying the fall angle of the fuselage in a vertical position or 0° and 15°. Fuselage design was modeled by using SolidWorks. Then the model is imported to the Abaqus for drop test simulation. From the simulation results, it can be obtained the phenomenon of deformation on the structure of the fuselage when it comes in contact with the rigid ground. The high deformation occurs shows the structure capabilities in order to absorb the impact. It could be happened because the deformation is influenced by internal energy and strain energy. The various positions shows the structure capability in order to withstand impact loads during periods of 4-8 seconds and the maximum deformation was reached in 12 seconds. The experiment on the vertical position and the position falls of 15° angle was delivered the highest stress strain. The stress was 483 MPa in struts section, 400.78 MPa in skin section, 358.28 MPa in the floor and 483 MPa in the cargo frame section.

  14. TO THE DEVELOPMENT OF AERODYNAMIC SHAPE OF MEDIUM SIZED PERSPECTIVE HELICOPTER FUSELAGE

    Directory of Open Access Journals (Sweden)

    2016-01-01

    Full Text Available This paper presents the initial stage of work out of the helicopter body aerodynamic configuration. The main pur- pose of this work is to design the model of the fuselage and to minimize its drag.The analysis of experimental data obtained in TsAGI and other research centers was made at the first stage of the work. All features of flow around parts of the fuselage obtained from experimental data were taken into account. The de- pendencies of the fuselage component drag, such as the bow, fairings exhaust pipes of helicopter, sponsons, and tail sectionof the fuselage, on their form are described in this article.At the second stage the fuselage geometry was created in program SolidWorks. All the features of the flow around various fuselage components derived from the experimental data were considered in designing.The third stage is calculating of fuselage model aerodynamic characteristics. The calculations were made in the program ANSYS CFX (TsAGI License №501024. Boundary conditions were chosen so as to correspond to normal at- mospheric conditions at 1,000 meters with velocity of flight is V = 85 m/s. The output of the hot jet from engines is takinginto account in computation. The purpose of this calculation is to find the optimal angle of the engine exhaust pipe whenthe hot spray does not intersect with the tail and stabilizer and creates the maximum of propulsive force. The volume of the grid in computational domain is approximately 13 million cells.Data analysis has shown that the fuselage has a 20% less drag at cruising flight (аf = -4 ° compared to the original model. The hot jets do not intersect with the tail and stabilizers at cruising flight so the fuselage is protected from overheating.

  15. Development of pressure containment and damage tolerance technology for composite fuselage structures in large transport aircraft

    Science.gov (United States)

    Smith, P. J.; Thomson, L. W.; Wilson, R. D.

    1986-01-01

    NASA sponsored composites research and development programs were set in place to develop the critical engineering technologies in large transport aircraft structures. This NASA-Boeing program focused on the critical issues of damage tolerance and pressure containment generic to the fuselage structure of large pressurized aircraft. Skin-stringer and honeycomb sandwich composite fuselage shell designs were evaluated to resolve these issues. Analyses were developed to model the structural response of the fuselage shell designs, and a development test program evaluated the selected design configurations to appropriate load conditions.

  16. An FSI Simulation of the Metal Panel Deflection in a Shock Tube Using Illinois Rocstar Simulation Suite

    Energy Technology Data Exchange (ETDEWEB)

    Shin, Jung Hun; Sa, Jeong Hwan; Kim, Han Gi; Cho, Keum Won [Korea Institute of Science and Technology Information, Daejeon (Korea, Republic of)

    2017-05-15

    As the recent development of computing architecture and application software technology, real world simulation, which is the ultimate destination of computer simulation, is emerging as a practical issue in several research sectors. In this paper, metal plate motion in a square shock tube for small time interval was calculated using a supercomputing-based fluid-structure-combustion multi-physics simulation tool called Illinois Rocstar, developed in a US national R and D program at the University of Illinois. Afterwards, the simulation results were compared with those from experiments. The coupled solvers for unsteady compressible fluid dynamics and for structural analysis were based on the finite volume structured grid system and the large deformation linear elastic model, respectively. In addition, a strong correlation between calculation and experiment was shown, probably because of the predictor corrector time-integration scheme framework. In the future, additional validation studies and code improvements for higher accuracy will be conducted to obtain a reliable open-source software research tool.

  17. EXPERIMENTAL INVESTIGATION OF AERODYNAMIC INTERACTION EFFECT OF ROTOR WAKE ON FUSELAGE OF HELICOPTER

    Institute of Scientific and Technical Information of China (English)

    2000-01-01

    The interaction effect of rotor wake on fuselage of helicopter was investigated with experimental method. The results from experiment have proved that for the drag of fuselage the effect of rotor airflow is closely in connection with both the flight speed and the collective pitch of blades, while for the thrust and pitch moment of fuselage the collective pitch angle of blades plays more important role. A simple and effective computing method about aerodynamic interaction can be derived from the measured data. In order to implement the experiment, a fuselage model, a special sensor, the measurement and data acquisition and processing system were designed and manufactured according to the special requirements of this research project, thereby a good base was built up for carrying out experiments successfully with high quality.

  18. 14 CFR 27.549 - Fuselage, landing gear, and rotor pylon structures.

    Science.gov (United States)

    2010-01-01

    ... engine mount and adjacent fuselage structure must be designed to withstand the loads occurring under accelerated flight and landing conditions, including engine torque. (Secs. 604, 605, 72 Stat. 778, 49...

  19. Coupled rotor-flexible fuselage vibration reduction using open loop higher harmonic control

    Science.gov (United States)

    Papavassiliou, I.; Friedmann, P. P.; Venkatesan, C.

    1991-01-01

    A fundamental study of vibration prediction and vibration reduction in helicopters using active controls was performed. The nonlinear equations of motion for a coupled rotor/flexible fuselage system have been derived using computer algebra on a special purpose symbolic computer facility. The trim state and vibratory response of the helicopter are obtained in a single pass by applying the harmonic balance technique and simultaneously satisfying the trim and the vibratory response of the helicopter for all rotor and fuselage degrees of freedom. The influence of the fuselage flexibility on the vibratory response is studied. It is shown that the conventional single frequency higher harmonic control is capable of reducing either the hub loads or only the fuselage vibrations but not both simultaneously. It is demonstrated that for simultaneous reduction of hub shears and fuselae vibrations a new scheme called multiple higher harmonic control is required.

  20. Sandwich Panels

    Directory of Open Access Journals (Sweden)

    N. Ramachandran

    1963-05-01

    Full Text Available This introductory article give an insight into the different methods employed in the construction of Sandwich panels, their limitations and future design application for defence use as a structural element with one of the highest strength-weight ratios yet devised.

  1. Panel Sessions.

    Science.gov (United States)

    Proceedings of the ASIS Mid-Year Meeting, 1992

    1992-01-01

    Lists the speakers and summarizes the issues addressed for 12 panel sessions on topics related to networking, including libraries and national networks, federal national resources and energy programs, multimedia issues, telecommuting, remote image serving, accessing the Internet, library automation, scientific information, applications of Z39.50,…

  2. Detailed design of a lattice composite fuselage structure by a mixed optimization method

    Science.gov (United States)

    Liu, D.; Lohse-Busch, H.; Toropov, V.; Hühne, C.; Armani, U.

    2016-10-01

    In this article, a procedure for designing a lattice fuselage barrel is developed. It comprises three stages: first, topology optimization of an aircraft fuselage barrel is performed with respect to weight and structural performance to obtain the conceptual design. The interpretation of the optimal result is given to demonstrate the development of this new lattice airframe concept for the fuselage barrel. Subsequently, parametric optimization of the lattice aircraft fuselage barrel is carried out using genetic algorithms on metamodels generated with genetic programming from a 101-point optimal Latin hypercube design of experiments. The optimal design is achieved in terms of weight savings subject to stability, global stiffness and strain requirements, and then verified by the fine mesh finite element simulation of the lattice fuselage barrel. Finally, a practical design of the composite skin complying with the aircraft industry lay-up rules is presented. It is concluded that the mixed optimization method, combining topology optimization with the global metamodel-based approach, allows the problem to be solved with sufficient accuracy and provides the designers with a wealth of information on the structural behaviour of the novel anisogrid composite fuselage design.

  3. A Study of the Utilization of Advanced Composites in Fuselage Structures of Commercial Aircraft

    Science.gov (United States)

    Watts, D. J.; Sumida, P. T.; Bunin, B. L.; Janicki, G. S.; Walker, J. V.; Fox, B. R.

    1985-01-01

    A study was conducted to define the technology and data needed to support the introduction of advanced composites in the future production of fuselage structure in large transport aircraft. Fuselage structures of six candidate airplanes were evaluated for the baseline component. The MD-100 was selected on the basis of its representation of 1990s fuselage structure, an available data base, its impact on the schedule and cost of the development program, and its availability and suitability for flight service evaluation. Acceptance criteria were defined, technology issues were identified, and a composite fuselage technology development plan, including full-scale tests, was identified. The plan was based on composite materials to be available in the mid to late 1980s. Program resources required to develop composite fuselage technology are estimated at a rough order of magnitude to be 877 man-years exclusive of the bird strike and impact dynamic test components. A conceptual composite fuselage was designed, retaining the basic MD-100 structural arrangement for doors, windows, wing, wheel wells, cockpit enclosure, major bulkheads, etc., resulting in a 32 percent weight savings.

  4. Damage tolerance analysis of aircraft reinforced panels

    Directory of Open Access Journals (Sweden)

    A. Pirondi

    2011-04-01

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

  5. 几种金属面夹芯板的耐火性能测试%Test on fire resistance performance of several metal surface sandwich panels

    Institute of Scientific and Technical Information of China (English)

    何国山; 潘永红; 李晓增; 刘东发; 尹碧军

    2013-01-01

    The fire resistance performance of rockwool sandwich panel,EPS sandwich panel,polyurethane sandwich panel and phenolic sandwich panel with different thickness was carried out by the vertical element fire test furnace.The fire resistance test of rock wool combined with EPS or polyurethane showed that the fire resistance of 100 mm thick rock wool-EPS sandwich panel and rock wool-polyurethane sandwich panel were 85 min,90 min,respectively.The fire resistance of EPS sandwich panel and polyurethane sandwich panel was improved greatly.%用垂直构件耐火试验炉研究不同厚度的金属面岩棉夹芯板、EPS夹芯板、聚氨酯夹芯板、酚醛夹芯板的耐火性能.用岩棉与EPS、岩棉与聚氨酯进行组合进行耐火性能测试,100 mm厚的岩棉—EPS夹芯板、岩棉—聚氨酯的耐火极限分别达到85、90 min,较大提高了EPS夹芯板和聚氨酯夹芯板的耐火性能.

  6. Damage Tolerance of Pre-Stressed Composite Panels Under Impact Loads

    Science.gov (United States)

    Johnson, Alastair F.; Toso-Pentecôte, Nathalie; Schueler, Dominik

    2014-02-01

    An experimental test campaign studied the structural integrity of carbon fibre/epoxy panels preloaded in tension or compression then subjected to gas gun impact tests causing significant damage. The test programme used representative composite aircraft fuselage panels composed of aerospace carbon fibre toughened epoxy prepreg laminates. Preload levels in tension were representative of design limit loads for fuselage panels of this size, and maximum compression preloads were in the post-buckle region. Two main impact scenarios were considered: notch damage from a 12 mm steel cube projectile, at velocities in the range 93-136 m/s; blunt impact damage from 25 mm diameter glass balls, at velocities 64-86 m/s. The combined influence of preload and impact damage on panel residual strengths was measured and results analysed in the context of damage tolerance requirements for composite aircraft panels. The tests showed structural integrity well above design limit loads for composite panels preloaded in tension and compression with visible notch impact damage from hard body impact tests. However, blunt impact tests on buckled compression loaded panels caused large delamination damage regions which lowered plate bending stiffness and reduced significantly compression strengths in buckling.

  7. Prediction and Measurement of the Vibration and Acoustic Radiation of Panels Subjected to Acoustic Loading

    Science.gov (United States)

    Turner, Travis L.; Rizzi, Stephen A.

    1995-01-01

    Interior noise and sonic fatigue are important issues in the development and design of advanced subsonic and supersonic aircraft. Conventional aircraft typically employ passive treatments, such as constrained layer damping and acoustic absorption materials, to reduce the structural response and resulting acoustic levels in the aircraft interior. These techniques require significant addition of mass and only attenuate relatively high frequency noise transmitted through the fuselage. Although structural acoustic coupling is in general very important in the study of aircraft fuselage interior noise, analysis of noise transmission through a panel supported in an infinite rigid baffle (separating two semi-infinite acoustic domains) can be useful in evaluating the effects of active/adaptive materials, complex loading, etc. Recent work has been aimed at developing adaptive and/or active methods of controlling the structural acoustic response of panels to reduce the transmitted noise1. A finite element formulation was recently developed to study the dynamic response of shape memory alloy (SMA) hybrid composite panels (conventional composite panel with embedded SMA fibers) subject to combined acoustic and thermal loads2. Further analysis has been performed to predict the far-field acoustic radiation using the finite element dynamic panel response prediction3. The purpose of the present work is to validate the panel vibration and acoustic radiation prediction methods with baseline experimental results obtained from an isotropic panel, without the effect of SMA.

  8. Metals 2000

    Energy Technology Data Exchange (ETDEWEB)

    Allison, S.W.; Rogers, L.C.; Slaughter, G. [Oak Ridge National Lab., TN (United States); Boensch, F.D. [6025 Oak Hill Lane, Centerville, OH (United States); Claus, R.O.; de Vries, M. [Virginia Polytechnic Inst. and State Univ., Blacksburg, VA (United States)

    1993-05-01

    This strategic planning exercise identified and characterized new and emerging advanced metallic technologies in the context of the drastic changes in global politics and decreasing fiscal resources. In consideration of a hierarchy of technology thrusts stated by various Department of Defense (DOD) spokesmen, and the need to find new and creative ways to acquire and organize programs within an evolving Wright Laboratory, five major candidate programs identified are: C-17 Flap, Transport Fuselage, Mach 5 Aircraft, 4.Fighter Structures, and 5. Missile Structures. These results were formed by extensive discussion with selected major contractors and other experts, and a survey of advanced metallic structure materials. Candidate structural applications with detailed metal structure descriptions bracket a wide variety of uses which warrant consideration for the suggested programs. An analysis on implementing smart skins and structures concepts is given from a metal structures perspective.

  9. 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

  10. Nonlinear coupled rotor-fuselage helicopter vibration studies with higher harmonic control

    Science.gov (United States)

    Friedmann, P. P.; Venkatesan, C.; Papavassiliou, I.

    1990-01-01

    This paper addresses the problem of vibration prediction and vibration reduction in helicopters by means of active control methodologies. The nonlinear equations of a coupled rotor/flexible-fuselage system have been derived using computer algebra, thus relegating this tedious task to the computer. In the solution procedure the trim state and vibratory response of the helicopter are obtained in a single pass by using a harmonic balance technique and simultaneously satisfying the trim and the vibratory response of the helicopter in all the rotor and fuselage degrees of freedom. Using this solution procedure, the influence of the fuselage flexibility on the vibratory response is studied. In addition, it is shown that the conventional single frequency HHC is capable of reducing either the hub loads or only the fuselage vibrations but not both simultaneously. A new scheme called MHHC, having multiple higher harmonic pitch inputs, was used to accomplish this task of simultaneously reducing both the vibratory hub loads and fuselage vibratory response. In addition, the uniqueness of this MHHC scheme is explained in detail.

  11. Energy transmission through a double-wall curved stiffened panel using Green's theorem

    Science.gov (United States)

    Ghosh, Subha; Bhattacharya, Partha

    2015-04-01

    It is a common practice in aerospace and automobile industries to use double wall panels as fuselage skins or in window panels to improve acoustic insulation. However, the scientific community is yet to develop a reliable prediction method for a suitable vibro-acoustic model for sound transmission through a curved double-wall panel. In this quest, the present work tries to delve into the modeling of energy transmission through a double-wall curved panel. Subsequently the radiation of sound power into the free field from the curved panel in the low to mid frequency range is also studied. In the developed model to simulate a stiffened aircraft fuselage configuration, the outer wall is provided with longitudinal stiffeners. A modal expansion theory based on Green's theorem is implemented to model the energy transmission through an acoustically coupled double-wall curved panel. An elemental radiator approach is implemented to calculate the radiated energy from the curved surface in to the free field. The developed model is first validated with various numerical models available. It has been observed in the present study that the radius of curvature of the surface has a prominent effect on the behavior of radiated sound power into the free field. Effect of the thickness of the air gap between the two curved surfaces on the sound power radiation has also been noted.

  12. Structural detailing of openings in sandwich panels

    NARCIS (Netherlands)

    Tomà, T.; Courage, W.

    1996-01-01

    European Recommendations exist which provide calculation rules to determine the strength and stiffness of sandwich panels composed of two metal faces with a foam in between. In case of openings in such panels (e.g. for windows) an influence will appear with regard to the stiffness and loadbearing ca

  13. Noniterative grid generation using parabolic difference equations for fuselage-wing flow calculations

    Science.gov (United States)

    Nakamura, S.

    1982-01-01

    A fast method for generating three-dimensional grids for fuselage-wing transonic flow calculations using parabolic difference equations is described. No iterative scheme is used in the three-dimensional sense; grids are generated from one grid surface to the next starting from the fuselage surface. The computational procedure is similar to the iterative solution of the two-dimensional heat conduction equation. The proposed method is at least 10 times faster than the elliptic grid generation method and has much smaller memory requirements. Results are presented for a fuselage and wing of NACA-0012 section and thickness ratio of 10 percent. Although only H-grids are demonstrated, the present technique should be applicable to C-grids and O-grids in three dimensions.

  14. Thermal Inspection of a Composite Fuselage Section Using a Fixed Eigenvector Principal Component Analysis Method

    Science.gov (United States)

    Zalameda, Joseph N.; Bolduc, Sean; Harman, Rebecca

    2017-01-01

    A composite fuselage aircraft forward section was inspected with flash thermography. The fuselage section is 24 feet long and approximately 8 feet in diameter. The structure is primarily configured with a composite sandwich structure of carbon fiber face sheets with a Nomex(Trademark) honeycomb core. The outer surface area was inspected. The thermal data consisted of 477 data sets totaling in size of over 227 Gigabytes. Principal component analysis (PCA) was used to process the data sets for substructure and defect detection. A fixed eigenvector approach using a global covariance matrix was used and compared to a varying eigenvector approach. The fixed eigenvector approach was demonstrated to be a practical analysis method for the detection and interpretation of various defects such as paint thickness variation, possible water intrusion damage, and delamination damage. In addition, inspection considerations are discussed including coordinate system layout, manipulation of the fuselage section, and the manual scanning technique used for full coverage.

  15. Panel discussion

    Energy Technology Data Exchange (ETDEWEB)

    No Author Given

    1975-01-01

    Panel discussion: summation and future projections. Introductory remarks by panelists followed by questions and comments from the floor. Panelists: Dr. Joseph Barnea (former director of Resources and Transport for the United Nations; energy consultant to the United Nations Institute for Training and Research (UNITAR)); the Honorable Clyde F. Bel, Jr. (member of the Louisiana House of Representatives representing District 90 and New Orleans); Dr. David Lombard (acting chief of the Advanced Systems Branch of the Division of Geothermal Energy Research and Technology, Energy Research and Development Administration (ERDA)); Fred C. Repper (vice-president of Central Power and Light Company in Corpus Christi, Texas); Dr. Hans Suter (environmental consultant in Corpus Christi, Texas; environmental columnist for the Corpus Christi Caller Times). Session chairman: Herbert Woodson.

  16. 78 FR 68775 - Special Conditions: Airbus, Model A350-900 Series Airplane; Composite Fuselage In-Flight Fire...

    Science.gov (United States)

    2013-11-15

    ...; Composite Fuselage In-Flight Fire/Flammability Resistance AGENCY: Federal Aviation Administration (FAA), DOT... associated with the in-flight fire and flammability resistance of the composite fuselage. Experience has shown that eliminating fire propagation on the surface of interior and insulating materials enhances...

  17. Interactive Inverse Design Optimization of Fuselage Shape for Low-Boom Supersonic Concepts

    Science.gov (United States)

    Li, Wu; Shields, Elwood; Le, Daniel

    2008-01-01

    This paper introduces a tool called BOSS (Boom Optimization using Smoothest Shape modifications). BOSS utilizes interactive inverse design optimization to develop a fuselage shape that yields a low-boom aircraft configuration. A fundamental reason for developing BOSS is the need to generate feasible low-boom conceptual designs that are appropriate for further refinement using computational fluid dynamics (CFD) based preliminary design methods. BOSS was not developed to provide a numerical solution to the inverse design problem. Instead, BOSS was intended to help designers find the right configuration among an infinite number of possible configurations that are equally good using any numerical figure of merit. BOSS uses the smoothest shape modification strategy for modifying the fuselage radius distribution at 100 or more longitudinal locations to find a smooth fuselage shape that reduces the discrepancies between the design and target equivalent area distributions over any specified range of effective distance. For any given supersonic concept (with wing, fuselage, nacelles, tails, and/or canards), a designer can examine the differences between the design and target equivalent areas, decide which part of the design equivalent area curve needs to be modified, choose a desirable rate for the reduction of the discrepancies over the specified range, and select a parameter for smoothness control of the fuselage shape. BOSS will then generate a fuselage shape based on the designer's inputs in a matter of seconds. Using BOSS, within a few hours, a designer can either generate a realistic fuselage shape that yields a supersonic configuration with a low-boom ground signature or quickly eliminate any configuration that cannot achieve low-boom characteristics with fuselage shaping alone. A conceptual design case study is documented to demonstrate how BOSS can be used to develop a low-boom supersonic concept from a low-drag supersonic concept. The paper also contains a study

  18. 热环境下金属壁板噪声激励动响应试验研究%Dynamic response tests of metallic panels excited by acoustic loads in thermal environment

    Institute of Scientific and Technical Information of China (English)

    吴振强; 李海波; 程昊; 郭静; 张伟

    2016-01-01

    Metallic panels are major structural components for thermal protection system of hypersonic vehicles, which are exposed to a severe combination of aerodynamic, thermal and acoustic environments during cruise or re-entry flights. It presents a significant challenge for the integrity and the durability for these structures. Titanium flat and stiffened panels are designed. Then, a series of dynamic response tests of these panels are carried out using a thermal-acoustic apparatus. The temperature of the testing panel is up to 400℃and the exciting acoustic load is over 162 dB. Dynamic responses of these testing panels are measured using high temperature accelerometer and strain gauge during the testing process. Results show that the maximal root mean square (RMS) acceleration values of the flat plate and stiffened panel are approximate to 94.5g and 199.0g, respectively. It is shown that the dynamic RMS values are dominated by sound pressure level of acoustic loads. However, the thermal environment has more effects on the power spectral density distribution than the RMS values of dynamic response excited by acoustic loads.%高超声速飞行器热防护系统包含多种形式的金属壁板结构,巡航或再入过程中经历着严酷的气动热、气动力、噪声等复合环境,严重威胁着飞行器结构的完整性和可靠性。为评估壁板结构的耐噪声性能,设计了钛合金平板和加筋板试验件,采用热噪声试验系统开展了试验件中心温度最高为400℃、噪声最高为162dB的动响应试验,采用高温加速度计和高温应变片对动态响应进行了测试。结果表明,钛合金平板和加筋板的最大加速度均方根值分别可达94.5 g和199.0g,金属壁板动态响应均方根值与噪声量级密切相关,受热环境影响较小,而热环境显著改变了动态响应的频谱分布。

  19. Study on flow behavior and structure over chined fuselage at high angle of attack

    Institute of Scientific and Technical Information of China (English)

    2010-01-01

    A study of leeward vortex structure over chined fuselage and the effects of micro tip perturbation on its vortex flow have been carried out in wind tunnel experiments at Reynolds numbers from 1.26×105 to 5.04×105 with PIV and pressure measurement techniques.Firstly,the experiment results have proved that micro tip perturbation has no effects on the vortex flow and its aerodynamic characteristics over chined fuselage at high angle of attack,in which there are not any non-deterministic flow behaviors.Secondly,the evolution of leeward vortex structure over chined fuselage along the axis of model can be divided into four flow regimes:linear conical developed regime,decay regime of leeward vortex intensity,asymmetric leeward vortex break down regime and completely break down regime.And a correlation between leeward vortex structure and sectional aerodynamic force was also revealed in the present paper.Thirdly,the experiment results show the behavior of leeward vortex core trajectories and zonal characteristics of leeward vortex structure with angles of attack.Finally,the experiment results of Reynolds number effect on the leeward vortex flow have further confirmed research conclusions from previous studies:the flows over chined fuselage at high angles of attack are insensitive to variation of Reynolds number,and there is a little effect on the secondary boundary layer separation and the suction peak induced by leeward vortex.

  20. Transonic perturbation analysis of wing-fuselage-nacelle-pylon configurations with powered jet exhausts

    Science.gov (United States)

    Wai, J. C.; Sun, C. C.; Yoshihara, H.

    1982-01-01

    A method using a transonic small disturbance code with successive line over-relaxation is described for treating wing/fuselage configurations with a nacelle/pylon/powered jet. Examples illustrating its use for the NASA transport research model are given. Reasonable test/theory comparisons were obtained.

  1. Design, Analysis, Fabrication and Testing of Grid-Stiffened for Fuselage Applications

    NARCIS (Netherlands)

    Shroff, S.

    2014-01-01

    The application of composites in aircraft structures has grown significantly in the past decade, and an increase in this growth in application has recently been achieved in fuselage designs for large civil aircraft such as the Boeing B787 and the Airbus A350. In conventional design philosophies, wei

  2. Study of multiple cracks in airplane fuselage by micromechanics and complex variables

    Science.gov (United States)

    Denda, Mitsunori; Dong, Y. F.

    1994-01-01

    Innovative numerical techniques for two dimensional elastic and elastic-plastic multiple crack problems are presented using micromechanics concepts and complex variables. The simplicity and the accuracy of the proposed method will enable us to carry out the multiple-site fatigue crack propagation analyses for airplane fuselage by incorporating such features as the curvilinear crack path, plastic deformation, coalescence of cracks, etc.

  3. Fracture and strain rate behavior of airplane fuselage materials under blast loading

    NARCIS (Netherlands)

    Mediavilla Varas, J.; Soetens, F.; Kroon, E.; Aanhold, J.E. van; Meulen, O.R. van der; Sagimon, M.

    2010-01-01

    The dynamic behavior of three commonly used airplane fuselage materials is investigated, namely of Al2024-T3, Glare-3 and CFRP. Dynamic tensile tests using a servo-hydraulic and a light weight shock testing machine (LSM) have been performed. The results showed no strain rate effect on Al2024-T3 and a

  4. Water Impact Test and Simulation of a Composite Energy Absorbing Fuselage Section

    Science.gov (United States)

    Fasanella, Edwin L.; Jackson, Karen E.; Sparks, Chad; Sareen, Ashish

    2003-01-01

    In March 2002, a 25-ft/s vertical drop test of a composite fuselage section was conducted onto water. The purpose of the test was to obtain experimental data characterizing the structural response of the fuselage section during water impact for comparison with two previous drop tests that were performed onto a rigid surface and soft soil. For the drop test, the fuselage section was configured with ten 100-lb. lead masses, five per side, that were attached to seat rails mounted to the floor. The fuselage section was raised to a height of 10-ft. and dropped vertically into a 15-ft. diameter pool filled to a depth of 3.5-ft. with water. Approximately 70 channels of data were collected during the drop test at a 10-kHz sampling rate. The test data were used to validate crash simulations of the water impact that were developed using the nonlinear, explicit transient dynamic codes, MSC.Dytran and LS-DYNA. The fuselage structure was modeled using shell and solid elements with a Lagrangian mesh, and the water was modeled with both Eulerian and Lagrangian techniques. The fluid-structure interactions were executed using the fast general coupling in MSC.Dytran and the Arbitrary Lagrange-Euler (ALE) coupling in LS-DYNA. Additionally, the smooth particle hydrodynamics (SPH) meshless Lagrangian technique was used in LS-DYNA to represent the fluid. The simulation results were correlated with the test data to validate the modeling approach. Additional simulation studies were performed to determine how changes in mesh density, mesh uniformity, fluid viscosity, and failure strain influence the test-analysis correlation.

  5. Detection of Zygosaccharomyces rouxii and Candida tropicalis in a High-Sugar Medium by a Metal Oxide Sensor-Based Electronic Nose and Comparison with Test Panel Evaluation.

    Science.gov (United States)

    Wang, Huxuan; Hu, Zhongqiu; Long, Fangyu; Guo, Chunfeng; Yuan, Yahong; Yue, Tianli

    2015-11-01

    Osmotolerant yeasts are primarily responsible for spoilage of sugar-rich foods. In this work, an electronic nose (e-nose) was used to diagnose contamination caused by two osmotolerant yeast strains (Zygosaccharomyces rouxii and Candida tropicalis) in a high-sugar medium using test panel evaluation as the reference method. Solid-phase microextraction gas chromatography with mass spectrometry (GC-MS) was used to determine the evolution of the volatile organic compound fingerprint in the contaminated samples during yeast growth. Principal component analysis and linear discriminant analysis revealed that the e-nose could identify contamination after 48 h, corresponding to the total yeast levels of 3.68 (Z. rouxii) and 3.09 (C. tropicalis) log CFU/ml. At these levels, the test panel could not yet diagnose the spoilage, indicating that the e-nose approach was more sensitive than the test panel evaluation. Loading analysis indicated that sensors 8 and 6 were the most important for detection of these two yeasts. Based on the result obtained with the e-nose, the incubation time and total yeast levels could be accurately predicted by established multiple regression models with a correlation of greater than 0.97. In the sensory evaluation, spoilage was diagnosed after 72 h in samples contaminated with C. tropicalis and after 48 to 72 h for samples contaminated with Z. rouxii. GC-MS revealed that compounds such as acetaldehyde, acetone, ethyl acetate, alcohol, and 3-methyl-1-butanol contributed to spoilage detection by the e-nose after 48 h. In the high-sugar medium, the e-nose was more sensitive than the test panel evaluation for detecting contamination with these test yeast strains. This information could be useful for developing instruments and techniques for rapid scanning of sugar-rich foods for contamination with osmotolerant yeasts before such spoilage could be detected by the consumer.

  6. Analysis of the Space Shuttle Orbiter skin panels under simulated hydrodynamic loads

    Science.gov (United States)

    Carden, Huey D.; Fasanella, Edwin L.; Jones, Lisa E.

    1988-01-01

    The Space Shuttle orbiter skin panels were analyzed under pressure loads simulating hydrodynamic loads to determine their capability to sustain a potential ditching and to determine pressures that typically would produce failures. Two Dynamic Crash Analysis of Structures (DYCAST) finite element models were used. One model was used to represent skin panels (bays) in the center body, while a second model was used to analyze a fuselage bay in the wing region of the orbiter. From an assessment of the DYCAST nonlinear computer results, it is concluded that the probability is extremely high that most, if not all, of the lower skin panels would rupture under ditching conditions. Extremely high pressure loads which are produced under hydrodynamic planning conditions far exceed the very low predicted failure pressures for the skin panels. Consequently, a ditching of the orbiter is not considered to have a high probability of success and should not be considered a means of emergency landing unless no other option exists.

  7. Numerical assessment of failure mechanisms in fibre metal laminates

    NARCIS (Netherlands)

    Hashagen, F.; De Borst, R.

    1998-01-01

    In this contribution numerical models are discussed for describing failure mechanisms in fibre metal laminates. Fibre metal laminates form a new class of materials which are considered for a possible application to the fuselage of future aircraft generations. The intensive experimental analyses of t

  8. The High Combustion Efficient Analysis of a Novel Metal Honeycomb Sandwich Panel Combustor%新型金属蜂窝板燃烧器的高效燃烧现象分析

    Institute of Scientific and Technical Information of China (English)

    张鸿声; 朱冬生; 蓝少健

    2011-01-01

    新型金属蜂窝板燃烧器是通过采用双层或多层金属薄片制成,能有效地解决普通燃气灶具燃烧器存在的不足,使产品结构更加合理完善,性能更加稳定可靠,能效更加优越。本文以红外燃气灶具的核心部件—新型金属蜂窝板燃烧器为研究对象,利用红外摄像仪对红外燃气灶具和普通燃气灶具进行了对比研究。结果表明,红外燃气灶的火焰集中,温度分布均匀,燃烧效率比普通燃气灶高12.7%。%A novel metal honeycomb sandwich panel combustor is made of multi-layer sheet metals. It can solve the problems effectively that the atmospheric gas range have,make the products more reasonable,stable and effective.In this paper,we study on the performances of an infrared gas range which is made from the novel metal honeycomb sandwich panel combustor.Using the infrared video camera to comparatively study the performances of the infrared gas range and the atmospheric gas range.The results show that the flame and temperature distribution of the infrared gas range is dense and homogeneous.The combustion efficiency of the infrared gas range is 12.7%higher than the atmospheric gas range.

  9. Research of the punch interaction with composite protective panel

    OpenAIRE

    Kulakov, N.; Lyubin, A.

    2008-01-01

    The work examines the structure of a protection composite panel consisting of a crushing layer (ceramic discrete elements of a cylindrical shape) and a restraining layer below (metallic leaf). This protection panel can be used for an armour-piercing bullet protection of the car. Here is the strength calculation of ceramic elements and metallic protective layer dynamic interaction under bullet impact. The problem was solved under a variety of protection panel parameters in order to define thei...

  10. Nonlinear Analysis and Post-Test Correlation for a Curved PRSEUS Panel

    Science.gov (United States)

    Gould, Kevin; Lovejoy, Andrew E.; Jegley, Dawn; Neal, Albert L.; Linton, Kim, A.; Bergan, Andrew C.; Bakuckas, John G., Jr.

    2013-01-01

    The Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) concept, developed by The Boeing Company, has been extensively studied as part of the National Aeronautics and Space Administration's (NASA s) Environmentally Responsible Aviation (ERA) Program. The PRSEUS concept provides a light-weight alternative to aluminum or traditional composite design concepts and is applicable to traditional-shaped fuselage barrels and wings, as well as advanced configurations such as a hybrid wing body or truss braced wings. Therefore, NASA, the Federal Aviation Administration (FAA) and The Boeing Company partnered in an effort to assess the performance and damage arrestments capabilities of a PRSEUS concept panel using a full-scale curved panel in the FAA Full-Scale Aircraft Structural Test Evaluation and Research (FASTER) facility. Testing was conducted in the FASTER facility by subjecting the panel to axial tension loads applied to the ends of the panel, internal pressure, and combined axial tension and internal pressure loadings. Additionally, reactive hoop loads were applied to the skin and frames of the panel along its edges. The panel successfully supported the required design loads in the pristine condition and with a severed stiffener. The panel also demonstrated that the PRSEUS concept could arrest the progression of damage including crack arrestment and crack turning. This paper presents the nonlinear post-test analysis and correlation with test results for the curved PRSEUS panel. It is shown that nonlinear analysis can accurately calculate the behavior of a PRSEUS panel under tension, pressure and combined loading conditions.

  11. Investigation on Stake Welding Method of T-joints for Metal Sandwich Panel%金属夹芯结构制造中的T型接头Stake焊接方法研究

    Institute of Scientific and Technical Information of China (English)

    谷侃锋; 魏强; 赵明扬

    2012-01-01

    The Stake welding method of T-joints is a critical technology for making metal sandwich panels. In order to demonstrate the feasibility of making metal sandwich panels with welding method, three welding methods, including laser welding, gas tungsten arc (TIG) welding, and laser-TIG hybrid welding with cold welding wire, were investigated experimentally on Stake welding method of titanium alloy thin sheet T-joints. The weld forming properties of the T-joints and some affecting factors were analyzed under this three welding methods. The results show that the laser-TIG hybrid welding with cold welding wire method is an ideal technical for the Stake welding method of T-joints for making metal sandwich panels, which has more advantages than the laser welding method and the gas tungsten arc(TIG) welding method in the microstructure of welded joint, efficiency of welding, weld shaping and adaptability of weld gap.%T型接头的Stake焊接方法是实现金属夹芯板焊接制造的关键技术之一.为了论证焊接制造金属夹芯板的可行性,本文通过实验对比研究了在单一激光、TIG电弧和激光-TIG电弧复合等三种焊接工艺下,钛合金薄板T型接头Stake焊接焊缝成形特点及影响因素.结果表明,激光-TIG电弧焊是实现钛合金薄板T型接头Stake焊接的理想工艺,在焊缝组织、焊接效率、焊缝成形、间隙适应性等方面比单一激光或TIG焊接工艺有明显的优势,可以应用于金属夹芯板的焊接制造.

  12. Implementation and verification of a comprehensive helicopter coupled rotor - Fuselage analysis

    Science.gov (United States)

    Wood, E. R.; Banerjee, D.; Shamie, J.; Straub, F.; Dinyavari, M. A. H.

    1985-01-01

    The analytical basis and the application of a Rotor/Airframe Comprehensive Aeroelastic Program (RACAP) are described in detail. The rationale behind each analytical choice is outlined and the modular procedure is described. The program is verified by application to the AH-1G helicopter. The applicability of various airload prediction models is examined, and both the steady and vibratory responses of the blade are compared with flight test data. Reasonable correlation is found between measured and calculated blade response, with excellent correlation for vibration amplitudes at various locations on the fuselage such as engine, pilot seat, and gunner. Within the analytical model, comparisons are drawn between an isolated blade analysis and a coupled rotor/fuselage model. The deficiency of the former in the context of the AH-1G is highlighted.

  13. Mechanical and analytical screening of braided composites for transport fuselage applications

    Science.gov (United States)

    Fedro, Mark J.; Gunther, Christian; Ko, Frank K.

    1991-01-01

    The mechanics of materials progress in support of the goal of understanding the application of braided composites in a transport aircraft fuselage are summarized. Composites consisting of both 2-D and 3-D braid patterns are investigated. Both consolidation of commingled graphite/PEEK and resin transfer molding of graphite-epoxy braided composite processes are studied. Mechanical tests were used to examine unnotched tension, open hole tension, compression, compression after impact, in-plane shear, out-of-plane tension, bearing, and crippling. Analytical methods are also developed and applied to predict the stiffness and strengths of test specimens. A preliminary study using the test data and analytical results is performed to assess the applicability of braided composites to a commercial aircraft fuselage.

  14. Automatic computation of Euler-marching and subsonic grids for wing-fuselage configurations

    Science.gov (United States)

    Barger, Raymond L.; Adams, Mary S.; Krishnan, Ramki R.

    1994-01-01

    Algebraic procedures are described for the automatic generation of structured, single-block flow computation grids for relatively simple configurations (wing, fuselage, and fin). For supersonic flows, a quasi two-dimensional grid for Euler-marching codes is developed, and some sample results in graphical form are included. A type of grid for subsonic flow calculation is also described. The techniques are algebraic and are based on a generalization of the method of transfinite interpolation.

  15. Parametric Fuselage Geometry Generation and Aerodynamic Performance Prediction in Preliminary Rotorcraft Design

    OpenAIRE

    Kunze, Philipp

    2013-01-01

    The creation of an integrated rotorcraft conceptual and preliminary design framework at DLR involved the development of geometry and fuselage aerodynamics modules at the Institute of Aerodynamics and Flow Technology. After a short revision of the RIDE rotorcraft design environment architecture this paper focuses on the implementation of these disciplinary modules. The aim of the geometry module is to bridge the gap between conceptual and preliminary design and to allow for geometry parameter ...

  16. Coupled rotor/fuselage dynamic analysis of the AH-1G helicopter and correlation with flight vibrations data

    Science.gov (United States)

    Corrigan, J. C.; Cronkhite, J. D.; Dompka, R. V.; Perry, K. S.; Rogers, J. P.; Sadler, S. G.

    1989-01-01

    Under a research program designated Design Analysis Methods for VIBrationS (DAMVIBS), existing analytical methods are used for calculating coupled rotor-fuselage vibrations of the AH-1G helicopter for correlation with flight test data from an AH-1G Operational Load Survey (OLS) test program. The analytical representation of the fuselage structure is based on a NASTRAN finite element model (FEM), which has been developed, extensively documented, and correlated with ground vibration test. One procedure that was used for predicting coupled rotor-fuselage vibrations using the advanced Rotorcraft Flight Simulation Program C81 and NASTRAN is summarized. Detailed descriptions of the analytical formulation of rotor dynamics equations, fuselage dynamic equations, coupling between the rotor and fuselage, and solutions to the total system of equations in C81 are included. Analytical predictions of hub shears for main rotor harmonics 2p, 4p, and 6p generated by C81 are used in conjunction with 2p OLS measured control loads and a 2p lateral tail rotor gearbox force, representing downwash impingement on the vertical fin, to excite the NASTRAN model. NASTRAN is then used to correlate with measured OLS flight test vibrations. Blade load comparisons predicted by C81 showed good agreement. In general, the fuselage vibration correlations show good agreement between anslysis and test in vibration response through 15 to 20 Hz.

  17. Application of Carbon Fibre Truss Technology to the Fuselage Structure of the SKYLON Spaceplane

    Science.gov (United States)

    Varvill, R.; Bond, A.

    A reusable SSTO spaceplane employing dual mode airbreathing/rocket engines, such as SKYLON, has a voluminous fuselage in order to accommodate the considerable quantities of hydrogen fuel needed for the ascent. The loading intensity which this fuselage has to withstand is relatively low due to the modest in-flight inertial accelerations coupled with the very low density of liquid hydrogen. Also the requirement to accommo- date considerable temperature differentials between the internal cryogenic tankage and the aerodynamically heated outer skin of the vehicle imposes an additional design constraint that results in an optimum fuselage structural concept very different to conventional aircraft or rocket practice. Several different structural con- cepts exist for the primary loadbearing structure. This paper explores the design possibilities of the various types and explains why an independent near ambient temperature CFRP truss structure was selected for the SKYLON vehicle. The construction of such a truss structure, at a scale not witnessed since the days of the airship, poses a number of manufacturing and design difficulties. In particular the construction of the nodes and their attachment to the struts is considered to be a key issue. This paper describes the current design status of the overall truss geometry, strut construction and manufacturing route, and the final method of assembly. The results of a preliminary strut and node test programme are presented which give confidence that the design targets will eventually be met.

  18. Development of a plasma panel radiation detector

    CERN Document Server

    Ball, R; Ben-Moshe, M; Benhammou, Y; Bensimon, R; Chapman, J W; Etzion, E; Ferretti, C; Friedman, P S; Levin, D S; Silver, Y; Varner, R L; Weaverdyck, C; Wetzel, R; Zhou, B; Anderson, T; McKinny, K; Bentefour, E H

    2014-01-01

    This article reports on an investigation of a radiation detector based on plasma display panel technology. The plasma panel sensor (PPS) is a variant of micropattern gas radiation detectors. PPS components are non-reactive and intrinsically radiation-hard materials, such as glass substrates, metal electrodes and inert gas mixtures. Plasma display panels used as detectors were tested with cosmic ray muons, beta rays and gamma rays, protons, and thermal neutrons. The results demonstrated risetimes and time resolution of a few nanoseconds, as well as spatial resolution compatible with the pixel pitch.

  19. Thin Film Photovoltaic/Thermal Solar Panels

    Institute of Scientific and Technical Information of China (English)

    David JOHNSTON

    2008-01-01

    A solar panel is described.in which thin films of semiconductor are deposited onto a metal substrate.The semiconductor-metal combination forms a thin film photovoltaic cell,and also acts as a reflector,absorber tandem, which acts as a solar selective surface,thus enhancing the solar thermal performance of the collector plate.The use of thin films reduces the distance heat is required to flow from the absorbing surface to the metal plate and heat exchange conduits.Computer modelling demonstrated that,by suitable choice of materials,photovohaic efficiency call be maintained,with thermal performance slishtly reduced,compared to that for thermal-only panels.By grading the absorber layer-to reduce the band gap in the lower region-the thermal performance can be improved,approaching that for a thermal-only solar panel.

  20. Antinuclear antibody panel

    Science.gov (United States)

    ... page: //medlineplus.gov/ency/article/003535.htm Antinuclear antibody panel To use the sharing features on this page, please enable JavaScript. The antinuclear antibody panel is a blood test that looks at ...

  1. Hepatitis virus panel

    Science.gov (United States)

    ... page: //medlineplus.gov/ency/article/003558.htm Hepatitis virus panel To use the sharing features on this page, please enable JavaScript. The hepatitis virus panel is a series of blood tests used ...

  2. Hepatic (Liver) Function Panel

    Science.gov (United States)

    ... 1- to 2-Year-Old Blood Test: Hepatic (Liver) Function Panel KidsHealth > For Parents > Blood Test: Hepatic (Liver) Function Panel Print A A A What's in ... Is The hepatic function panel, also known as liver function tests, is a group of seven tests ...

  3. TRMM Solar Array Panels

    Science.gov (United States)

    1998-01-01

    This final report presents conclusions/recommendations concerning the TRMM Solar Array; deliverable list and schedule summary; waivers and deviations; as-shipped performance data, including flight panel verification matrix, panel output detail, shadow test summary, humidity test summary, reverse bias test panel; and finally, quality assurance summary.

  4. A nonlinear analysis of infinitely long graphite-epoxy cylindrical panels loaded with internal pressure

    Science.gov (United States)

    Boitnott, R. L.; Johnson, E. R.; Starnes, J. H., Jr.

    1985-01-01

    The structural response of internally pressurized composite cylindrical panels, representative of a transport aircraft's fuselage skins, is predicted by means of a one-dimensional, geometrically nonlinear analysis. An analytical study is conducted for the response of 4-, 8-, and 16-ply graphite/epoxy skins. The results obtained indicate that the response is geometrically nonlinear, and that a boundary layer with a severe bending gradient exists at the panel edges. The importance of through-the-thickness shearing deformations in the bending boundary layer is illustrated through comparison of analyses based on Kirchhoff-Love and shear deformation theories. Numerical results for the bending boundary layer lengths of the different panels are presented, and two bending boundary layers are predicted with the shear deformation theory.

  5. THE THERMOELECTRIC SOLAR PANELS

    Directory of Open Access Journals (Sweden)

    R. Ahiska

    2016-07-01

    Full Text Available In this study, load characteristics of thermoelectric and photovoltaic solar panels are investigated and compared with each other with experiments. Thermoelectric solar panels converts the heat generated by sun directly to electricity; while, photovoltaic solar pales converts photonic energy from sun to electricity. In both types, maximum power can be obtained when the load resistance is equal to internal resistance. According to experimental results, power generated from unit surface with thermoelectric panel is 30 times greater than the power generated by photovoltaic panel. From a panel surface of 1 m2, thermoelectric solar panel has generated 4 kW electric power, while from the same surface, photovoltaic panel has generated 132 W only.

  6. A study of coupled rotor-fuselage vibration with higher harmonic control using a symbolic computing facility

    Science.gov (United States)

    Papavassiliou, I.; Venkatesan, C.; Friedmann, P. P.

    1990-01-01

    A fundamental study of vibration prediction and vibration reduction in helicopters using active controls was performed. The nonlinear equations of motion for a coupled rotor/flexible fuselage system have been derived using computer algebra on a special purpose symbolic computing facility. The details of the derivation using the MACSYMA program are described. The trim state and vibratory response of the helicopter are obtained in a single pass by applying the harmonic balance technique and simultaneously satisfying the trim and the vibratory response of the helicopter for all rotor and fuselage degrees of freedom. The influence of the fuselage flexibility on the vibratory response is studied. It is shown that the conventional single frequency higher harmonic control (HHC) capable of reducing either the hub loads or only the fuselage vibrations but not both simultaneously. It is demonstrated that for simultaneous reduction of hub shears and fuselage vibrations a new scheme called multiple higher harmonic control (MHHC) is required. The fundamental aspects of this scheme and its uniqueness are described in detail, providing new insight on vibration reduction in helicopters using HHC.

  7. Paneling architectural freeform surfaces

    KAUST Repository

    Eigensatz, Michael

    2010-07-26

    The emergence of large-scale freeform shapes in architecture poses big challenges to the fabrication of such structures. A key problem is the approximation of the design surface by a union of patches, socalled panels, that can be manufactured with a selected technology at reasonable cost, while meeting the design intent and achieving the desired aesthetic quality of panel layout and surface smoothness. The production of curved panels is mostly based on molds. Since the cost of mold fabrication often dominates the panel cost, there is strong incentive to use the same mold for multiple panels. We cast the major practical requirements for architectural surface paneling, including mold reuse, into a global optimization framework that interleaves discrete and continuous optimization steps to minimize production cost while meeting user-specified quality constraints. The search space for optimization is mainly generated through controlled deviation from the design surface and tolerances on positional and normal continuity between neighboring panels. A novel 6-dimensional metric space allows us to quickly compute approximate inter-panel distances, which dramatically improves the performance of the optimization and enables the handling of complex arrangements with thousands of panels. The practical relevance of our system is demonstrated by paneling solutions for real, cutting-edge architectural freeform design projects. © 2010 ACM.

  8. Paneling architectural freeform surfaces

    KAUST Repository

    Eigensatz, Michael

    2010-07-25

    The emergence of large-scale freeform shapes in architecture poses big challenges to the fabrication of such structures. A key problem is the approximation of the design surface by a union of patches, so-called panels, that can be manufactured with a selected technology at reasonable cost, while meeting the design intent and achieving the desired aesthetic quality of panel layout and surface smoothness. The production of curved panels is mostly based on molds. Since the cost of mold fabrication often dominates the panel cost, there is strong incentive to use the same mold for multiple panels. We cast the major practical requirements for architectural surface paneling, including mold reuse, into a global optimization framework that interleaves discrete and continuous optimization steps to minimize production cost while meeting user-specified quality constraints. The search space for optimization is mainly generated through controlled deviation from the design surface and tolerances on positional and normal continuity between neighboring panels. A novel 6-dimensional metric space allows us to quickly compute approximate inter-panel distances, which dramatically improves the performance of the optimization and enables the handling of complex arrangements with thousands of panels. The practical relevance of our system is demonstrated by paneling solutions for real, cutting-edge architectural freeform design projects.

  9. Drop test and crash simulation of a civil airplane fuselage section

    Directory of Open Access Journals (Sweden)

    Liu Xiaochuan

    2015-04-01

    Full Text Available Crashworthiness of a civil airplane fuselage section was studied in this paper. Firstly, the failure criterion of a rivet was studied by test, showing that the ultimate tension and shear failure loads were obviously affected by the loading speed. The relations between the loading speed and the average ultimate shear, tension loads were expressed by two logarithmic functions. Then, a vertical drop test of a civil airplane fuselage section was conducted with an actual impact velocity of 6.85 m/s, meanwhile the deformation of cabin frame and the accelerations at typical locations were measured. The finite element model of a main fuselage structure was developed and validated by modal test, and the error between the calculated frequencies and the test ones of the first four modes were less than 5%. Numerical simulation of the drop test was performed by using the LS-DYNA code and the simulation results show a good agreement with that of drop test. Deforming mode of the analysis was the same as the drop test; the maximum average rigid acceleration in test was 8.81g while the calculated one was 9.17g, with an error of 4.1%; average maximum test deformation at four points on the front cabin floor was 420 mm, while the calculated one was 406 mm, with an error of 3.2%; the peak value of the calculated acceleration at a typical location was 14.72g, which is lower than the test result by 5.46%; the calculated rebound velocity result was greater than the test result 17.8% and energy absorption duration was longer than the test result by 5.73%.

  10. Plasma panel-based radiation detectors

    CERN Document Server

    Friedman, Peter; Beene, James; Benhammou, Yan; Ben-Moshe, Meny; Bentefour, Hassan; Chapman, J W; Etzion, Erez; Ferretti, Claudio; Levin, Daniel; Silver, Yiftah; Varner, Robert; Weaverdyck, Curtis; Zhou, Bing; 10.1002/jsid.151

    2013-01-01

    The plasma panel sensor (PPS) is a gaseous micropattern radiation detector under current development. It has many operational and fabrication principles common to plasma display panels. It comprises a dense matrix of small, gas plasma discharge cells within a hermetically sealed panel. As in plasma display panels, it uses nonreactive, intrinsically radiation-hard materials such as glass substrates, refractory metal electrodes, and mostly inert gas mixtures. We are developing these devices primarily as thin, low-mass detectors with gas gaps from a few hundred microns to a few millimeters. The PPS is a high gain, inherently digital device with the potential for fast response times, fine position resolution (<50-mm RMS) and low cost. In this paper, we report on prototype PPS experimental results in detecting betas, protons, and cosmic muons, and we extrapolate on the PPS potential for applications including the detection of alphas, heavy ions at low-to-medium energy, thermal neutrons, and X-rays.

  11. Experimental and analytical study of the effects of floor location on response of composite fuselage frames

    Science.gov (United States)

    Jones, Lisa E.; Robinson, Martha; Fasanella, Edwin L.; Boitnott, Richard L.

    1992-01-01

    Experimental and analytical results are presented of the effects of floor placement on the structural response and strength of I-cross section, semi-circular fuselage frames constructed of graphite-epoxy composite material. The composite frame configuration is representative of current conventional aircraft design. Experimental strain distributions are presented from static loading tests of the composite frames and compared with finite element structural models and closed form solutions. An understanding of floor location effects can aid dynamists in predicting the crash behavior of these conventional structures, and may assist the designer in developing crashworthy structures for future aircraft.

  12. Titanium honeycomb panel testing

    Science.gov (United States)

    Richards, W. L.; Thompson, Randolph C.

    The paper describes the procedures of thermal mechanical tests carried out at the NASA Dryden Flight Research Facility on two tianium honeycomb wing panels bonded using liquid interface diffusion (LID) technique, and presents the results of these tests. The 58.4 cm square panels consisted of two 0.152-cm-thick Ti 6-2-4-2 face sheets LID-bonded to a 1.9-cm-thick honeycomb core, with bearing plates fastened to the perimeter of the upper and the lower panel surfaces. The panels were instrumented with sensors for measuring surface temperature, strain, and deflections to 315 C and 482 C. Thermal stress levels representative of those encountered during aerodynamic heating were produced by heating the upper panel surface and restraining all four edges. After more than 100 thermal cycles from room temperature to 315 C and 50 cycles from room temperature to 482 C, no significant structural degradation was detected in the panels.

  13. REINFORCED COMPOSITE PANEL

    DEFF Research Database (Denmark)

    2003-01-01

    A composite panel having front and back faces, the panel comprising facing reinforcement, backing reinforcement and matrix material binding to the facing and backing reinforcements, the facing and backing reinforcements each independently comprising one or more reinforcing sheets, the facing...... by matrix material, the facing and backing reinforcements being interconnected to resist out-of-plane relative movement. The reinforced composite panel is useful as a barrier element for shielding structures, equipment and personnel from blast and/or ballistic impact damage....

  14. REINFORCED COMPOSITE PANEL

    DEFF Research Database (Denmark)

    2003-01-01

    A composite panel having front and back faces, the panel comprising facing reinforcement, backing reinforcement and matrix material binding to the facing and backing reinforcements, the facing and backing reinforcements each independently comprising one or more reinforcing sheets, the facing rein...... by matrix material, the facing and backing reinforcements being interconnected to resist out-of-plane relative movement. The reinforced composite panel is useful as a barrier element for shielding structures, equipment and personnel from blast and/or ballistic impact damage....

  15. Impact Testing and Simulation of a Crashworthy Composite Fuselage Section with Energy-Absorbing Seats and Dummies

    Science.gov (United States)

    Fasanella, Edwin L.; Jackson, Karen E.

    2002-01-01

    A 25-ft/s vertical drop test of a composite fuselage section was conducted with two energy-absorbing seats occupied by anthropomorphic dummies to evaluate the crashworthy features of the fuselage section and to determine its interaction with the seats and dummies. The 5-ft diameter fuselage section consists of a stiff structural floor and an energy-absorbing subfloor constructed of Rohacel foam blocks. The experimental data from this test were analyzed and correlated with predictions from a crash simulation developed using the nonlinear, explicit transient dynamic computer code, MSC.Dytran. The anthropomorphic dummies were simulated using the Articulated Total Body (ATB) code, which is integrated into MSC.Dytran.

  16. Optimized grid design for thin film solar panels

    NARCIS (Netherlands)

    Deelen, J. van; Klerk, L.; Barink, M.

    2014-01-01

    There is a gap in efficiency between record thin film cells and mass produced thin film solar panels. In this paper we quantify the effect of monolithic integration on power output for various configurations by modeling and present metallization as a way to improve efficiency of solar panels. Grid d

  17. Effect of winglets on a first-generation jet transport wing. 5: Stability characteristics of a full-span wing with a generalized fuselage at high subsonic speeds

    Science.gov (United States)

    Jacobs, P. F.

    1978-01-01

    The effects of winglets on the static aerodynamic stability characteristics of a KC-135A jet transport model at high subsonic speeds are presented. The investigation was conducted in the Langley 8 foot transonic pressure tunnel using 0.035-scale wing panels mounted on a generalized research fuselage. Data were taken over a Mach number range from 0.50 to 0.95 at angles of attack ranging from -12 deg to 20 deg and sideslip angles of 0 deg, 5 deg, and -5 deg. The model was tested at two Reynolds number ranges to achieve a wide angle of attack range and to determine the effect of Reynolds number on stability. Results indicate that adding the winglets to the basic wing configuration produces small increases in both lateral and longitudinal aerodynamic stability and that the model stability increases slightly with Reynolds number. The winglets do increase the wing bending moments slightly, but the buffet onset characteristics of the model are not affected by the winglets.

  18. Structural Analysis of Sandwich Foam Panels

    Energy Technology Data Exchange (ETDEWEB)

    Kosny, Jan [ORNL; Huo, X. Sharon [Tennessee Technological University

    2010-04-01

    The Sandwich Panel Technologies including Structural Insulated Panels (SIPs) can be used to replace the conventional wooden-frame construction method. The main purpose of this Cooperative Research and Development Agreement (CRADA) between UT-Battelle, LLC and SGI Venture, Inc. was to design a novel high R-value type of metal sandwich panelized technology. This CRADA project report presents design concept discussion and numerical analysis results from thermal performance study of this new building envelope system. The main objective of this work was to develop a basic concept of a new generation of wall panel technologies which will have R-value over R-20 will use thermal mass to improve energy performance in cooling dominated climates and will be 100% termite resistant. The main advantages of using sandwich panels are as follows: (1) better energy saving structural panels with high and uniform overall wall R-value across the elevation that could not be achieved in traditional walls; and (2) reducing the use of raw materials or need for virgin lumber. For better utilization of these Sandwich panels, engineers need to have a thorough understanding of the actual performance of the panels and system. Detailed analysis and study on the capacities and deformation of individual panels and its assembly have to be performed to achieve that goal. The major project activity was to conduct structural analysis of the stresses, strains, load capacities, and deformations of individual sandwich components under various load cases. The analysis simulated the actual loading conditions of the regular residential building and used actual material properties of the steel facings and foam.

  19. A three-dimensional, compressible, laminar boundary-layer method for general fuselages. Volume 1: Numerical method

    Science.gov (United States)

    Wie, Yong-Sun

    1990-01-01

    A procedure for calculating 3-D, compressible laminar boundary layer flow on general fuselage shapes is described. The boundary layer solutions can be obtained in either nonorthogonal 'body oriented' coordinates or orthogonal streamline coordinates. The numerical procedure is 'second order' accurate, efficient and independent of the cross flow velocity direction. Numerical results are presented for several test cases, including a sharp cone, an ellipsoid of revolution, and a general aircraft fuselage at angle of attack. Comparisons are made between numerical results obtained using nonorthogonal curvilinear 'body oriented' coordinates and streamline coordinates.

  20. A methodology for computing nonlinear fracture parameters for a bulging crack in a pressurised aircraft fuselage

    Science.gov (United States)

    Shenoy, V. B.; Potyondy, D. O.; Atluri, S. N.

    1994-09-01

    A computational methodology for obtaining nonlinear fracture parameters which account for the effects of plasticity at the tips of a bulging crack in a pressurised aircraft fuselage is developed. The methodology involves a hierarchical three stage analysis (global, intermediate, and local) of the cracked fuselage, with the crack incorporated into the model at each stage. The global analysis is performed using a linear elastic shell finite element model in which the stiffeners are treated as beam elements. The geometrically nonlinear nature of the bulging phenomenon is emulated in the intermediate analysis using a geometrically nonlinear shell finite element model. The local analysis is a three-dimensional solid finite element model of the cracked skin using a hypoelastic-plastic rate formulation. Kinematic boundary conditions for each stage are obtained from the preceding stage in the hierarchy using a general mesh independent mechanism. The T *integral, which accounts for both large deformations and plasticity, is taken to be the fracture parameter characterising the severity of the conditions at the crack tip, and is evaluated from the local analysis using the Equivalent Domain Integral (EDI) method. The implementation of the EDI technique for finite deformations in shell space is also outlined. The methodology is applied to a number of example problems for which correction factors relating the nonlinear T * values to those obtained from a linear elastic stiffened shell analysis are computed. The issue of flapping is addressed by investigating the behaviour of the longitudinal stress parallel to the crack for various cases.

  1. Optimization of Blended Wing Body Composite Panels Using Both NASTRAN and Genetic Algorithm

    Science.gov (United States)

    Lovejoy, Andrew E.

    2006-01-01

    The blended wing body (BWB) is a concept that has been investigated for improving the performance of transport aircraft. A trade study was conducted by evaluating four regions from a BWB design characterized by three fuselage bays and a 400,000 lb. gross take-off weight (GTW). This report describes the structural optimization of these regions via computational analysis and compares them to the baseline designs of the same construction. The identified regions were simplified for use in the optimization. The regions were represented by flat panels having appropriate classical boundary conditions and uniform force resultants along the panel edges. Panel-edge tractions and internal pressure values applied during the study were those determined by nonlinear NASTRAN analyses. Only one load case was considered in the optimization analysis for each panel region. Optimization was accomplished using both NASTRAN solution 200 and Genetic Algorithm (GA), with constraints imposed on stress, buckling, and minimum thicknesses. The NASTRAN optimization analyses often resulted in infeasible solutions due to violation of the constraints, whereas the GA enforced satisfaction of the constraints and, therefore, always ensured a feasible solution. However, both optimization methods encountered difficulties when the number of design variables was increased. In general, the optimized panels weighed less than the comparable baseline panels.

  2. 钢蒙皮-复合材料芯材夹层板弯曲性能研究%Research on Bending Properties of Metal Faced-composite Core Sandwich Panel

    Institute of Scientific and Technical Information of China (English)

    王跃; 方海; 刘伟庆

    2015-01-01

    Sandwich structure consisting of steel and glass fiber reinforced composite (GFRP) core pultruded hollow square tube was proposed .Bending experiment of metal faced‐composite core sandwich beam through using four‐point bending test method was carried out .The distribution of strain ,the mid‐span deflections and the ultimate failure of the slab w ere analyzed .T he effective bending stiffness of metal faced‐composite core sandwich panel was deduced by transformed section method ,and the mid‐span displacement computational formula was deduced by mechanics of materials theory .The mid‐span deflections of samples were calculated .The theory results and test results were compared and they fitted well .The study results show that when the thickness of the core is constant , the mid‐span deflection decreases with increasing thickness of metal f aced .%采用钢板蒙皮与玻璃纤维增强复合材料(GFRP)拉挤成型的空心方管芯材组成夹层结构,运用四点弯曲试验方法,开展了钢蒙皮‐复合材料芯材夹层梁的受弯性能试验,研究了其受力性能情况、跨中上下面板应力分布和跨中挠度。运用换算截面法推导出钢蒙皮‐复合材料芯材夹层板截面有效抗弯刚度,并采用材料力学理论推导出夹层板跨中挠度计算公式,计算各试件的跨中上下面板应力分布情况和跨中挠度。研究结果表明:当芯材厚度一致时,试件的跨中挠度随着钢板面层厚度的增加而逐渐减小;跨中挠度理论值与试验值吻合较好。

  3. Calculation of the rotor-fuselage interaction using the resolution of Euler equations; Calcul de l'interaction rotor-fuselage par resolution des equations d'Euler

    Energy Technology Data Exchange (ETDEWEB)

    Bettschart, N.

    1998-07-01

    This paper presents the recent developments made at ONERA for the prediction of helicopter rotor-fuselage aerodynamic interactions. An actuator disk model has been implemented in the FLU3M code. Applications on isolated rotors as well as complete helicopter are performed using the Euler option of the code. The numerical results are compared with theoretical and experimental results. (author)

  4. Calculation of the rotor-fuselage interaction using the resolution of Euler equations; Calcul de l'interaction rotor-fuselage par resolution des equations d'Euler

    Energy Technology Data Exchange (ETDEWEB)

    Bettschart, N.

    1998-07-01

    This paper presents the recent developments made at ONERA for the prediction of helicopter rotor-fuselage aerodynamic interactions. An actuator disk model has been implemented in the FLU3M code. Applications on isolated rotors as well as complete helicopter are performed using the Euler option of the code. The numerical results are compared with theoretical and experimental results. (author)

  5. Transonic Aerodynamic Characteristics of a 45 deg Swept Wing Fuselage Model with a Finned and Unfinned Body Pylon Mounted Beneath the Fuselage or Wing, Including Measurements of Body Loads

    Science.gov (United States)

    Wornom, Dewey E.

    1959-01-01

    An investigation of a model of a standard size body in combination with a representative 45 deg swept-wing-fuselage model has been conducted in the Langley 8-foot transonic pressure tunnel over a Mach number range from 0.80 to 1.43. The body, with a fineness ratio of 8.5, was tested with and without fins, and was pylon-mounted beneath the fuselage or wing. Force measurements were obtained on the wing-fuselage model with and without the body, for an angle-of-attack range from -2 deg to approximately 12 deg and an angle-of-sideslip range from -8 deg to 8 deg. In addition, body loads were measured over the same angle-of-attack and angle-of-sideslip range. The Reynolds number for the investigation, based on the wing mean aerodynamic chord, varied from 1.85 x 10(exp 6) to 2.85 x 10(exp 6). The addition of the body beneath the fuselage or the wing increased the drag coefficient of the complete model over the Mach number range tested. On the basis of the drag increase per body, the under-fuselage position was the more favorable. Furthermore, the bodies tended to increase the lateral stability of the complete model. The variation of body loads with angle of attack for the unfinned bodies was generally small and linear over the Mach number range tested with the addition of fins causing large increases in the rates of change of normal-force coefficient and nose-down pitching-moment coefficient. The variation of body side-force coefficient with sideslip for the unfinned body beneath the fuselage was at least twice as large as the variation of this load for the unfinned body beneath the wing. The addition of fins to the body beneath either the fuselage or the wing approximately doubled the rate of change of body side-force coefficient with sideslip. Furthermore, the variation of body side-force coefficient with sideslip for the body beneath the wing was at least twice as large as the variation of this load with angle of attack.

  6. Make Your Own Solar Panel.

    Science.gov (United States)

    Suzuki, David

    1992-01-01

    Presents an activity in which students make a simulated solar panel to learn about the principles behind energy production using solar panels. Provides information about how solar panels function to produce energy. (MCO)

  7. Make Your Own Solar Panel.

    Science.gov (United States)

    Suzuki, David

    1992-01-01

    Presents an activity in which students make a simulated solar panel to learn about the principles behind energy production using solar panels. Provides information about how solar panels function to produce energy. (MCO)

  8. DEVELOPMENT AND VALIDATION OF NUMERICAL METHOD FOR STRENGTH ANALYSIS OF LATTICE COMPOSITE FUSELAGE STRUCTURES

    Directory of Open Access Journals (Sweden)

    2016-01-01

    Full Text Available Lattice composite fuselage structures are developed as an alternative to conventional composite structures based on laminated skin and stiffeners. Structure layout of lattice structures allows to realize advantages of current composite materials to a maximal extent, at the same time minimizing their main shortcomings, that allows to provide higher weight efficiency for these structures in comparison with conventional analogues.Development and creation of lattice composite structures requires development of novel methods of strength anal- ysis, as conventional methods, as a rule, are aiming to strength analysis of thin-walled elements and do not allow to get confident estimation of local strength of high-loaded unidirectional composite ribs.In the present work the method of operative strength analysis of lattice composite structure is presented, based onspecialized FE-models of unidirectional composite ribs and their intersections. In the frames of the method, every rib is modeled by a caisson structure, consisting of arbitrary number of flanges and webs, modeled by membrane finite elements. Parameters of flanges and webs are calculated automatically from the condition of stiffness characteristics equality of real rib and the model. This method allows to perform local strength analysis of high-loaded ribs of lattice structure without use of here-dimensional finite elements, that allows to shorten time of calculations and sufficiently simplify the procedure of analysis of results of calculations.For validation of the suggested method, the results of experimental investigations of full-scale prototype of shell of lattice composite fuselage section have been used. The prototype of the lattice section was manufactured in CRISM and tested in TsAGI within the frames of a number of Russian and International scientific projects. The results of validation have shown that the suggested method allows to provide high operability of strength analysis, keeping

  9. NASTRAN data generation of helicopter fuselages using interactive graphics. [preprocessor system for finite element analysis using IBM computer

    Science.gov (United States)

    Sainsbury-Carter, J. B.; Conaway, J. H.

    1973-01-01

    The development and implementation of a preprocessor system for the finite element analysis of helicopter fuselages is described. The system utilizes interactive graphics for the generation, display, and editing of NASTRAN data for fuselage models. It is operated from an IBM 2250 cathode ray tube (CRT) console driven by an IBM 370/145 computer. Real time interaction plus automatic data generation reduces the nominal 6 to 10 week time for manual generation and checking of data to a few days. The interactive graphics system consists of a series of satellite programs operated from a central NASTRAN Systems Monitor. Fuselage structural models including the outer shell and internal structure may be rapidly generated. All numbering systems are automatically assigned. Hard copy plots of the model labeled with GRID or elements ID's are also available. General purpose programs for displaying and editing NASTRAN data are included in the system. Utilization of the NASTRAN interactive graphics system has made possible the multiple finite element analysis of complex helicopter fuselage structures within design schedules.

  10. POPOVER Review Panel report

    Energy Technology Data Exchange (ETDEWEB)

    Davito, A.; Baker, C.J.; King, C.J.; Costerus, B.; Nelson, T.; Prokosch, D.; Pastrnak, J.; Grace, P.

    1996-04-10

    The POPOVER series of high explosive (HE) certification tests was conducted at the Big Explosives Experimental Facility (BEEF) in Area 4 of the Nevada Test Site (NTS). The two primary objectives of POPOVER were to certify that: (1) BEEF meets DOE requirements for explosives facilities and is safe for personnel-occupied operations during testing of large charges of conventional HE. (2) Facility structures and equipment will function as intended when subjected to the effects of these charges. After careful analysis of test results, the POPOVER Review Panel concludes that the POPOVER series met both objectives. Further details on the Review Panel`s conclusions are included in Section 7--Findings and Recommendations.

  11. Panel 4: Report of the Microbiology Panel

    Science.gov (United States)

    Barenkamp, Stephen J.; Chonmaitree, Tasnee; Hakansson, Anders P.; Heikkinen, Terho; King, Samantha; Nokso-Koivisto, Johanna; Novotny, Laura A.; Patel, Janak A.; Pettigrew, Melinda; Swords, W. Edward

    2017-01-01

    Objective To perform a comprehensive review of the literature from July 2011 until June 2015 on the virology and bacteriology of otitis media in children. Data Sources PubMed database of the National Library of Medicine. Review Methods Two subpanels comprising experts in the virology and bacteriology of otitis media were created. Each panel reviewed the relevant literature in the fields of virology and bacteriology and generated draft reviews. These initial reviews were distributed to all panel members prior to meeting together at the Post-symposium Research Conference of the 18th International Symposium on Recent Advances in Otitis Media, National Harbor, Maryland, in June 2015. A final draft was created, circulated, and approved by all panel members. Conclusions Excellent progress has been made in the past 4 years in advancing our understanding of the microbiology of otitis media. Numerous advances were made in basic laboratory studies, in animal models of otitis media, in better understanding the epidemiology of disease, and in clinical practice. Implications for Practice (1) Many viruses cause acute otitis media without bacterial coinfection, and such cases do not require antibiotic treatment. (2) When respiratory syncytial virus, metapneumovirus, and influenza virus peak in the community, practitioners can expect to see an increase in clinical otitis media cases. (3) Biomarkers that predict which children with upper respiratory tract infections will develop otitis media may be available in the future. (4) Compounds that target newly identified bacterial virulence determinants may be available as future treatment options for children with otitis media. PMID:28372529

  12. Aircraft Engine Noise Scattering by Fuselage and Wings: A Computational Approach

    Science.gov (United States)

    Stanescu, D.; Hussaini, M. Y.; Farassat, F.

    2003-01-01

    The paper presents a time-domain method for computation of sound radiation from aircraft engine sources to the far-field. The effects of nonuniform flow around the aircraft and scattering of sound by fuselage and wings are accounted for in the formulation. The approach is based on the discretization of the inviscid flow equations through a collocation form of the Discontinuous Galerkin spectral element method. An isoparametric representation of the underlying geometry is used in order to take full advantage of the spectral accuracy of the method. Large-scale computations are made possible by a parallel implementation based on message passing. Results obtained for radiation from an axisymmetric nacelle alone are compared with those obtained when the same nacelle is installed in a generic configuration, with and without a wing.

  13. STS-26 MS Hilmers during egress training at JSC's MAIL full fuselage trainer

    Science.gov (United States)

    1988-01-01

    STS-26 Discovery, Orbiter Vehicle (OV) 103, Mission Specialist (MS) David C. Hilmers, wearing a launch and entry suit (LES) and launch and entry helmet (LEH), tries out the new crew escape system (CES) inflated slide during an emergency egress training exercise in JSC's Shuttle Mockup and Integration Laboratory (MAIL) Bldg 9A. Technicians stand on either side of the slide ready to help Hilmers to his feet once he reaches the bottom. Watching from floor level at the far left is astronaut Steven R. Nagel. A second crewmember stands in the open side hatch of the Full Fuselage Trainer (FFT) awaiting his turn to slide to 'safety'. During Crew Station Review (CSR) #3, the crew donned the new (navy blue) partial pressure suits (LESs) and checked out CES slide and other CES configurations to evaluate crew equipment and procedures related to emergency egress methods and proposed crew escape options. The CES pole extends out the side hatch just above Hilmers' head.

  14. STS-26 Pilot Covey during egress training at JSC's MAIL full fuselage trainer

    Science.gov (United States)

    1988-01-01

    STS-26 Discovery, Orbiter Vehicle (OV) 103, Pilot Richard O. Covey, wearing a launch and entry suit (LES) and launch and entry helmet (LEH), slides to safety using the new crew escape system (CES) inflated slide during an emergency egress training exercise in JSC's Shuttle Mockup and Integration Laboratory (MAIL) Bldg 9A. Technicians stand on either side of the slide ready to help Covey to his feet once he reaches the bottom. The CES pole extends out the open side hatch of the Full Fuselage Trainer (FFT). During Crew Station Review (CSR) #3, the crew donned the new (navy blue) partial pressure suits (LESs) and checked out CES slide and other CES configurations to evaluate crew equipment and procedures related to emergency egress methods and proposed crew escape options.

  15. Multicyclic jet-flap control for alleviation of helicopter blade stresses and fuselage vibration

    Science.gov (United States)

    Mccloud, J. L., III; Kretz, M.

    1974-01-01

    Results of wind tunnel tests of a 12-meter-diameter rotor utilizing multicyclic jet-flap control deflection are presented. Analyses of these results are shown, and experimental transfer functions are determined by which optimal control vectors are developed. These vectors are calculated to eliminate specific harmonic bending stresses, minimize rms levels (a measure of the peak-to-peak stresses), or minimize vertical vibratory loads that would be transmitted to the fuselage. Although the specific results and the ideal control vectors presented are for a specific jet-flap driven rotor, the method employed for the analyses is applicable to similar investigations. A discussion of possible alternative methods of multicyclic control by mechanical flaps or nonpropulsive jet-flaps is presented.

  16. On sound transmission into a heavily-damped cylinder. [aircraft noise in fuselage

    Science.gov (United States)

    Koval, L. R.

    1978-01-01

    A mathematical model for the transmission of sound into a thin monocoque cylindrical shell is discussed. The model is used to evaluate an oblique plane wave incident upon a flexible thin cylindrical shell. The solution is applicable to the transmission of sound under actual flight conditions. The model is then used to determine curves of cylinder-transmission loss for heavily damped cylinders. Numerical results are found for several plane-wave incidence angles for a narrow-bodied jet fuselage made of aluminum. It is noted that damping (i.e., the loss factor) increases, dips because of reduced cylinder resonances, and eventually disappears when the loss factor of the shell is large enough.

  17. Fuselage Boundary Layer Ingestion Propulsion Applied to a Thin Haul Commuter Aircraft for Optimal Efficiency

    Science.gov (United States)

    Mikic, Gregor Veble; Stoll, Alex; Bevirt, JoeBen; Grah, Rok; Moore, Mark D.

    2016-01-01

    Theoretical and numerical aspects of aerodynamic efficiency of propulsion systems are studied. Focus is on types of propulsion that closely couples to the aerodynamics of the complete vehicle. We discuss the effects of local flow fields, which are affected both by conservative flow acceleration as well as total pressure losses, on the efficiency of boundary layer immersed propulsion devices. We introduce the concept of a boundary layer retardation turbine that helps reduce skin friction over the fuselage. We numerically investigate efficiency gains offered by boundary layer and wake interacting devices. We discuss the results in terms of a total energy consumption framework and show that efficiency gains offered depend on all the elements of the propulsion system.

  18. Conceptual Design of a Single-Aisle Turboelectric Commercial Transport With Fuselage Boundary Layer Ingestion

    Science.gov (United States)

    Welstead, Jason R.; Felder, James L.

    2016-01-01

    A single-aisle commercial transport concept with a turboelectric propulsion system architecture was developed assuming entry into service in 2035 and compared to a similar technology conventional configuration. The turboelectric architecture consisted of two underwing turbofans with generators extracting power from the fan shaft and sending it to a rear fuselage, axisymmetric, boundary layer ingesting fan. Results indicate that the turbo- electric concept has an economic mission fuel burn reduction of 7%, and a design mission fuel burn reduction of 12% compared to the conventional configuration. An exploration of the design space was performed to better understand how the turboelectric architecture changes the design space, and system sensitivities were run to determine the sensitivity of thrust specific fuel consumption at top of climb and propulsion system weight to the motor power, fan pressure ratio, and electrical transmission efficiency of the aft boundary layer ingesting fan.

  19. STS-26 crew trains in JSC full fuselage trainer (FFT) shuttle mockup

    Science.gov (United States)

    1988-01-01

    STS-26 Discovery, Orbiter Vehicle (OV) 103, crewmembers are briefed during a training exercise in the Shuttle Mockup and Integration Laboratory Bldg 9A. Seated outside the open side hatch of the full fuselage trainer (FFT) (left to right) are Mission Specialist (MS) George D. Nelson, Commander Frederick H. Hauck, and Pilot Richard O. Covey. Astronaut Steven R. Nagel (left), positioned in the open side hatch, briefs the crew on the pole escape system as he demonstrates some related equipment. During Crew Station Review (CSR) #3, the crew donned the new (navy blue) partial pressure suits (launch and entry suits (LESs)) and checked out crew escape system (CES) configurations to evaluate crew equipment and procedures related to emergency egress methods and proposed crew escape options. The photograph was taken by Keith Meyers of the NEW YORK TIMES.

  20. Autoimmune liver disease panel

    Science.gov (United States)

    Liver disease test panel - autoimmune ... Autoimmune disorders are a possible cause of liver disease. The most common of these diseases are autoimmune hepatitis and primary biliary cholangitis (formerly called primary biliary cirrhosis). This group of tests ...

  1. Blue Ribbon Panel Report

    Science.gov (United States)

    An NCI Cancer Currents blog by the NCI acting director thanking the cancer community for contributing to the Cancer Moonshot Blue Ribbon Panel report, which was presented to the National Cancer Advisory Board on September 7.

  2. Pop-Art Panels

    Science.gov (United States)

    Alford, Joanna

    2012-01-01

    James Rosenquist's giant Pop-art panels included realistic renderings of well-known contemporary foods and objects, juxtaposed with famous people in the news--largely from the 1960s, '70s and '80s--and really serve as visual time capsules. In this article, eighth-graders focus on the style of James Rosenquist to create their own Pop-art panel that…

  3. Equal Opportunities Advisory Panel

    CERN Multimedia

    HR Department

    2006-01-01

    At its meeting on 7 December 2006, the Standing Concertation Committee took note of the appointment of four new members of the Panel: Wisla Carena, Pierre Charrue, Sue Foffano and Markus Nordberg. The present composition of the Panel (appointed ad personam) is as follows: Tiziano Camporesi (Chairperson), Wisla Carena, Pierre Charrue, Sue Foffano, Josi Schinzel (Equal Opportunities Officer), Markus Nordberg, Christine Petit-Jean-Genaz et Elena Wildner. Human Resources Department Tel. 74480

  4. THE THERMOELECTRIC SOLAR PANELS

    OpenAIRE

    R. Ahiska; Nykyruy, L. I.; Omer, G.; G. D. Mateik

    2016-01-01

    In this study, load characteristics of thermoelectric and photovoltaic solar panels are investigated and compared with each other with experiments. Thermoelectric solar panels converts the heat generated by sun directly to electricity; while, photovoltaic solar pales converts photonic energy from sun to electricity. In both types, maximum power can be obtained when the load resistance is equal to internal resistance. According to experimental results, power generated from unit surface with th...

  5. Pop-Art Panels

    Science.gov (United States)

    Alford, Joanna

    2012-01-01

    James Rosenquist's giant Pop-art panels included realistic renderings of well-known contemporary foods and objects, juxtaposed with famous people in the news--largely from the 1960s, '70s and '80s--and really serve as visual time capsules. In this article, eighth-graders focus on the style of James Rosenquist to create their own Pop-art panel that…

  6. Theoretical prediction of thick wing and pylon-fuselage-fanpod-nacelle aerodynamic characteristics at subcritical speeds. Part 1: Theory and results

    Science.gov (United States)

    Tulinius, J. R.

    1974-01-01

    The theoretical development and the comparison of results with data of a thick wing and pylon-fuselage-fanpod-nacelle analysis are presented. The analysis utilizes potential flow theory to compute the surface velocities and pressures, section lift and center of pressure, and the total configuration lift, moment, and vortex drag. The skin friction drag is also estimated in the analysis. The perturbation velocities induced by the wing and pylon, fuselage and fanpod, and nacelle are represented by source and vortex lattices, quadrilateral vortices, and source frustums, respectively. The strengths of these singularities are solved for simultaneously including all interference effects. The wing and pylon planforms, twists, cambers, and thickness distributions, and the fuselage and fanpod geometries can be arbitrary in shape, provided the surface gradients are smooth. The flow through nacelle is assumed to be axisymmetric. An axisymmetric center engine hub can also be included. The pylon and nacelle can be attached to the wing, fuselage, or fanpod.

  7. Origami of thick panels

    Science.gov (United States)

    Chen, Yan; Peng, Rui; You, Zhong

    2015-07-01

    Origami patterns, including the rigid origami patterns in which flat inflexible sheets are joined by creases, are primarily created for zero-thickness sheets. In order to apply them to fold structures such as roofs, solar panels, and space mirrors, for which thickness cannot be disregarded, various methods have been suggested. However, they generally involve adding materials to or offsetting panels away from the idealized sheet without altering the kinematic model used to simulate folding. We develop a comprehensive kinematic synthesis for rigid origami of thick panels that differs from the existing kinematic model but is capable of reproducing motions identical to that of zero-thickness origami. The approach, proven to be effective for typical origami, can be readily applied to fold real engineering structures.

  8. Panel 3 - characterization

    Energy Technology Data Exchange (ETDEWEB)

    Erck, R.A.; Erdemir, A.; Janghsing Hsieh; Lee, R.H.; Xian Zheng Pan; Deming Shu [Argonne National Lab., IL (United States); Feldman, A. [National Inst. of Standards and Technology, Gaithersburg, MD (United States); Glass, J.T. [North Carolina State Univ., Raleigh (United States); Kleimer, R. [Coors Ceramics Co., Golden, CO (United States); Lawton, E.A. [JPL/Caltech, Pasadena, CA (United States); McHargue, C.J. [Univ. of Tennessee, Knoxville (United States)

    1993-01-01

    The task of this panel was to identify and prioritize needs in the area of characterization of diamond and diamond-like-carbon (DLC) films for use in the transportation industry. Until recent advances in production of inexpensive films of diamonds and DLC, it was not feasible that these materials could be mass produced. The Characterization Panel is restricting itself to identifying needs in areas that would be most useful to manufacturers and users in producing and utilizing diamond and DLC coatings in industry. These characterization needs include in-situ monitoring during growth, relation of structure to performance, and standards and definitions.

  9. Comparison of STRUCTURAL-ACOUSTIC Control Designs on AN Active Composite Panel

    Science.gov (United States)

    BINGHAM, B.; ATALLA, M. J.; HAGOOD, N. W.

    2001-07-01

    This work presents a comparison of three technologies for structural-acoustic control that, while prevalent in the literature, had not been compared on a single structure. The comparison is generalizable because the techniques are implemented on a panel structure representative of a more complex structure (e.g., an aircraft fuselage, a submarine vehicle hull, a satellite payload shroud, etc.). The test-bed used for this comparison is a carbon-fiber composite panel manufactured with embedded active fiber composite actuators. Since such integrated structures constitute a continued avenue of research, the manufacturing and performance of this structure is illustrated. The design of the test-bed is guided by an effort to achieve a dynamic response similar to a single panel in a typical aircraft or rotorcraft fuselage.Existing active control architectures for broadband acoustic radiation reduction are compared both analytically and experimentally on a representative structure to quantify the capabilities and limitations of the existing control methodologies. Specifically, three broad categories of control are compared: classical feedback (rate feedback), optimal feedback (linear quadratic Gaussian), and adaptive feedforward control (x -filtered least mean square). The control architectures implemented during this study are all single-input/single-output in order to allow a fair comparison of the issues involved in the design, as well as the use and performance of each approach. Both the vibration and the acoustic performance are recorded for each experiment under equivalent conditions to allow a generalizable comparison. Experimental results lead to conclusions pertaining to the application of active structural-based control to improve the acoustic performance of more complex structures.

  10. Comparison of ALE and SPH Simulations of Vertical Drop Tests of a Composite Fuselage Section into Water

    Science.gov (United States)

    Jackson, Karen E.; Fuchs, Yvonne T.

    2008-01-01

    Simulation of multi-terrain impact has been identified as an important research area for improved prediction of rotorcraft crashworthiness within the NASA Subsonic Rotary Wing Aeronautics Program on Rotorcraft Crashworthiness. As part of this effort, two vertical drop tests were conducted of a 5-ft-diameter composite fuselage section into water. For the first test, the fuselage section was impacted in a baseline configuration without energy absorbers. For the second test, the fuselage section was retrofitted with a composite honeycomb energy absorber. Both tests were conducted at a nominal velocity of 25-ft/s. A detailed finite element model was developed to represent each test article and water impact was simulated using both Arbitrary Lagrangian Eulerian (ALE) and Smooth Particle Hydrodynamics (SPH) approaches in LS-DYNA, a nonlinear, explicit transient dynamic finite element code. Analytical predictions were correlated with experimental data for both test configurations. In addition, studies were performed to evaluate the influence of mesh density on test-analysis correlation.

  11. Lightweight Sandwich Panel in Cold Stores and Refrigerated Warehouses

    OpenAIRE

    Chidom, Charles

    2013-01-01

    The use of sandwich panels has gained considerable recognition in the construction industry and more use of this composite structure is ever increasing. This study highlights and familiarizes the use of lightweight sandwich panel in refrigerated warehouses and cold storage facility and construction and the challenges such construction faces in warm climates considering the effects of thermal load. The study was commissioned by HAMK Sheet Metal Center, the steel research and development ce...

  12. Rational Design of Composite Panels

    DEFF Research Database (Denmark)

    Riber, Hans Jørgen

    1996-01-01

    panels as well as single-skin panels, the effect of shear is included. The finite difference method is used solving the system of governing plate equations. Laterally loaded panels are analysed with respect to mid-point deflections and stresses. The numerical results are discussed in the light of 'Det......A non-linear structural model for composite panels is presented. The non-linear terms in the lateral displacements are modelled as an additional set of lateral loads acting on the panel. Hence the solution is reduced to that of an equivalent panel with small displacements In order to treat sandwich...

  13. Photovoltaic-Panel Laminator

    Science.gov (United States)

    Keenan, R.

    1985-01-01

    Two-piece unit heats and presses protective layers to form laminate. Rubber diaphragm between upper and lower vacuum chambers alternates between neutral position and one that presses against solar-cell array, supplying distributed force necessary to press layers of laminate together. Encapsulation helps to protect cells from environment and to ensure long panel life while allowing efficient generation of electricity from Sunlight.

  14. Advanced solar panel designs

    Science.gov (United States)

    Ralph, E. L.; Linder, E. B.

    1996-01-01

    Solar panel designs that utilize new high-efficiency solar cells and lightweight rigid panel technologies are described. The resulting designs increase the specific power (W/kg) achievable in the near-term and are well suited to meet the demands of higher performance small satellites (smallsats). Advanced solar panel designs have been developed and demonstrated on two NASA SBIR contracts at Applied Solar. The first used 19% efficient, large area (5.5 cm x 6.5 cm) GaAs/Ge solar cells with a lightweight rigid graphite epoxy isogrid substrate configuration. A 1,445 cm(exp 2) coupon was fabricated and tested to demonstrate 60 W/kg with a high potential of achieving 80 W/kg. The second panel design used new 22% efficiency, dual junction GaInP2/GaAs/Ge solar cells combined with a lightweight aluminum core/graphite fiber mesh facesheet substrate. A 1,445 cm(exp 2) coupon was fabricated and tested to demonstrate 105 W/kg with the potential of achieving 115 W/kg. This paper will address the construction details for the GaAs/isogrid and dual-junction GaAs/carbon mesh panel configurations. These are ultimately sized to provide 75 Watts and 119 Watts respectively for smallsats or may be used as modular building blocks for larger systems. GaAs/isogrid and dual-junction GaAs/carbon mesh coupons have been fabricated and tested to successfully demonstrate critical performance parameters and results are also provided here.

  15. Analysis and Testing of a Composite Fuselage Shield for Open Rotor Engine Blade-Out Protection

    Science.gov (United States)

    Pereira, J. Michael; Emmerling, William; Seng, Silvia; Frankenberger, Charles; Ruggeri, Charles R.; Revilock, Duane M.; Carney, Kelly S.

    2016-01-01

    The Federal Aviation Administration is working with the European Aviation Safety Agency to determine the certification base for proposed new engines that would not have a containment structure on large commercial aircraft. Equivalent safety to the current fleet is desired by the regulators, which means that loss of a single fan blade will not cause hazard to the Aircraft. The NASA Glenn Research Center and The Naval Air Warfare Center (NAWC), China Lake, collaborated with the FAA Aircraft Catastrophic Failure Prevention Program to design and test lightweight composite shields for protection of the aircraft passengers and critical systems from a released blade that could impact the fuselage. LS-DYNA® was used to predict the thickness of the composite shield required to prevent blade penetration. In the test, two composite blades were pyrotechnically released from a running engine, each impacting a composite shield with a different thickness. The thinner shield was penetrated by the blade and the thicker shield prevented penetration. This was consistent with pre-test LS-DYNA predictions. This paper documents the analysis conducted to predict the required thickness of a composite shield, the live fire test from the full scale rig at NAWC China Lake and describes the damage to the shields as well as instrumentation results.

  16. Proficiency testing for sensory profile panels : measuring panel performance

    NARCIS (Netherlands)

    Mcewan, J.A.; Hunter, E.A.; Gemert, L.J. van; Lea, P.

    2002-01-01

    Proficiency testing in sensory analysis is an important step towards demonstrating that results from one sensory panel are consistent with the results of other sensory panels. The uniqueness of sensory analysis poses some specific problems for measuring the proficiency of the human instrument (panel

  17. FEMA DFIRM Panel Scheme Polygons

    Data.gov (United States)

    Minnesota Department of Natural Resources — This layer contains information about the Flood Insurance Rate Map (FIRM) panel areas. The spatial entities representing FIRM panels are polygons. The polygon for...

  18. LCD Panels: The Electronic Wonder.

    Science.gov (United States)

    Anderson, Glenn

    1994-01-01

    Describes Liquid Crystal Display (LCD) panels and their use in the classroom. Topics discussed include active versus passive matrix panels; the number of pixels; projectors, including transmissive or reflective overhead projectors; costs; and vendors that supply LCDs. (LRW)

  19. Sandwich Panels Evaluated With Ultrasonic Spectroscopy

    Science.gov (United States)

    Cosgriff, Laura M.

    2004-01-01

    Enhanced, lightweight material systems, such as 17-4PH stainless steel sandwich panels are being developed for use as fan blades and fan containment systems for next-generation engines. The bond strength between the core and face sheets is critical in maintaining the structural integrity of the sandwich structure. To improve the inspection and production of these systems, researchers at the NASA Glenn Research Center are using nondestructive evaluation (NDE) techniques, such as ultrasonic spectroscopy, to evaluate the brazing quality between the face plates and the metallic foam core. The capabilities and limitations of a swept-frequency approach to ultrasonic spectroscopy were evaluated with respect to these sandwich structures. This report discusses results from three regions of a sandwich panel representing different levels of brazing quality between the outer face plates and a metallic foam core. Each region was investigated with ultrasonic spectroscopy. Then, on the basis of the NDE results, three shear specimens sectioned from the sandwich panel to contain each of these regions were mechanically tested.

  20. Medical Physics Panel Discussion

    Science.gov (United States)

    Guèye, Paul; Avery, Steven; Baird, Richard; Soares, Christopher; Amols, Howard; Tripuraneni, Prabhakar; Majewski, Stan; Weisenberger, Drew

    2006-03-01

    The panel discussion will explore opportunities and vistas in medical physics research and practice, medical imaging, teaching medical physics to undergraduates, and medical physics curricula as a recruiting tool for physics departments. Panel members consist of representatives from NSBP (Paul Guèye and Steven Avery), NIH/NIBIB (Richard Baird), NIST (Christopher Soares), AAPM (Howard Amols), ASTRO (Prabhakar Tripuraneni), and Jefferson Lab (Stan Majewski and Drew Weisenberger). Medical Physicists are part of Departments of Radiation Oncology at hospitals and medical centers. The field of medical physics includes radiation therapy physics, medical diagnostic and imaging physics, nuclear medicine physics, and medical radiation safety. It also ranges from basic researcher (at college institutions, industries, and laboratories) to applications in clinical environments.

  1. Low-Subsonic-Speed Static Longitudinal Stability and Control Characteristics of a Winged Reentry-Vehicle Configuration Having Wingtip Panels that Fold up for High-Drag Reentry

    Science.gov (United States)

    Ware, George M.

    1960-01-01

    An investigation of the low-subsonic-speed static longitudinal stability and control characteristics of a model of a manned reentry-vehicle configuration capable of high-drag reentry and glide landing has been a made in the Langley free-flight tunnel. The model had a modified 63 deg delta plan-form wing with a fuselage on the upper surface. This configuration had wingtip panels designed to fold up 90 deg for the high-drag reentry phase of the flight and to extend horizontally for the glide landing. Data for the basic configurations and modifications to determine the effects of plan form, wingtip panel incidence, dihedral, and vertical position of the wingtip panels are presented without analysis.

  2. Student Panels, Business Administration

    DEFF Research Database (Denmark)

    Rask, Morten

    The purpose of student panels is to give feedback on students’ general and overall impression with the content and teaching of the individual courses as well as the progression and relationship between the courses offered. This will provide us with a background for assessing whether we meet...... are able to understand needed changes regarding courses and studies especially in relation to change the course portfolio of a study in order to strengthen the study’s content and/or progression....

  3. B-52B Cockpit Instrument Panel

    Science.gov (United States)

    1996-01-01

    casings. It also supported eight orbiter (space shuttle) drag chute tests in 1990. In addition, the B-52 served as the air launch platform for the first six Pegasus space boosters. During its many years of service, the B-52 has undergone several modifications. The first major modification was made by North American Aviation (now part of Boeing) in support of the X-15 program. This involved creating a launch-panel-operator station for monitoring the status of the test vehicle being carried, cutting a large notch in the right inboard wing flap to accommodate the vertical tail of the X-15 aircraft, and installing a wing pylon that enables the B-52 to carry research vehicles and test articles to be air-launched/dropped. Located on the right wing, between the inboard engine pylon and the fuselage, this wing pylon was subjected to extensive testing prior to its use. For each test vehicle the B-52 carried, minor changes were made to the launch-panel operator's station. Built originally by the Boeing Company, the NASA B-52 is powered by eight Pratt & Whitney J57-19 turbojet engines, each of which produce 12,000 pounds of thrust. The aircraft's normal launch speed has been Mach 0.8 (about 530 miles per hour) and its normal drop altitude has been 40,000 to 45,000 feet. It is 156 feet long and has a wing span of 185 feet. The heaviest load it has carried was the No. 2 X-15 aircraft at 53,100 pounds. Project manager for the aircraft is Roy Bryant.

  4. Panel data analysis using EViews

    CERN Document Server

    Agung, I Gusti Ngurah

    2013-01-01

    A comprehensive and accessible guide to panel data analysis using EViews software This book explores the use of EViews software in creating panel data analysis using appropriate empirical models and real datasets. Guidance is given on developing alternative descriptive statistical summaries for evaluation and providing policy analysis based on pool panel data. Various alternative models based on panel data are explored, including univariate general linear models, fixed effect models and causal models, and guidance on the advantages and disadvantages of each one is given. Panel Data Analysis

  5. Can I use a Panel? Panel Conditioning and Attrition Bias in Panel Surveys

    NARCIS (Netherlands)

    Das, J.W.M.; Toepoel, V.; van Soest, A.H.O.

    2007-01-01

    Over the past decades there has been an increasing use of panel surveys at the household or individual level, instead of using independent cross-sections. Panel data have important advantages, but there are also two potential drawbacks: attrition bias and panel conditioning effects. Attrition bias c

  6. Ground-based and in-flight simulator studies of flight characteristics of a twin-fuselage passenger transport airplane during approach and landing

    Science.gov (United States)

    Grantham, W. D.; Smith, P. M.; Neely, W. R., Jr.; Deal, P. L.; Yenni, K. R.

    1985-01-01

    Six-degree-of-freedom ground-based and in-flight simulator studies were conducted to evaluate the low-speed flight characteristics of a twin-fuselage passenger transport airplane and to compare these characteristics with those of a large, single-fuselage (reference) transport configuration similar to the Lockheed C-5A airplane. The primary piloting task was the approach and landing task. The results of this study indicated that the twin-fuselage transport concept had acceptable but unsatisfactory longitudinal and lateral-directional low-speed flight characteristics, and that stability and control augmentation would be required in order to improve the handling qualities. Through the use of rate-command/attitude-hold augmentation in the pitch and roll axes, and the use of several turn coordination features, the handling qualities of the simulated transport were improved appreciably. The in-flight test results showed excellent agreement with those of the six-degree-of-freedom ground-based simulator handling qualities tests. As a result of the in-flight simulation study, a roll-control-induced normal-acceleration criterion was developed. The handling qualities of the augmented twin-fuselage passenger transport airplane exhibited an improvement over the handling characteristics of the reference (single-fuselage) transport.

  7. Decontamination Efficacy of Three Commercial Off-the-Shelf Sporicidal Agents on Medium-Sized Panels Contaminated with Surrogates of Bacillus anthracis

    Science.gov (United States)

    2012-04-01

    from the panels. Depending on the surface composition and the decontamination technology tested, viable spore recovery from the panels varied after...water. 2.2 Panel Construction The mid-sized panels (33 each) were constructed from the following materials: • Brick veneer • Stainless steel...screws. A 1/2 in. thick brick veneer (Brickit.com [Cat. No. TSMODKINGW]) was then secured to the metal grid using construction adhesive. 2.3 Panel

  8. Photovoltaic panel clamp

    Energy Technology Data Exchange (ETDEWEB)

    Brown, Malcolm P.; Mittan, Margaret Birmingham; Miros, Robert H. J.; Stancel, Robert

    2013-03-19

    A photovoltaic panel clamp includes an upper and lower section. The interface between the assembled clamp halves and the module edge is filled by a flexible gasket material, such as EPDM rubber. The gasket preferably has small, finger like protrusions that allow for easy insertion onto the module edge while being reversed makes it more difficult to remove them from the module once installed. The clamp includes mounting posts or an integral axle to engage a bracket. The clamp also may include a locking tongue to secure the clamp to a bracket.

  9. Microsphere Insulation Panels

    Science.gov (United States)

    Mohling, R.; Allen, M.; Baumgartner, R.

    2006-01-01

    Microsphere insulation panels (MIPs) have been developed as lightweight, longlasting replacements for the foam and vacuum-jacketed systems heretofore used for thermally insulating cryogenic vessels and transfer ducts. The microsphere core material of a typical MIP consists of hollow glass bubbles, which have a combination of advantageous mechanical, chemical, and thermal-insulation properties heretofore available only separately in different materials. In particular, a core filling of glass microspheres has high crush strength and low density, is noncombustible, and performs well in soft vacuum.

  10. Photovoltaic panel clamp

    Science.gov (United States)

    Mittan, Margaret Birmingham; Miros, Robert H. J.; Brown, Malcolm P.; Stancel, Robert

    2012-06-05

    A photovoltaic panel clamp includes an upper and lower section. The interface between the assembled clamp halves and the module edge is filled by a flexible gasket material, such as EPDM rubber. The gasket preferably has small, finger like protrusions that allow for easy insertion onto the module edge while being reversed makes it more difficult to remove them from the module once installed. The clamp includes mounting posts or an integral axle to engage a bracket. The clamp also may include a locking tongue to secure the clamp to a bracket.

  11. Concentrating photovoltaic solar panel

    Science.gov (United States)

    Cashion, Steven A; Bowser, Michael R; Farrelly, Mark B; Hines, Braden E; Holmes, Howard C; Johnson, Jr., Richard L; Russell, Richard J; Turk, Michael F

    2014-04-15

    The present invention relates to photovoltaic power systems, photovoltaic concentrator modules, and related methods. In particular, the present invention features concentrator modules having interior points of attachment for an articulating mechanism and/or an articulating mechanism that has a unique arrangement of chassis members so as to isolate bending, etc. from being transferred among the chassis members. The present invention also features adjustable solar panel mounting features and/or mounting features with two or more degrees of freedom. The present invention also features a mechanical fastener for secondary optics in a concentrator module.

  12. CFRP panel concept design study for the CCAT

    Science.gov (United States)

    Martin, Robert N.; Romeo, Robert C.; Kingsley, Jeffrey S.

    2006-06-01

    Under contract from the Cornell-Caltech Atacama Telescope Project (CCAT), Composite Mirror Applications, Inc. (CMA) has undertaken a feasibility design study for the use of Carbon Fiber Reinforced Plastic (CFRP) panels in forming the primary mirror surface. We review some of the past projects using CFRP panel technology for millimeter and submillimeter wavelength radio astronomy telescopes. Pros and cons of the technology are discussed. A particular panel configuration was proposed and computer modeled with finite element analysis (FEA). The technology of replicated CFRP panels for short wavelength radio astronomical telescopes is mature and cost effective. For shorter wavelengths into the IR and visible, it is becoming a very attractive alternative to traditional, heavy glass or metal technologies.

  13. Improvement and evaluation of polymer-matrix composite panels with hat stiffeners

    Directory of Open Access Journals (Sweden)

    Li S. J.

    2016-01-01

    Full Text Available Hat-stiffened composite panels fabricated by co-curing technologies are widely used in the fuselage panel due to the good structural stability and high efficiency of axial load transferring. The bonding capability between the stiffener and skin is a primary criterion to assess the co-curing quality. In this paper, two reinforcement technologies of filling filler in the triangle region and adding split-stopping tape between the stiffener and skin were employed to improve the bonding capability. Effect of filler and split-stopping tape on the interface strength was analyzed, and the optimal size range of the filler and split-stopping tape were obtained. To improve the universality of application for the two reinforcement techniques, the filling coefficient of 0.62~0.77 and the split-stopping tape width coefficient of 0.56~0.67 were obtained by calculation. Results of the study can be used to develop other kinds of stiffened panels and will ultimately lead to optimized skin/stiffener designs.

  14. Solar panel parallel mounting configuration

    Science.gov (United States)

    Mutschler, Jr., Edward Charles (Inventor)

    1998-01-01

    A spacecraft includes a plurality of solar panels interconnected with a power coupler and an electrically operated device to provide power to the device when the solar cells are insolated. The solar panels are subject to bending distortion when entering or leaving eclipse. Spacecraft attitude disturbances are reduced by mounting each of the solar panels to an elongated boom made from a material with a low coefficient of thermal expansion, so that the bending of one panel is not communicated to the next. The boom may be insulated to reduce its bending during changes in insolation. A particularly advantageous embodiment mounts each panel to the boom with a single mounting, which may be a hinge. The single mounting prevents transfer of bending moments from the panel to the boom.

  15. ALDS 1978 panel review. [PNL

    Energy Technology Data Exchange (ETDEWEB)

    Hall, D.L. (ed.)

    1979-08-01

    Pacific Northwest Laboratory (PNL) is examining the analysis of large data sets (ALDS). After one year's work, a panel was convened to evaluate the project. This document is the permanent record of that panel review. It consists of edited transcripts of presentations made to the panel by the PNL staff, a summary of the responses of the panel to these presentations, and PNL's plans for the development of the ALDS project. The representations of the PNL staff described various aspects of the project and/or the philosophy surrounding the project. Supporting materials appear in appendixes. 20 figures, 4 tables. (RWR)

  16. Investigation of the Influence of Fuselage and Tail Surfaces on Low-speed Static Stability and Rolling Characteristics of a Swept-wing Model

    Science.gov (United States)

    Bird, John D; Lichtenstein, Jacob H; Jaquet, Byron M

    1952-01-01

    Results are presented of a wind-tunnel investigation to determine influence of the fuselage and tail on static stability and rotary derivatives in roll of a model having 45 degrees sweptback wing and tail surfaces. The wing alone and the model without the horizontal tail showed marginal longitudinal stability near maximum lift. The longitudinal stability of the complete model was satisfactory. The vertical tail produced larger increments of rate of change of lateral-force and yawing-moment coefficients with wing-tip helix angle than the fuselage or the horizontal tail.

  17. Guideline for Forming Stiffened Panels by Using the Electromagnetic Forces

    Directory of Open Access Journals (Sweden)

    Jinqiang Tan

    2016-11-01

    Full Text Available Electromagnetic forming (EMF, as a high-speed forming technology by applying the electromagnetic forces to manufacture sheet or tube metal parts, has many potential advantages, such as contact-free and resistance to buckling and springback. In this study, EMF is applied to form several panels with stiffened ribs. The distributions and variations of the electromagnetic force, the velocity and the forming height during the EMF process of the bi-directional panel with gird ribs are obtained by numerical simulations, and are analyzed via the comparison to those with the flat panel (non-stiffened and two uni-directional panels (only with X-direction or Y-direction ribs. It is found that the electromagnetic body force loads simultaneously in the ribs and the webs, and the deformation of the panels is mainly driven by the force in the ribs. The distribution of force in the grid-rib panel can be found as the superposition of the two uni-directional stiffened panels. The velocity distribution for the grid-rib panel is primarily affected by the X-directional ribs, then the Y-directional ribs, and the variation of the velocity are influenced by the force distribution primarily and secondly the inertial effect. Mutual influence of deformation exists between the region undergoing deformation and the deformed or underformed free ends. It is useful to improve forming uniformity via a second discharge at the same position. Comparison between EMF and the brake forming with a stiffened panel shows that the former has more advantages in reducing the defects of springback and buckling.

  18. Thermal and Mechanical Buckling Analysis of Hypersonic Aircraft Hat-Stiffened Panels With Varying Face Sheet Geometry and Fiber Orientation

    Science.gov (United States)

    Ko, William L.

    1996-01-01

    Mechanical and thermal buckling behavior of monolithic and metal-matrix composite hat-stiffened panels were investigated. The panels have three types of face-sheet geometry: Flat face sheet, microdented face sheet, and microbulged face sheet. The metal-matrix composite panels have three types of face-sheet layups, each of which is combined with various types of hat composite layups. Finite-element method was used in the eigenvalue extractions for both mechanical and thermal buckling. The thermal buckling analysis required both eigenvalue and material property iterations. Graphical methods of the dual iterations are shown. The mechanical and thermal buckling strengths of the hat-stiffened panels with different face-sheet geometry are compared. It was found that by just microdenting or microbulging of the face sheet, the axial, shear, and thermal buckling strengths of both types of hat-stiffened panels could be enhanced considerably. This effect is more conspicuous for the monolithic panels. For the metal-matrix composite panels, the effect of fiber orientations on the panel buckling strengths was investigated in great detail, and various composite layup combinations offering, high panel buckling strengths are presented. The axial buckling strength of the metal-matrix panel was sensitive to the change of hat fiber orientation. However, the lateral, shear, and thermal buckling strengths were insensitive to the change of hat fiber orientation.

  19. Reaction-to-Fire Properties and Fire Spread Properties of Metal-Skinned Expanded Polystyrene Foam Sandwich Panel%金属面EPS泡沫夹芯板的对火反应特性和火蔓延特性

    Institute of Scientific and Technical Information of China (English)

    尤飞; 胡源

    2012-01-01

    利用3种强度汽油火源引燃金属面可发性聚苯乙烯泡沫夹芯板(EPS彩钢板),分别采用ISO9705房屋/墙角试验装置和热电偶束测定了不同处理方式下的板材对火反应特性和火蔓延特性.结果发现,3种强度火源下封边加固板材峰值热释放速率为未封边板材的0.1倍、0.5倍和0.8倍,最高温度范围分别为35~ 249℃、61~820℃和50~527℃,水平方向0.1 ~0.3m距离内最高平均蔓延速率分别为0.09 ~2 cn/s、1.4 ~ 10 cm/s和4.4~10 cm/s,火源功率增大可使达到同—温度的传播速率最高增大100倍,同一时刻水平和垂直方向上不同测点温度呈现一阶指数衰减的分布规律.采用槽铝和白铁皮覆盖夹芯板面板边缘处并均匀使用铆钉加固后,夹芯板整体燃烧性能被有效抑制,对外墙保温板材的应用方式具有积极借鉴意义.%Gasoline pool fires with three fire powers were used to ignite EPS panels treated with and without edge sealing and reinforcement. The ISO9705 full-scale room/corner test apparatus and thermocouple trees were adopted to measure the reaction-to-fire properties and fire spread properties. The results show that, under three fire powers, the peak heat release rate values of edge-sealed and incision-strengthened panels are 0.1, 0.5 and 0.8 times those of unsealed panels, the maximum temperatures lie within the range of 35?49?, 61?20 ? and 50?27 ?, and the maximum average spread rates in 0.1?.3 m horizontal distances lie within the range of 0.09? cm/s, 1.4?0 cm/s and 4.4?0 cm/s, respectively. As fire power increases, the spread rate reaching the same temperature at various measuring points can increase as high as 100 times. The temperatures at various horizontal and vertical points at the same moment distribute as the first order decay exponent. All the data indicate that the overall burning properties are effectively restrained when EPS panels are wrapped peripherally with aluminium slots

  20. Electronic route information panels (DRIPs).

    NARCIS (Netherlands)

    2008-01-01

    Also in the Netherlands, the term Dynamic Route Information Panel (DRIP) is used for an electronic route information panel. A DRIP usually indicates whether there are queues on the various routes to a particular destination and how long they are. On certain locations DRIPS also give the estimated tr

  1. Thermal-Diode Sandwich Panel

    Science.gov (United States)

    Basiulis, A.

    1986-01-01

    Thermal diode sandwich panel transfers heat in one direction, but when heat load reversed, switches off and acts as thermal insulator. Proposed to control temperature in spacecraft and in supersonic missiles to protect internal electronics. In combination with conventional heat pipes, used in solar panels and other heat-sensitive systems.

  2. Plane and parabolic solar panels

    CERN Document Server

    Sales, J H O

    2009-01-01

    We present a plane and parabolic collector that absorbs radiant energy and transforms it in heat. Therefore we have a panel to heat water. We study how to increment this capture of solar beams onto the panel in order to increase its efficiency in heating water.

  3. Mounting clips for panel installation

    Energy Technology Data Exchange (ETDEWEB)

    Cavieres, Andres; Al-Haddad, Tristan; Goodman, Joseph; Valdes, Francisco

    2017-02-14

    An exemplary mounting clip for removably attaching panels to a supporting structure comprises a base, spring locking clips, a lateral flange, a lever flange, and a spring bonding pad. The spring locking clips extend upwardly from the base. The lateral flange extends upwardly from a first side of the base. The lateral flange comprises a slot having an opening configured to receive at least a portion of one of the one or more panels. The lever flange extends outwardly from the lateral flange. The spring bonding flange extends downwardly from the lever flange. At least a portion of the first spring bonding flange comprises a serrated edge for gouging at least a portion of the one or more panels when the one or more panels are attached to the mounting clip to electrically and mechanically couple the one or more panels to the mounting clip.

  4. Thermal fatigue tests of a radiative heat shield panel for a hypersonic transport

    Science.gov (United States)

    Webb, Granville L.; Clark, Ronald K.; Sharpe, Ellsworth L.

    1985-01-01

    A pair of corrugation stiffened, beaded skin Rene 41 heat shield panels were exposed to 20,000 thermal cycles between room temperature and 1450 F to evaluate the thermal fatigue response of Rene 41 metallic heat shields for hypersonic cruise aircraft applications. At the conclusion of the tests, the panels retained substantial structural integrity; however, there were cracks and excessive wear in the vicinity of fastener holes and there was an 80-percent loss in ductility of the skin. Shrinkage of the panel which caused the cracks and wear must be considered in design of panels for Thermal Protection Systems (TPS) applications.

  5. Effects of Boattail Area Contouring and Simulated Turbojet Exhaust on the Loading and Fuselage-tail Component Drag of a Twin-engine Fighter-type Airplane Model

    Science.gov (United States)

    Foss, Willard E , Jr; Runckel, Jack F; Lee, Edwin E , Jr

    1958-01-01

    An investigation of a twin-engine fighter-type airplane model has been conducted in the Langley 16-foot transonic tunnel to determine the effect on drag of a fuselage volume addition incorporating streamline contouring and more extensive boattailing of the engine shrouds. The effect of hot exhausts from the turbojet engines was simulated with hydrogen peroxide gas generators using scaled nonafterburning engine nozzles. Afterbody pressure distributions, base drag coefficients, and forces on the fuselage-tail configurations are presented at Mach numbers from 0.80 to 1.05 angles of attack of 0 degree and 4 degrees for jet pressure ratios from 1 to 7. The effect of jet operation on both the basic and modified models was generally to decrease base pressures but to increase most other afterbody pressures and, therefore, to result in an overall decrease in fuselage-tail component drag. The addition of volume to the basic model reduced the base drag coefficient by 0.0010 with the jets off and 0.0018 at a typical cruise operating condition of a jet pressure ratio of 3, a Mach number of 0.85, and an angle of attack of 4 degrees. The overall jet-off reduction in fuselage-tail component drag due to the volume addition was a maximum of 0.0040 at a Mach number of 0.90 for an angle of attack of 4 degrees.

  6. 78 FR 66317 - Special Conditions: Learjet Inc. Model LJ-200-1A10; Airplane Fuselage Post-Crash Fire Survivability

    Science.gov (United States)

    2013-11-05

    ... fabricated from monolithic carbon-fiber reinforced plastic (CFRP) prepreg material (reinforcement fiber pre... feature associated with advanced composite materials in the construction of its fuselage and wings. The... generated from toxic levels of gases produced from carbon-fiber/resin system materials following a...

  7. Common aspects and differences in the behaviour of classical configuration versus canard configuration aircraft in the presence of vertical gusts, assuming the hypothesis of an elastic fuselage

    Directory of Open Access Journals (Sweden)

    Octavian PREOTU

    2011-06-01

    Full Text Available The paper analyzes, in parallel, common aspects and differences in the behavior of classical configuration versus canard configuration aircraft in the presence of vertical gusts, assuming the hypothesis of an elastic fuselage. The effects of the main constructional dimensions of the horizontal empennage on lift cancelling and horizontal empennage control are being analyzed

  8. Theoretical prediction of thick wing and pylon-fuselage-fanpod-nacelle aerodynamic characteristics at subcritical speeds. Part 2: Computer program description

    Science.gov (United States)

    Kojima, J.; Tulinius, J. R.

    1974-01-01

    The procedures required to operate the thick wing and pylon-fuselage-fanpod-nacelle computer program are presented. The program computes surface velocities and pressure, section loads, and total configuration loads and pitching moment. Potential flow theory is used to compute the surface pressures and the associated lift, moment, and vortex drag. The skin friction drag is also computed.

  9. Fabrication and development of several heat pipe honeycomb sandwich panel concepts

    Science.gov (United States)

    Tanzer, H. J.

    1982-06-01

    The feasibility of fabricating and processing liquid metal heat pipes in a low mass honeycomb sandwich panel configuration for application on the NASA Langley airframe-integrated Scramjet engine was investigated. A variety of honeycomb panel facesheet and core-ribbon wick concepts was evaluated within constraints dictated by existing manufacturing technology and equipment. The chosen design consists of an all-stainless steel structure, sintered screen facesheets, and two types of core-ribbon; a diffusion bonded wire mesh and a foil-screen composite. Cleaning, fluid charging, processing, and process port sealing techniques were established. The liquid metals potassium, sodium and cesium were used as working fluids. Eleven honeycomb panels 15.24 cm X 15.24 cm X 2.94 cm were delivered to NASA Langley for extensive performance testing and evaluation; nine panels were processed as heat pipes, and two panels were left unprocessed.

  10. Fabrication and development of several heat pipe honeycomb sandwich panel concepts. [airframe integrated scramjet engine

    Science.gov (United States)

    Tanzer, H. J.

    1982-01-01

    The feasibility of fabricating and processing liquid metal heat pipes in a low mass honeycomb sandwich panel configuration for application on the NASA Langley airframe-integrated Scramjet engine was investigated. A variety of honeycomb panel facesheet and core-ribbon wick concepts was evaluated within constraints dictated by existing manufacturing technology and equipment. The chosen design consists of an all-stainless steel structure, sintered screen facesheets, and two types of core-ribbon; a diffusion bonded wire mesh and a foil-screen composite. Cleaning, fluid charging, processing, and process port sealing techniques were established. The liquid metals potassium, sodium and cesium were used as working fluids. Eleven honeycomb panels 15.24 cm X 15.24 cm X 2.94 cm were delivered to NASA Langley for extensive performance testing and evaluation; nine panels were processed as heat pipes, and two panels were left unprocessed.

  11. Steady and Periodic Pressure Measurements on a Generic Helicopter Fuselage Model in the Presence of a Rotor

    Science.gov (United States)

    Mineck, Raymond E.; Gorton, Susan A.

    2000-01-01

    A wind tunnel test of a generic helicopter fuselage model with an independently mounted rotor has been conducted to obtain steady and periodic pressure data on the helicopter body. The model was tested at four advance ratios and three thrust coefficients. The periodic unsteady pressure coefficients are marked by four peaks associated with the passage of the four rotor blades. Blade passage effects are largest on the nose and tail boom of the model. The magnitude of the pulse increases with rotor thrust coefficient. Tabular listings of the unsteady pressure data are included to permit independent analysis. A CD-rom containing the steady and unsteady pressure data presented in the report is available from the authors.

  12. Conceptual shape optimization of entry vehicles applied to capsules and winged fuselage vehicles

    CERN Document Server

    Dirkx, Dominic

    2017-01-01

    This book covers the parameterization of entry capsules, including Apollo capsules and planetary probes, and winged entry vehicles such as the Space Shuttle and lifting bodies. The aerodynamic modelling is based on a variety of panel methods that take shadowing into account, and it has been validated with flight and wind tunnel data of Apollo and the Space Shuttle. The shape optimization is combined with constrained trajectory analysis, and the multi-objective approach provides the engineer with a Pareto front of optimal shapes. The method detailed in Conceptual Shape Optimization of Entry Vehicles is straightforward, and the output gives the engineer insight in the effect of shape variations on trajectory performance. All applied models and algorithms used are explained in detail, allowing for reconstructing the design tool to the researcher’s requirements. Conceptual Shape Optimization of Entry Vehicles will be of interest to both researchers and graduate students in the field of aerospace engineering, an...

  13. Exascale Workshop Panel Report Meeting

    Energy Technology Data Exchange (ETDEWEB)

    Khaleel, Mohammad A.

    2010-07-01

    The Exascale Review Panel consists of 12 scientists and engineers with experience in various aspects of high-performance computing and its application, development, and management. The Panel hear presentations by several representatives of the workshops and town meetings convened over the past few years to examine the need for exascale computation capability and the justification for a U.S. Department of Energy (DOE) program to develop such capability. This report summarizes information provided by the presenters and substantial written reports to the Panel in advance of the meeting in Washington D.C. on January 19-20, 2010. The report also summarizes the Panel's conclusions with regard to the justification of a DOE-led exascale initiative.

  14. Plasma Panel Sensors for Particle and Beam Detection

    CERN Document Server

    Friedman, Peter S; Beene, James R; Benhammou, Yan; Bentefour, E H; Chapman, J W; Etzion, Erez; Ferretti, Claudio; Guttman, Nir; Levin, Daniel S; Ben-Moshe, Meny; Silver, Yiftah; Varner, Robert L; Weaverdyck, Curtis; Zhou, Bing

    2012-01-01

    The plasma panel sensor (PPS) is an inherently digital, high gain, novel variant of micropattern gas detectors inspired by many operational and fabrication principles common to plasma display panels (PDPs). The PPS is comprised of a dense array of small, plasma discharge, gas cells within a hermetically-sealed glass panel, and is assembled from non-reactive, intrinsically radiation-hard materials such as glass substrates, metal electrodes and mostly inert gas mixtures. We are developing the technology to fabricate these devices with very low mass and small thickness, using gas gaps of at least a few hundred micrometers. Our tests with these devices demonstrate a spatial resolution of about 1 mm. We intend to make PPS devices with much smaller cells and the potential for much finer position resolutions. Our PPS tests also show response times of several nanoseconds. We report here our results in detecting betas, cosmic-ray muons, and our first proton beam tests.

  15. Reminder - Equal Opportunities Advisory Panel

    CERN Multimedia

    HR Department

    2007-01-01

    At its meeting on 7 December 2006, the Standing Concertation Committee also took note of the nomination of a fourth new member of the Panel: Wisla Carena. The present composition of the Panel (appointed ad personam) is now as follows: Tiziano Camporesi (Chairperson), Wisla Carena, Pierre Charrue, Sue Foffano, Josi Schinzel (Equal Opportunities Officer), Markus Nordberg, Christine Petit-Jean-Genaz and Elena Wildner. Human Resources Department Tel. 74480

  16. Section Parameters Design of the Curved Surface Fuselage and Stealth Performance Optimization%曲面机身剖面参数设计与隐身性能优化

    Institute of Scientific and Technical Information of China (English)

    李启鹏; 王和平; 潘志雄; 司亮

    2011-01-01

    To reduce fuselage side face RCS ( Radar Cross Section ), the section parametrics of fuselage are designed and optimized. Section parametrics modeling and model of the curved surface fuselage are established. Multilevel Fast Multipole Algorithm is used to calculate fuselage' s RCS. The impact of the angle of minimal normal slope of the upper and lower fuselage surface and the wedge angle to fuselage side face RCS is researched. Through the calculation of different fuselage, response surface is built by Radial Basis Function modeling method. And the section parameters of fuselage model are optimized by SQP. Comparing with the fuselage model without optimization and with the same size ellipse fuselage, side face RCS of the optimized fuselage model dropped away by 2.2dBm2 and 6.0dBm2, which validated the effectiveness of fuselage optimization with parametric modeling method and RCS reduction.%研究飞机的战斗力和生存力问题,为了降低机身侧向雷达散射截面(RCS),对机身剖面参数进行设计和优化.将典型曲面机身分段进行剖面参数化造型,并建立曲面机身模型,利用多层快速多极子方法计算机身RCS,研究了机身上下表面最小法线斜率角和尖劈角对机身侧向RCS的影响.通过对不同剖面参数机身的计算,采用径向基函数建模方法建立机身侧向RCS对机身剖面参数的响应面,根据序列二次子规划方法对机身模型剖面参数进行优化.优化后的机身模型侧向RCS分别较优化前椭圆机身尺寸降低了,验证了剖面参数优化和RCS减缩的有效性.

  17. Performance of a Supersonic Ramp-type Side Inlet with Ram-scoop Throat Bleed and Varying Fuselage Boundary-layer Removal : Mach Number Range 1.5 to 2.0 / Glenn A. Mitchell and Robert C. Campbell

    Science.gov (United States)

    Mitchell, Glenn A; Campbell, Robert C

    1957-01-01

    Provided sufficient throat bleed was employed, maximum pressure recoveries of 0.87 to 0.88 at Mach number 2.0 were obtained for a fuselage-mounted 14 degrees ramp inlet regardless of the amount of fuselage boundary layer ingested. The addition of inlet side fairings yielded further increases in pressure recovery to 0.90 to 0.91, decreased critical drag coefficients, and increased critical mass-flow ratios. With throat bleed, peak pressure recoveries and calculated thrust-minus-drag values were comparable at two axial positions of the scoop and were highest with the greatest amount of fuselage boundary layer ingested.

  18. Studying Impact Damage on Carbon-Fiber Reinforced Aircraft Composite Panels with Sonicir

    Science.gov (United States)

    Han, Xiaoyan; Zhao, Xinyue; Zhang, Ding; He, Qi; Song, Yuyang; Lubowicki, Anthony; Newaz, Golam.; Favro, Lawrence D.; Thomas, Robert L.

    2011-06-01

    Composites are becoming more important materials in commercial aircraft structures such as the fuselage and wings with the new B787 Dreamliner from Boeing which has the target to utilize 50% by weight of composite materials. Carbon-fiber reinforced composites are the material of choice in aircraft structures. This is due to their light weight and high strength (high strength-to-weight ratio), high specific stiffness, tailorability of properties, design flexibility etc. Especially, by reducing the aircraft's body weight by using such lighter structures, the cost of fuel can be greatly reduced with the high jet fuel price for commercial airlines. However, these composites are prone to impact damage and the damage may occur without any observable sign on the surface, yet resulting in delaminations and disbonds that may occur well within the layers. We are studying the impact problem with carbon-fiber reinforced composite panels and developing SonicIR for this application as a fast and wide-area NDE technology. In this paper, we present our results in studying composite structures including carbon-fiber reinforced composite materials, and preliminary quantitative studies on delamination type defect depth identification in the panels.

  19. A Novel Lighting OLED Panel Design

    Directory of Open Access Journals (Sweden)

    Enyang Zhang

    2016-11-01

    Full Text Available A novel OLED (organic light emitting diode lighting panel, which uses a special layout design, can reduce the photolithography cycles and process costs and is more reliable. It only needs two steps of photolithography cycles, which include an ITO (InSnO compound transparent oxide pattern and insulator pattern. There is no need for the metal bus pattern of the ordinary design. The OLED device structure is a type of red–green–blue (RGB-stacked emitting layer that has a good color index and greater adjustability, which improves the performance of the device. This novel design has the same equipment and material requirement compared to the ordinary design, and it is very beneficial in terms of high volume and low-cost production. It uses a hyper driving method because the entire OLED lighting panel is divided into many sub-emitting units; if one of the sub-emitting units is burned out, it has no effect on the adjacent sub-emitting unit, so the reliability is markedly better than the ordinary design.

  20. Easy Attachment Of Panels To A Truss

    Science.gov (United States)

    Thomson, Mark; Gralewski, Mark

    1992-01-01

    Conceptual antenna dish, solar collector, or similar structure consists of hexagonal panels supported by truss erected in field. Truss built in increments to maintain access to panel-attachment nodes. Each panel brought toward truss at angle and attached to two nodes. Panel rotated into attachment at third node.

  1. Easy Attachment Of Panels To A Truss

    Science.gov (United States)

    Thomson, Mark; Gralewski, Mark

    1992-01-01

    Conceptual antenna dish, solar collector, or similar structure consists of hexagonal panels supported by truss erected in field. Truss built in increments to maintain access to panel-attachment nodes. Each panel brought toward truss at angle and attached to two nodes. Panel rotated into attachment at third node.

  2. Metal foams: A survey

    Institute of Scientific and Technical Information of China (English)

    Michael; F.; Ashby; LU; Tianjian(卢天健)

    2003-01-01

    The current state-of-the-art in the development of cellular metal foams is reviewed, with focus on their fabrication, mechanical/thermal/acoustic properties, and potential applications as lightweight panels, energy absorbers, heat exchangers, and acoustic liners. Foam property charts with scaling relations are presented, allowing scoping and selection through the use of material indices.

  3. Consideration of some factors affecting low-frequency fuselage noise transmission for propeller aircraft

    Science.gov (United States)

    Mixson, J. S.; Roussos, L. A.

    1986-01-01

    Possible reasons for disagreement between measured and predicted trends of sidewall noise transmission at low frequency are investigated using simplified analysis methods. An analytical model combining incident plane acoustic waves with an infinite flat panel is used to study the effects of sound incidence angle, plate structural properties, frequency, absorption, and the difference between noise reduction and transmission loss. Analysis shows that these factors have significant effects on noise transmission but they do not account for the differences between measured and predicted trends at low frequencies. An analytical model combining an infinite flat plate with a normally incident acoustic wave having exponentially decaying magnitude along one coordinate is used to study the effect of a localized source distribution such as is associated with propeller noise. Results show that the localization brings the predicted low-frequency trend of noise transmission into better agreement with measured propeller results. This effect is independent of low-frequency stiffness effects that have been previously reported to be associated with boundary conditions.

  4. High temperature structural sandwich panels

    Science.gov (United States)

    Papakonstantinou, Christos G.

    High strength composites are being used for making lightweight structural panels that are being employed in aerospace, naval and automotive structures. Recently, there is renewed interest in use of these panels. The major problem of most commercial available sandwich panels is the fire resistance. A recently developed inorganic matrix is investigated for use in cases where fire and high temperature resistance are necessary. The focus of this dissertation is the development of a fireproof composite structural system. Sandwich panels made with polysialate matrices have an excellent potential for use in applications where exposure to high temperatures or fire is a concern. Commercial available sandwich panels will soften and lose nearly all of their compressive strength temperatures lower than 400°C. This dissertation consists of the state of the art, the experimental investigation and the analytical modeling. The state of the art covers the performance of existing high temperature composites, sandwich panels and reinforced concrete beams strengthened with Fiber Reinforced Polymers (FRP). The experimental part consists of four major components: (i) Development of a fireproof syntactic foam with maximum specific strength, (ii) Development of a lightweight syntactic foam based on polystyrene spheres, (iii) Development of the composite system for the skins. The variables are the skin thickness, modulus of elasticity of skin and high temperature resistance, and (iv) Experimental evaluation of the flexural behavior of sandwich panels. Analytical modeling consists of a model for the flexural behavior of lightweight sandwich panels, and a model for deflection calculations of reinforced concrete beams strengthened with FRP subjected to fatigue loading. The experimental and analytical results show that sandwich panels made with polysialate matrices and ceramic spheres do not lose their load bearing capability during severe fire exposure, where temperatures reach several

  5. Metal-induced crystallization fundamentals and applications

    CERN Document Server

    Wang, Zumin; Mittemeijer, Eric J

    2014-01-01

    Introduction to Metal-Induced CrystallizationAtomic Mechanisms and Interface Thermodynamics of Metal-Induced Crystallization of Amorphous Semiconductors at Low TemperaturesThermodynamics and Kinetics of Layer Exchange upon Low-Temperature Annealing Amorphous Si/Polycrystalline Al Layered StructuresMetal-Induced Crystallization by Homogeneous Insertion of Metallic Species in Amorphous SemiconductorsAluminum-Induced Crystallization: Applications in Photovoltaic TechnologiesApplications of Metal-Induced Crystallization for Advanced Flat-Panel DisplaysLaser-Assisted Meta

  6. The Conservation of Panel paintings

    DEFF Research Database (Denmark)

    Until the early 17th century almost all portable paintings were created on wood supports, including masterpieces by famous painters, ranging from Giotto to Dürer to Rembrandt. The structural conservation of these paintings requires specific knowledge and skills as the supports are susceptible...... to damage caused by unstable environmental conditions. Unfortunately, past structural interventions often caused significant damage due to insufficient knowledge of the behaviour of the wood panels, glue and paint layers. Over the last fifty years, the field has developed treatment strategies based......, it is imperative to strengthen scientific research into the production methods, ageing and future behaviour of panel paintings, being an intricate interplay between different materials. A deeper understanding of the processes that adversely affect panel paintings over time will contribute to the improved care...

  7. Solar Panel based Milk Pasteurization

    DEFF Research Database (Denmark)

    Nielsen, Kirsten Mølgaard; Pedersen, Tom Søndergaard

    This paper treats the subject of analysis, design and development of the control system for a solar panel based milk pasteurization system to be used in small villages in Tanzania. The analysis deals with the demands for an acceptable pasteurization, the varying energy supply and the low cost, low...... complexity, simple user interface and high reliability demands. Based on these demands a concept for the pasteurization system is established and a control system is developed. A solar panel has been constructed and the energy absorption has been tested in Tanzania. Based on the test, the pasteurization...... system is dimensioned. A functional prototype of the pasteurization facility with a capacity of 200 l milk/hour has been developed and tested. The system is prepared for solar panels as the main energy source and is ready for a test in Tanzania....

  8. Solar Panel based Milk Pasteurization

    DEFF Research Database (Denmark)

    Nielsen, Kirsten Mølgaard; Pedersen, Tom Søndergaard

    2002-01-01

    This paper treats the subject of analysis, design and development of the control system for a solar panel based milk pasteurization system to be used in small villages in Tanzania. The analysis deals with the demands for an acceptable pasteurization, the varying energy supply and the low cost, low...... complexity, simple user interface and high reliability demands. Based on these demands a concept for the pasteurization system is established and a control system is developed. A solar panel has been constructed and the energy absorption has been tested in Tanzania. Based on the test, the pasteurization...... system is dimensioned. A functional prototype of the pasteurization facility with a capacity of 200 l milk/hour has been developed and tested. The system is prepared for solar panels as the main energy source and is ready for a test in Tanzania....

  9. Active control of broadband sound transmission through an airplane trim panel using hybrid feedforward and feedback techniques

    Science.gov (United States)

    Ho, Yun-Ren

    This thesis presents a method of actively controlling the sound transmission through two designs of aircraft trim panels using a hybrid feedforward and feedback control technique. The active trim panels are designed for a high stiffness to mass ratio to allow only rigid body modal vibration in the frequency range of interest, thus simplifying the control technique, which is developed to minimize the vibration of a panel and therefore minimize the sound transmission. The hybrid controller consists of an adaptive feedforward (filtered-X LMS algorithm) controller in conjunction with a linear quadratic Gaussian (LQG) feedback controller. The LQG feedback controller is designed to alter the dynamics of the estimated plant model of the filtered-x LMS algorithm, improving control performance for both steady state and transient disturbances. Numerical simulations indicate that the hybrid controller is a more effective method of reducing the vibrations of the panels (and therefore the sound transmission) when compared to using only a feedforward or feedback controller. Experiments were carried out by using two trim panel designs, the first exhibiting only an out-of-plane piston mode, and the second exhibiting three rigid body modes and the first bending mode in control frequency range. For the first trim panel, the implementation of the active control experiment showed that a 5 to 20 dB reduction in both the vibration level and sound pressure level could be achieved over 50 to 500 Hz under a plane acoustic wave excitation. For the second trim panel, the hybrid controller achieved a 5 to 20 dB vibration reduction over the 50 to 400 Hz frequency band under structure-borne excitation. For air-borne excitation, the control scheme produced a 5 to 15 dB vibration reduction over the 70 to 400 Hz bandwidth with a reference microphone attached on the center of the fuselage skin and facing the sound source. In the near field (50 cm from the panel), the sound pressure levels measured

  10. NO y Blue Ribbon panel

    Science.gov (United States)

    Crosley, David R.

    1996-01-01

    Total NOy was determined on the Pacific Exploratory Mission-West A using two separate instruments, one operated by Georgia Institute of Technology and one by Nagoya University. The two data sets exhibited significant disagreement, with no systematic correlation, and differences often a factor of 2 or more. Additionally, regardless of data set chosen, the total NOy was much greater than the sum of its components measured separately. A panel was convened by NASA in July 1993 to examine these conflicting datasets and the question of "missing NOy" on this mision. This paper reports the conclusions and recommendations from the panel.

  11. Solar Panel based Milk Pasteurization

    DEFF Research Database (Denmark)

    Nielsen, Kirsten Mølgaard; Pedersen, Tom Søndergaard

    2002-01-01

    This paper treats the subject of analysis, design and development of the control system for a solar panel based milk pasteurization system to be used in small villages in Tanzania. The analysis deals with the demands for an acceptable pasteurization, the varying energy supply and the low cost, low...... system is dimensioned. A functional prototype of the pasteurization facility with a capacity of 200 l milk/hour has been developed and tested. The system is prepared for solar panels as the main energy source and is ready for a test in Tanzania....

  12. The "Virtual" Panel: A Computerized Model for LGBT Speaker Panels

    Science.gov (United States)

    Beasley, Christopher; Torres-Harding, Susan; Pedersen, Paula J.

    2012-01-01

    Recent societal trends indicate more tolerance for homosexuality, but prejudice remains on college campuses. Speaker panels are commonly used in classrooms as a way to educate students about sexual diversity and decrease negative attitudes toward sexual diversity. The advent of computer-delivered instruction presents a unique opportunity to…

  13. 飞机机身结构的腐蚀及防护方法%Structure Corrosion and Protective Measures for Aircraft Fuselage

    Institute of Scientific and Technical Information of China (English)

    郭小波

    2013-01-01

    Structure corrosion of aircraft fuselage is inevitable. This paper analyzes the causes of corrosion, and put out the measures and remedies how to prevent and delay the occurrence of corrosion.%  飞机机身结构腐蚀不可避免,本文通过分析腐蚀产生的原因,提出了如何预防和延缓腐蚀发生的措施及补救方法。

  14. Solar panel truss mounting systems and methods

    Energy Technology Data Exchange (ETDEWEB)

    Al-Haddad, Tristan Farris; Cavieres, Andres; Gentry, Russell; Goodman, Joseph; Nolan, Wade; Pitelka, Taylor; Rahimzadeh, Keyan; Brooks, Bradley; Lohr, Joshua; Crooks, Ryan; Porges, Jamie; Rubin, Daniel

    2016-06-28

    An exemplary embodiment of the present invention provides a solar panel truss mounting system comprising a base and a truss assembly coupled to the base. The truss assembly comprises a first panel rail mount, second panel rail mount parallel to the first panel rail mount, base rail mount parallel to the first and second panel rail mounts, and a plurality of support members. A first portion of the plurality of support members extends between the first and second panel rail mounts. A second portion of the plurality of support members extends between the first panel rail mount and the base rail mount. A third portion of the plurality of support members extends between the second panel rail mount and the base rail mount. The system can further comprise a plurality of connectors for coupling a plurality of photovoltaic solar panels to the truss assembly.

  15. Solar panel truss mounting systems and methods

    Energy Technology Data Exchange (ETDEWEB)

    Al-Haddad, Tristan Farris; Cavieres, Andres; Gentry, Russell; Goodman, Joseph; Nolan, Wade; Pitelka, Taylor; Rahimzadeh, Keyan; Brooks, Bradley; Lohr, Joshua; Crooks, Ryan; Porges, Jamie; Rubin, Daniel

    2015-10-20

    An exemplary embodiment of the present invention provides a solar panel truss mounting system comprising a base and a truss assembly coupled to the base. The truss assembly comprises a first panel rail mount, second panel rail mount parallel to the first panel rail mount, base rail mount parallel to the first and second panel rail mounts, and a plurality of support members. A first portion of the plurality of support members extends between the first and second panel rail mounts. A second portion of the plurality of support members extends between the first panel rail mount and the base rail mount. A third portion of the plurality of support members extends between the second panel rail mount and the base rail mount. The system can further comprise a plurality of connectors for coupling a plurality of photovoltaic solar panels to the truss assembly.

  16. Mobile response in web panels

    NARCIS (Netherlands)

    de Bruijne, M.A.; Wijnant, A.

    2014-01-01

    This article investigates unintended mobile access to surveys in online, probability-based panels. We find that spontaneous tablet usage is drastically increasing in web surveys, while smartphone usage remains low. Further, we analyze the bias of respondent profiles using smartphones and tablets com

  17. ASIST 2003: Part II: Panels.

    Science.gov (United States)

    Proceedings of the ASIST Annual Meeting, 2003

    2003-01-01

    Forty-six panels address topics including women in information science; users and usability; information studies; reference services; information policies; standards; interface design; information retrieval; information networks; metadata; shared access; e-commerce in libraries; knowledge organization; information science theories; digitization;…

  18. Humid free efficient solar panel

    Science.gov (United States)

    Panjwani, Manoj Kumar; Panjwani, Suresh Kumar; Mangi, Fareed Hussain; Khan, Danish; Meicheng, Li

    2017-09-01

    The paper examines the impact of the humidity on the Solar panels which makes a space for the drastic variation in the power generated and makes the device less efficient. Humidity readily affects the efficiency of the solar cells and creates a minimal layer of water on its surface. It also decreases the efficiency by 10-20% of the total power output produced. Moreover, to handle this issue, all around characterized measures are required to be taken to guarantee the smooth working of the solar panels utilized in humid areas. In connection with this issue, Karachi, the biggest city of Pakistan which is located near the costal line touching Arabian Sea, was taken as a reference city to measure the humidity range. In Karachi, the average humidity lies between 25-70% (as per Pakistan Meteorological Department PMD), that indirectly leads in decreasing power acquired from a Solar Panel and develops various complexities for the solar system. The system on average experiences stability issues, such as those of power fluctuations etc., due to which, the whole solar system installed observes abnormal variations in acquired power. Silica Gel was used as a desiccant material in order to assure dryness over the solar panel. More than four experiments were conducted with the usage of water absorbent to improve the efficiency and to make system more power efficient.

  19. Microclimate boxes for panel paintings

    DEFF Research Database (Denmark)

    Wadum, Jørgen

    1998-01-01

    The use of microclimate boxes to protect vulnerable panel paintings is, therefore, not a new phenomenon of the past two or three decades. Rather, it has been a concern for conservators and curators to protect these objects of art at home and in transit since the end of the nineteenth century. The...

  20. Risk-based decisionmaking (Panel)

    Energy Technology Data Exchange (ETDEWEB)

    Smith, T.H.

    1995-12-31

    By means of a panel discussion and extensive audience interaction, explore the current challenges and progress to date in applying risk considerations to decisionmaking related to low-level waste. This topic is especially timely because of the proposed legislation pertaining to risk-based decisionmaking and because of the increased emphasis placed on radiological performance assessments of low-level waste disposal.

  1. NAS Panel faults export controls

    Science.gov (United States)

    Katzoff, Judith A.

    A study prepared by a top-level panel says that current export controls on militarily sensitive U.S. technology may be “overcorrecting” previous weaknesses in that system, resulting in “a complex and confusing control system” that makes it more difficult for U.S. businesses to compete in international markets. Moreover, this control system has “an increasingly corrosive effect” on U.S. relations with allies. The panel recommended that the United States concentrate more effort on bringing about uniformity in the export control policies of countries belonging to the Coordinating Committee on Multilateral Export Controls (CoCom), i.e., most of the member nations in NATO (the North Atlantic Treaty Organization) and Japan.The 21-member panel was appointed by the Committee on Science, Engineering, and Public Policy (COSEPUP), a joint unit of the National Academy of Sciences (NAS), the National Academy of Engineering (NAE), and the Institute of Medicine (IOM). The panel, composed of administrators, researchers, and former government officials, was chaired by AGU member Lew Allen, Jr., director of the Jet Propulsion Laboratory (Pasadena, Calif.) and former chief of staff of the U.S. Air Force. Their report was supported by NAS funds, by a number of private organizations (including AGU), by the U.S. Departments of Commerce, Defense, Energy, and State, by the National Science Foundation, and by the National Aeronautics and Space Administration.

  2. EXTREMAL CONTROL FOR PHOTOVOLTAIC PANELS

    Directory of Open Access Journals (Sweden)

    Genevieve DAPHIN TANGUY

    2016-11-01

    Full Text Available In this paper a methodology for extremal control of photovoltaic panels has been designed through the use of an embedded polynomial controller using robust approaches and algorithms. Also, a framework for testing solar trackers in a hard ware in the loop (HIL configuration has been established. Efficient gradient based optimization methods were put in place in order to determine the parameters of the employed photovoltaic panel, as well as for computing the Maximum Power Point (MPP. Further a numerical RST controller has been computed in order to allow the panel to follow the movement of the sun to obtain a maximum energetic efficiency. A robustness analysis and correction procedure has been done on the RST polynomial algorithm. The hardware in the loop configuration allows for the development of a test and development platform which can be used for bringing improvements to the current design and also test different control approaches. For this, a microcontroller based solution was chosen. The achieved performances of the closed loop photovoltaic panel (PP system are validated in simulation using the MATLAB / SIMULINK environment and the WinPim & WinReg dedicated software. As it will be seen further in this paper, the extremal control of this design resides in a sequential set of computations used for obtaining the new Maximum Power Point at each change in the system.

  3. Panel: RFID Security and Privacy

    Science.gov (United States)

    Fu, Kevin

    The panel on RFID security and privacy included Ross Anderson, Jon Callas, Yvo Desmedt, and Kevin Fu. Topics for discussion included the "chip and PIN" EMV payment systems, e-Passports, "mafia" attacks, and RFID-enabled credit cards. Position papers by the panelists appear in the following pages, and the RFID-enabled credit card work appears separately in these proceedings.

  4. ASIST 2003: Part II: Panels.

    Science.gov (United States)

    Proceedings of the ASIST Annual Meeting, 2003

    2003-01-01

    Forty-six panels address topics including women in information science; users and usability; information studies; reference services; information policies; standards; interface design; information retrieval; information networks; metadata; shared access; e-commerce in libraries; knowledge organization; information science theories; digitization;…

  5. F-15B in on ramp with close-up of test panels covered with advanced spray-on foam insulation materia

    Science.gov (United States)

    1999-01-01

    Test panels covered with an advanced foam insulation material for the Space Shuttle's giant external fuel tank were test flown aboard an F-15B research aircraft at NASA's Dryden Flight Research Center, Edwards, Calif. Six panels were mounted on the left side of a heavily instrumented Flight Text Fixture mounted underneath the F-15B's fuselage. Insulation on this panel was finely machined over a horizontal rib structure to simulate in-line airflow past the tank; other panels had the ribs mounted vertically or had the insulation left in a rough as-sprayed surface. The tests were part of an effort by NASA's Marshall Space Flight Center to determine why small particles of the new insulation flaked off the tank on recent Shuttle missions. The tests with Dryden's F-15B were designed to replicate the pressure environment the Shuttle encounters during the first minute after launch. No noticeable erosion of the insulation material was noted after the flight experiment at Dryden.

  6. Use of Internet panels to conduct surveys.

    Science.gov (United States)

    Hays, Ron D; Liu, Honghu; Kapteyn, Arie

    2015-09-01

    The use of Internet panels to collect survey data is increasing because it is cost-effective, enables access to large and diverse samples quickly, takes less time than traditional methods to obtain data for analysis, and the standardization of the data collection process makes studies easy to replicate. A variety of probability-based panels have been created, including Telepanel/CentERpanel, Knowledge Networks (now GFK KnowledgePanel), the American Life Panel, the Longitudinal Internet Studies for the Social Sciences panel, and the Understanding America Study panel. Despite the advantage of having a known denominator (sampling frame), the probability-based Internet panels often have low recruitment participation rates, and some have argued that there is little practical difference between opting out of a probability sample and opting into a nonprobability (convenience) Internet panel. This article provides an overview of both probability-based and convenience panels, discussing potential benefits and cautions for each method, and summarizing the approaches used to weight panel respondents in order to better represent the underlying population. Challenges of using Internet panel data are discussed, including false answers, careless responses, giving the same answer repeatedly, getting multiple surveys from the same respondent, and panelists being members of multiple panels. More is to be learned about Internet panels generally and about Web-based data collection, as well as how to evaluate data collected using mobile devices and social-media platforms.

  7. Posture Alignment and Joining Test System for Large Aircraft Fuselages%大型飞机机身调姿与对接试验系统

    Institute of Scientific and Technical Information of China (English)

    邱宝贵; 蒋君侠; 毕运波; 方强; 王青; 詹建潮; 李江雄; 柯映林

    2011-01-01

    To realize numeralization, automation end flexibility during large aircraft components assembly, a novel posture alignment and joining test system for large aircraft fuselages is developed.Firstly, the working principle of the test system is introduced.Based on test-fuselages' measurement data from the laser tracker, test-fuselages' postures are calculated by integrated management system, and several three coordinate numerical control Iocalizers are driven to move harmoniously by control system, to achieve test-fuselages' posture alignment end joining.Secondly, the kinematics model for the posture alignment system is established.The relevant software, including integrated menagement system, measure system and control system, are developed end integrated on the basis of the hardware platform.Finally, the test system is applied to simulate test-fuselages' posture alignment and joining.Experimental results show that test-fuselages' position alignment precision is better than 0.09 mm, and test-fuselages' posture alignment precision is better than 0.000 5*.Some technologies of the test system have been successfully applied in several national key projects, which cen greatly improve the quality and efficiency of the aircraft assembly.%为实现飞机大部件装配过程的数字化、自动化和柔性化,研制了大型飞机机身调姿与对接试验系统.阐述了该系统的工作原理,通过激光跟踪仪测量试验机身上的检测点,集成管理系统计算试验机身的位姿,控制系统驱动多个三坐标数控定位器协同运动,实现试验机身的调姿与对接.建立了位姿调整机构的运动学模型,针对构建的硬件平台完成了包括集成管理系统、测量系统和控制系统在内的软件开发与集成,并对系统的性能进行了测试.试验结果表明,试验机身的位置调整精度优于0.09 mm,姿态调整精度优于0.000 5°.试验系统涉及的若干关键技术已成功应用于多项国家重点型号工

  8. El Salvador - Rural Electrification - Solar Panels

    Data.gov (United States)

    Millennium Challenge Corporation — This is a summative qualitative performance evaluation (PE) of the solar panel component of the solar panel component of the RE Sub-Activity. The final report will...

  9. Blue Ribbon Panel Report - BRP - Cancer Moonshot

    Science.gov (United States)

    The Blue Ribbon Panel Report outlines 10 recommendations to accelerate progress against cancer. The panel was established to ensure that the Cancer Moonshot's approaches are grounded in the best science.

  10. Blue Ribbon Panel 2016 Video Playlist

    Science.gov (United States)

    Blue Ribbon Panel members discuss recommendations from the panel report that was presented to the National Cancer Advisory Board on September 7, 2016. The playlist includes an overview video and 10 videos on the specific recommendations.

  11. Effect of microencapsulated phase change material in sandwich panels

    Energy Technology Data Exchange (ETDEWEB)

    Castellon, Cecilia; Medrano, Marc; Roca, Joan; Cabeza, Luisa F. [GREA Innovacio Concurrent, Edifici CREA, Universitat de Lleida, Pere de Cabrera s/n, 25001 Lleida (Spain); Navarro, Maria E.; Fernandez, Ana I. [Departamento de Ciencias de los Materiales e Ingenieria Metalurgica, Universitat de Barcelona, Marti i Franques 1, 08028 Barcelona (Spain); Lazaro, Ana; Zalba, Belen [Instituto de Investigacion en Ingenieria de Aragon, I3A, Grupo de Ingenieria Termica y Sistemas Energeticos (GITSE), Dpto. Ingenieria Mecanica, Area de Maquinas y Motores Termicos, Universidad de Zaragoza, Campus Politecnico Rio Ebro, Edificio ' ' Agustin de Betancourt,' ' Maria de Luna s/n, 50018 Zaragoza (Spain)

    2010-10-15

    Sandwich panels are a good option as building materials, as they offer excellent characteristics in a modular system. The goal of this study was to demonstrate the feasibility of using the microencapsulated PCM (Micronal BASF) in sandwich panels to increase their thermal inertia and to reduce the energy demand of the final buildings. In this paper, to manufacture the sandwich panel with microencapsulated PCM three different methods were tested. In case 1, the PCM was added mixing the microencapsulated PCM with one of the components of the polyurethane. In the other two cases, the PCM was added either a step before (case 2) or a step after (case 3) to the addition of the polyurethane to the metal sheets. The results show that in case 1 the effect of PCM was overlapped by a possible increase in thermal conductivity, but an increase of thermal inertia was found in case 3. In case 2, different results were obtained due to the poor distribution of the PCM. Some samples showed the effect of the PCM (higher thermal inertia), and other samples results were similar to the conventional sandwich panel. In both cases (2 and 3), it is required to industrialize the process to improve the results. (author)

  12. Grounds of two positions photovoltaic panels

    OpenAIRE

    Castán Fortuño, Fernando

    2008-01-01

    The objective of this Master Thesis is to find the optimum positioning for a two positions photovoltaic panel. Hence, it will be implemented a model in order to optimize the energy of the sun that the photovoltaic panel is receiving by its positioning. Likewise this project will include the comparison with other photovoltaic panel systems as the single position photovoltaics panels. Ultimately, it is also going to be designed a system array for the optimized model of two positions photovoltai...

  13. Lightweight composites for modular panelized construction

    Science.gov (United States)

    Vaidya, Amol S.

    Rapid advances in construction materials technology have enabled civil engineers to achieve impressive gains in the safety, economy, and functionality of structures built to serve the common needs of society. Modular building systems is a fast-growing modern, form of construction gaining recognition for its increased efficiency and ability to apply modern technology to the needs of the market place. In the modular construction technique, a single structural panel can perform a number of functions such as providing thermal insulation, vibration damping, and structural strength. These multifunctional panels can be prefabricated in a manufacturing facility and then transferred to the construction site. A system that uses prefabricated panels for construction is called a "panelized construction system". This study focuses on the development of pre-cast, lightweight, multifunctional sandwich composite panels to be used for panelized construction. Two thermoplastic composite panels are proposed in this study, namely Composite Structural Insulated Panels (CSIPs) for exterior walls, floors and roofs, and Open Core Sandwich composite for multifunctional interior walls of a structure. Special manufacturing techniques are developed for manufacturing these panels. The structural behavior of these panels is analyzed based on various building design codes. Detailed descriptions of the design, cost analysis, manufacturing, finite element modeling and structural testing of these proposed panels are included in this study in the of form five peer-reviewed journal articles. The structural testing of the proposed panels involved in this study included flexural testing, axial compression testing, and low and high velocity impact testing. Based on the current study, the proposed CSIP wall and floor panels were found satisfactory, based on building design codes ASCE-7-05 and ACI-318-05. Joining techniques are proposed in this study for connecting the precast panels on the construction

  14. Giant Magnetostrictive Material Exciter for Panel Loudspeaker

    Institute of Scientific and Technical Information of China (English)

    WANG Rui; ZHANG Yong-fa

    2008-01-01

    The exciter component in a panel loudspeaker has a profound effect on the overall performance of the system.The equivalent circuit analysis of the combination of giant magnetostrictive material exciter and distributed mode panel is introduced and how exciter parameters influence panel lffudspeaker's performance is discussed.NumericaI predictions are given in order to show how these influences are manifested.

  15. Recent Discoveries on Antwerp Panel Makers' Marks

    DEFF Research Database (Denmark)

    Wadum, Jørgen

    1993-01-01

    There still exist today uncertainties and misunderstandings in our interpretation of panel makers' marks from early 17th century Antwerp. In the future, panel marks and the panels on which they can be found will certainly render much more information concerning the technology of that time. Still...

  16. Bamboo-based Panels for Structural Applications

    Institute of Scientific and Technical Information of China (English)

    CHENXuhe; WANGZheng

    2005-01-01

    With technical assistance from INBAR and the Research Institute of Wood Industry of the Chinese Academy of Forestry, the construction of the Pingbian Primary School was completed in 2004,where bamboo plywood panels and laminated beams were used for the roof trusses, sheathing boards and wall panels. This is the first time that bamboo-based panels are used for structural applications.

  17. Noise reduction in double-panel structures by cavity and panel resonance control

    NARCIS (Netherlands)

    Ho, J.-H.; Berkhoff, A.P

    2011-01-01

    This paper presents an investigation of the cavity and the panel resonance control in a double‐panel structure. The double‐panel structure, which consists of two panels with air in the gap, is widely adopted in many applications such as aerospace due to its light weight and effective transmission‐lo

  18. Panel 4 - applications to transportation

    Energy Technology Data Exchange (ETDEWEB)

    Nichols, F. [Argonne National Lab., IL (United States); Au, J. [Sundstrand Aerospace, Rockford, IL (United States); Bhattacharya, R. [Universal Energy Systems, Inc., Dayton, OH (United States); Bhushan, B. [Ohio State Univ., Columbus (United States); Blunier, D. [Caterpillar, Inc., Peoria, IL (United States); Boardman, B. [Deere & Co., Moline, IL (United States); Brombolich, L. [Compu-Tec Engineering, Chesterfield, MO (United States); Davidson, J. [Vanderbilt Univ., Nashville, TN (United States); Graham, M. [Northwestern Univ., Evanston, IL (United States); Hakim, N. [Detroit Diesel Corp., MI (United States); Harris, K. [Dubbeldee Harris Diamond Corp., Mt. Arlington, NJ (United States); Hay, R. [Norton Diamond Film, Northboro, MA (United States); Herk, L. [Southwest Research Inst., Southfield, MI (United States); Hojnacki, H.; Rourk, D. [Intelligent Structures Incorporated, Canton, MI (United States); Kamo, R. [Adiabatics, Inc., Columbus, IN (United States); Nieman, B. [Allied-Signal Inc., Des Plaines, IL (United States); O`Neill, D. [3M, St. Paul, MN (United States); Peterson, M.B. [Wear Sciences, Arnold, MD (United States); Pfaffenberger, G. [Allison Gas Turbine, Indianapolis, IN (United States); Pryor, R.W. [Wayne State Univ., Detroit, MI (United States); Russell, J. [Superconductivity Publications, Inc., Somerset, NJ (United States); Syniuta, W. [Advanced Mechanical Technology, Inc., Newton, MA (United States); Tamor, M. [Ford Motor Co., Dearborn, MI (United States); Vojnovich, T. [Dept. of Energy, Washington, DC (United States); Yarbrough, W. [Pennsylvania State Univ., University Park (United States); Yust, C.S. [Oak Ridge National Lab., TN (United States)

    1993-01-01

    The aim of this group was to compile a listing of current and anticipated future problem areas in the transportation industry where the properties of diamond and DLC films make them especially attractive and where the panel could strongly endorse the establishment of DOE/Transportation Industry cooperative research efforts. This section identifies the problem areas for possible applications of diamond/DLC technology and presents indications of current approaches to these problems.

  19. Solar Cells and Solar Panels

    Science.gov (United States)

    1977-04-01

    TO CATALOG THIS DATA IN THE FORM OF A MODELo THE PRESENT DATA CAN BE MADE TO FIT A P-N JUNCTION WITH PHOTOCONDUCTIVE SERIES AND SHUNT RESISTANCES...TO THE SUN. ANALYSIS OF THE APPARENT MOTION OF THE SUN, WIND EFFECTS, PANEL ORIENTATION, SUN SENSING , AND BASIC SYSTEM CONFIGURATIONS ARE INCLUDED IN...DESIGN REQUIREMENTS LED TO SPECIFICATION OF A TWO-DEGREE-OF- FREEDOM GEARLESS MECHANISM INCORPORATING SUN SENSING , DIRECT SHAFT TORQUINGs AND POWER

  20. Striations in Plasma Display Panel

    Institute of Scientific and Technical Information of China (English)

    OUYANG Ji-Ting; CAO Jing; MIAO Jin-Song

    2005-01-01

    @@ The phenomenon of striation has been investigated experimentally in a macroscopic ac-plasma display panel (PDP). The relationship between the characteristics of striation and the operation conditions including voltage, frequency, rib, and electrode configuration, etc is obtained experimentally. The origin of the striations is considered to be the ionization waves in the transient positive column near the dielectric surface in the anode area during the discharge, and the perturbation is caused by resonance kinetic effects in inert gas.

  1. Method of forming oxide coatings. [for solar collector heating panels

    Science.gov (United States)

    Mcdonald, G. E. (Inventor)

    1983-01-01

    This invention is concerned with an improved plating process for covering a substrate with a black metal oxide film. The invention is particularly directed to making a heating panel for a solar collector. A compound is electrodeposited from an aqueous solution containing cobalt metal salts onto a metal substrate. This compound is converted during plating into a black, highly absorbing oxide coating which contains hydrated oxides. This is achieved by the inclusion of an oxidizing agent in the plating bath. The inclusion of an oxidizing agent in the plating bath is contrary to standard electroplating practice. The hydrated oxides are converted to oxides by treatment in a hot bath, such as boiling water. An oxidizing agent may be added to the hot liquid treating bath.

  2. Panel urges cloning ethics boards

    Energy Technology Data Exchange (ETDEWEB)

    Marshall, E.

    1997-01-03

    A 7-month review of the system that guides U.S. policy on the ethical, legal, and social issues (ELSI) of the Human Genome Project has concluded that it is time for a radical overhaul. A report completed last month recommends that a high-level policy board be created in the office of the Secretary of Health and Human Services to help develop policies on such sensitive issues as genetic privacy, antidiscrimination legislation, public education on genetic risks, and the regulation of genetic testing. If accepted, the proposal-from a review panel chaired by attorney Mark Rothstein of the University of Houston and geneticist M. Anne Spence of the University of California, Irvine-would create a new panel of 15 to 18 members to serve as {open_quotes}a public forum for discussion of ... critical issues.{close_quotes} This panel would replace the current advisory body, known as the ELSI Working Group, and end what the report calls a {open_quotes}discordance{close_quotes} between the broad scope of the Working Group and the {open_quotes}very limited focus{close_quotes} of the research program under which it operates.

  3. Analytical comparison of three stiffened panel concepts

    Science.gov (United States)

    Maloney, Jill M.; Wu, K. Chauncey; Robinson, James C.

    1995-01-01

    Three stiffened panel concepts are evaluated to find optimized designs for integral stiffeners in the barrels of Reusable Launch Vehicle fuel tanks. The three panel concepts considered are a T-stiffened panel, a panel with one blade stiffener centered between each pair of T-stiffeners, and a panel with two blade stiffeners equally spaced between each pair of T-stiffeners. The panels are optimized using PASCO for a range of compressive loads, and the computed areal weight for each panel is used to compare the concepts and predict tank weights. The areal weight of the T-stiffened panel with one blade is up to seven-percent lower than the other panel concepts. Two tank construction methods are compared for a representative tank design with three barrels. In the first method, 45-degree circumferential sections of a barrel are each designed to carry the same maximum load in the barrel. In the second method, each barrel section is designed for the maximum load in that section. Representative tanks designed with the first method are over 250 lb heavier than tanks designed using the second method. Optimized panel designs and areal weights are also computed for variation of the nominal panel length and skin thickness.

  4. Highly stretchable, transparent ionic touch panel

    Science.gov (United States)

    Kim, Chong-Chan; Lee, Hyun-Hee; Oh, Kyu Hwan; Sun, Jeong-Yun

    2016-08-01

    Because human-computer interactions are increasingly important, touch panels may require stretchability and biocompatibility in order to allow integration with the human body. However, most touch panels have been developed based on stiff and brittle electrodes. We demonstrate an ionic touch panel based on a polyacrylamide hydrogel containing lithium chloride salts. The panel is soft and stretchable, so it can sustain a large deformation. The panel can freely transmit light information because the hydrogel is transparent, with 98% transmittance for visible light. A surface-capacitive touch system was adopted to sense a touched position. The panel can be operated under more than 1000% areal strain without sacrificing its functionalities. Epidermal touch panel use on skin was demonstrated by writing words, playing a piano, and playing games.

  5. Flat panel display - Impurity doping technology for flat panel displays

    Energy Technology Data Exchange (ETDEWEB)

    Suzuki, Toshiharu [Advanced Technology Planning, Sumitomo Eaton Nova Corporation, SBS Tower 9F, 10-1, Yoga 4-chome, Setagaya-ku, 158-0097 Tokyo (Japan)]. E-mail: suzuki_tsh@senova.co.jp

    2005-08-01

    Features of the flat panel displays (FPDs) such as liquid crystal display (LCD) and organic light emitting diode (OLED) display, etc. using low temperature poly-Si (LTPS) thin film transistors (TFTs) are briefly reviewed comparing with other FPDs. The requirements for fabricating TFTs used for high performance FPDs and system on glass (SoG) are addressed. This paper focuses on the impurity doping technology, which is one of the key technologies together with crystallization by laser annealing, formation of high quality gate insulator and gate-insulator/poly-Si interface. The issues to be solved in impurity doping technology for state of the art and future TFTs are clarified.

  6. Flame Propagation Airworthiness Issue of Composite Fuselage%复合材料机身火焰蔓延适航问题研究

    Institute of Scientific and Technical Information of China (English)

    黄少麟; 张柱国

    2016-01-01

    大型运输类飞机机身大量采用复合材料将带来新的防火安全问题。本文首先介绍了A380、B787和A350飞机复合材料机身火焰蔓延专用条件差异,通过回顾隔音隔热材料火焰蔓延试验要求的立法历程,介绍了专用条件和符合性验证试验方法的介绍,分析了这些飞机的专用条件存在差异的原因。最后还归纳了复合材料火焰蔓延问题的后续研究方向,并对相关规章修订进行了展望,可供复合材料机身的设计和验证参考使用。%New fire safety issue would be introduced due to extensive use of composite on fuselage of large transport category airplane. Firstly this paper presented the difference of special conditions of composite fuselage flame propagation among A380,B787 and A350 airplanes. Then,through rulemaking history review of thermal/acoustic insulation material flame propagation test requirement,and introduction of special conditions and substantiation test method,analyzed the reason that the differences of these special conditions exist. Finally,subsequent research areas of composite flame propagation were summarized,and conclusion was provided with the future rulemaking of this issue. This paper could be a reference for the design and substantiation of composite fuselage.

  7. Potential environmental hazards of photovoltaic panel disposal: Discussion of Tammaro et al. (2015).

    Science.gov (United States)

    Sinha, Parikhit

    2017-02-05

    In their recent publication in Journal of Hazardous Materials (http://dx.doi.org/10.1016/j.jhazmat.2015.12.018), Tammaro et al. evaluate the potential environmental impacts of an illegal disposal scenario of photovoltaic panels in the European Union. Critical assumptions that underlie the study's conclusions would benefit from clarification. A scenario of photovoltaic panels finely crushed and abandoned in nature is not supported with field breakage data, in which photovoltaic panels remain largely intact with a number of glass fractures or cracks, as opposed to breakage into cm-scale pieces. Fate and transport analysis is necessary to evaluate how leachate transforms and disperses in moving from the point of emissions to the point of exposure, prior to making comparisons with drinking water limits. Some hazardous metal content has declined in both crystalline silicon and thin film panels, including a 50% decline in semiconductor material intensity in CdTe thin film panels (g CdTe/W) from 2009 to 2015. Waste laws, recycling requirements and minimum treatment standards under the EU WEEE Directive, and illegal disposal rates affect the accuracy of forecasts of releasable metal amounts from PV panels in Europe through 2050.

  8. Experimental investigation to evaluate the potential environmental hazards of photovoltaic panels.

    Science.gov (United States)

    Tammaro, Marco; Salluzzo, Antonio; Rimauro, Juri; Schiavo, Simona; Manzo, Sonia

    2016-04-05

    Recently the potential environmental hazard of photovoltaic modules together with their management as waste has attracted the attention of scientists. Particular concern is aroused by the several metals contained in photovoltaic panels whose potential release in the environment were scarcely investigated. Here, for the first time, the potential environmental hazard of panels produced in the last 30 years was investigated through the assessment of up to 18 releasable metals. Besides, the corresponding ecotoxicological effects were also evaluated. Experimental data were compared with the current European and Italian law limits for drinking water, discharge on soil and landfill inert disposal in order to understand the actual pollution load. Results showed that less than 3% of the samples respected all law limits and around 21% was not ecotoxic. By considering the technological evolutions in manufacturing, we have shown that during the years crystalline silicon panels have lower tendency to release hazardous metals with respect to thin film panels. In addition, a prediction of the amounts of lead, chromium, cadmium and nickel releasable from next photovoltaic waste was performed. The prevision up to 2050 showed high amounts of lead (30t) and cadmium (2.9t) releasable from crystalline and thin film panels respectively.

  9. Hypervelocity Impact Performance of Open Cell Foam Core Sandwich Panel Structures

    Science.gov (United States)

    Ryan, S.; Ordonez, E.; Christiansen, E. L.; Lear, D. M.

    2010-01-01

    Open cell metallic foam core sandwich panel structures are of interest for application in spacecraft micrometeoroid and orbital debris shields due to their novel form and advantageous structural and thermal performance. Repeated shocking as a result of secondary impacts upon individual foam ligaments during the penetration process acts to raise the thermal state of impacting projectiles ; resulting in fragmentation, melting, and vaporization at lower velocities than with traditional shielding configurations (e.g. Whipple shield). In order to characterize the protective capability of these structures, an extensive experimental campaign was performed by the Johnson Space Center Hypervelocity Impact Technology Facility, the results of which are reported in this paper. Although not capable of competing against the protection levels achievable with leading heavy shields in use on modern high-risk vehicles (i.e. International Space Station modules), metallic foam core sandwich panels are shown to provide a substantial improvement over comparable structural panels and traditional low weight shielding alternatives such as honeycomb sandwich panels and metallic Whipple shields. A ballistic limit equation, generalized in terms of panel geometry, is derived and presented in a form suitable for application in risk assessment codes.

  10. Automated solar panel assembly line

    Science.gov (United States)

    Somberg, H.

    1981-01-01

    The initial stage of the automated solar panel assembly line program was devoted to concept development and proof of approach through simple experimental verification. In this phase, laboratory bench models were built to demonstrate and verify concepts. Following this phase was machine design and integration of the various machine elements. The third phase was machine assembly and debugging. In this phase, the various elements were operated as a unit and modifications were made as required. The final stage of development was the demonstration of the equipment in a pilot production operation.

  11. The Conservation of Panel paintings

    DEFF Research Database (Denmark)

    Until the early 17th century almost all portable paintings were created on wood supports, including masterpieces by famous painters, ranging from Giotto to Dürer to Rembrandt. The structural conservation of these paintings requires specific knowledge and skills as the supports are susceptible...... to damage caused by unstable environmental conditions. Unfortunately, past structural interventions often caused significant damage due to insufficient knowledge of the behaviour of the wood panels, glue and paint layers. Over the last fifty years, the field has developed treatment strategies based...

  12. Optimum design of composite panel with photovoltaic-thermo module. Absorbing effect of cooling panel; Hikari netsu fukugo panel no saiteki sekkei. Reikyaku panel no kyunetsu koka

    Energy Technology Data Exchange (ETDEWEB)

    Sato, M.; Kikuchi, S.; Tani, T. [Science University of Tokyo, Tokyo (Japan); Kadotani, K.; Imaizumi, H. [Komatsu Ltd., Tokyo (Japan)

    1996-10-27

    The composite panel with photovoltaic-thermo module becomes higher in energy-saving than the conventional air-conditioning system by the independent radiational heating and cooling effect obtained when the generating panel using a solar cell module is combined with the heating and cooling panel using a thermo-element module. The output of a solar cell module can be directly used because the solar cell module operates in AC. This paper reports the relation between the absorbed value and power consumption of the cooling panel, while paying attention to the cooling panel. The performance coefficient of the maximum absorbed value from an non-absorbing substance to a cooling panel is 2 to 3. Assume that the cooling panel during non-adiabatic operation is operated using a solar cell module of 800 W/m{sup 2} in solar intensity and 15% in conversion efficiency. The cooling-surface temperature difference is 12.12 K, and the maximum absorbed value of a non-absorbing substance to a cooling panel is 39.12 W/m{sup 2}. The absorbed value of the outer temperature to the cooling panel is 74.4 W/m{sup 2}, and each performance coefficient is 3.26 and 0.62. The absorbed value must be calculated for evaluation from the cooling-surface temperature difference measured directly from the cooling panel. 4 refs., 8 figs., 1 tab.

  13. Experimental and numerical analysis of defects in composite panels used in business aircrafts interior

    Science.gov (United States)

    Ruiz, Edu; Courteau-Godmaire, H.; Fotsing, R.; Billotte, C.; Levesque, M.

    2016-05-01

    This paper provides an optical characterization and numerical prediction of local deformations appearing on the visible side of composite sandwich panels used for interior furniture of business airplanes. During manufacturing of furniture panels, metallic inserts are bonded inside the sandwich panel using an epoxy adhesive. Surface defects appear on the visible side of the panels due to curing of the adhesive, but also because of temperature gradients and humidity during manufacturing and in service. This paper presents an optical characterization based on deflectometry principle, that allows qualitative and quantitative analyses of the surface deformations in 3-dimensions. In addition, this paper presents a parametric model based on finite elements to predict the formation of surface defects using ABAQUS. A comparison is presented between the experimental observations and numerical predictions with good agreement between them.

  14. Determining the microstructure and properties of magnesium aluminum composite panels by hot rolling and annealing

    Directory of Open Access Journals (Sweden)

    Zilong Zhao

    2016-09-01

    Full Text Available The researchers made magnesium aluminum composite panels by asymmetric metal packaging and studied rolling temperature, holding time, and high temperature heat treatment, such as short time and low temperatures over long periods of time parameters under the new preparation method. We tested the new magnesium aluminum composite panels' tensing properties and bending performance by using scanning electric mirror and EDS. It is concluded that the new magnesium aluminum composite panels' elongation is 24% under the tensile strength of 260 MPa. Regarding performance when compared with other methods, traditional magnesium aluminum composite panels' elongation is 10%, which shows its advanced nature. At the same time, bending performance test showed that the combination of the composite board has higher performance, offering the reference value for the preparation of magnesium–aluminum composite plate.

  15. ROOFER Inventory Procedures and Inspection Manual for Metal Panel Roofing

    Science.gov (United States)

    2012-12-01

    DESIGN CATEGORY CODE : I I I I I I TYPE CONST • : p I FACILITY NUMBER : I I I I I I I LOCATION : USE : I YEAR BUILT: ROOF SECTIONS : A 1,097 SF...INST . NO.: I I I I I I DATE : I I AGENCY I I NST .: BUILDING NAME : BUILDING NUMBER : DESIGN ~-TEGORY CODE : I I I I I I TYPE CONST...oov.nstope Sioo lfM H o oruns8810d I ....... , or ocner Integrated S!¥oght S!Ons or de<trooouon PanetOefect SPH jOint botwoen_ skylight panol and

  16. Blank Panel Design of Integral Wing Skin Panels Based on Feature Mapping Methods

    Institute of Scientific and Technical Information of China (English)

    Wang; Junbiao; Zhang; Xianjie

    2007-01-01

    A blank panel design algorithm based on feature mapping methods for integral wing skin panels with supercritical airfoil surface is presented.The model of a wing panel is decomposed into features,and features of the panel are decomposed into information of location,direction,dimension and Boolean types.Features are mapped into the plane through optimal surface development algorithm.The plane panel is modeled by rebuilding the mapped features.Blanks of shot-peen forming panels are designed to identify the effectiveness of the methods.

  17. Structural evaluation of curved stiffened composite panels fabricated using a THERM-Xsm process

    Science.gov (United States)

    Kassapoglou, Christos; Dinicola, Albert J.; Chou, Jack C.; Deaton, Jerry W.

    1991-01-01

    The use of composites in aircraft structures is often limited by material and manufacturing costs which, for some designs and applications, are prohibitively high. To increase the frequency of application of composites in primary airframe components alternative manufacturing processes are sought that reduce cost and/or enhance structural efficiency. One alternative process involves the use of THERM-Xsm as the pressure transfer medium during autoclave curing. THERM-Xsm, a silicon-based flow able polymer which behaves like a liquid under autoclave presssure, transmits quasi-hydrostatic pressure to all contacting surfaces of the part to be cured. Once the autoclave pressure is relieved, THERM-Xsm reverts back to the powdery solid state and can be reused many times. The THERM-Xsm process to be evaluated is depicted and consists of (1) enclosing the tool and part to be cured by a set of frames that create a box, (2) pouring THERM-Xsm powder onto the part and filling the box, and (3) placing a vacuum bag over the box assembly. In this program, a separating non-porous film (Teflon) was placed between the part to be cured and THERM-Xsm powder to avoid any contamination. The use of THERM-Xsm has two significant advantages over conventional manufacturing procedures. First, it eliminates complicated hard tooling since it guarantees uniform pressure transfer and thus, good compaction at complex structural details (such as frame-stiffener intersections and corners). Second, it greatly simplifies vacuum bagging, since once the part to be cured is covered by THERM-Xsm powder, the vacuum bag need only conform to a relatively flat shape reducing significantly the number of pleats required. A program is on-going at Sikorsky Aircraft to evaluate the structural performance of complex composite fuselage structures made with this THERM-Xsm process and to quantify the impact of THERM-Xsm on manufacturing labor hours and cost. The program involves fuselage panel optimization analysis, a

  18. Solar-Panel Dust Accumulation and Cleanings

    Science.gov (United States)

    2005-01-01

    Air-fall dust accumulates on the solar panels of NASA's Mars Exploration Rovers, reducing the amount of sunlight reaching the solar arrays. Pre-launch models predicted steady dust accumulation. However, the rovers have been blessed with occasional wind events that clear significant amounts of dust from the solar panels. This graph shows the effects of those panel-cleaning events on the amount of electricity generated by Spirit's solar panels. The horizontal scale is the number of Martian days (sols) after Spirit's Jan. 4, 2005, (Universal Time) landing on Mars. The vertical scale indicates output from the rover's solar panels as a fraction of the amount produced when the clean panels first opened. Note that the gradual declines are interrupted by occasional sharp increases, such as a dust-cleaning event on sol 420.

  19. Castro Valley High School's Solar Panels

    Science.gov (United States)

    Lew, A.; Ham, S.; Shin, Y.; Yang, W.; Lam, J.

    2014-12-01

    Solar panels are photovoltaic cells that are designed to convert the sun's kinetic energy to generate usable energy in the form of electricity. Castro Valley High School has tried to offset the cost of electricity by installing solar panels, costing the district approximately 3.29 million dollars, but have been installed incorrectly and are not operating at peak efficency. By using trigonometry we deduced that Castro Valley High School's south facing solar panels were at an incline of 10o and that the east and west facing solar panels are at an incline of 5o. By taking the averages of the optimum angles for the months of September through May, roughly when school is in session, we found that the optimum angle for south facing solar panels should be roughly 46o. This shows that Castro Valley High School has not used it's budget to its full potential due to the fact that the solar panels were haphazardly installed.

  20. Solar-Panel Dust Accumulation and Cleanings

    Science.gov (United States)

    2005-01-01

    Air-fall dust accumulates on the solar panels of NASA's Mars Exploration Rovers, reducing the amount of sunlight reaching the solar arrays. Pre-launch models predicted steady dust accumulation. However, the rovers have been blessed with occasional wind events that clear significant amounts of dust from the solar panels. This graph shows the effects of those panel-cleaning events on the amount of electricity generated by Spirit's solar panels. The horizontal scale is the number of Martian days (sols) after Spirit's Jan. 4, 2005, (Universal Time) landing on Mars. The vertical scale indicates output from the rover's solar panels as a fraction of the amount produced when the clean panels first opened. Note that the gradual declines are interrupted by occasional sharp increases, such as a dust-cleaning event on sol 420.

  1. Geothermal Technologies Program Blue Ribbon Panel Recommendations

    Energy Technology Data Exchange (ETDEWEB)

    none,

    2011-06-17

    The Geothermal Technologies Program assembled a geothermal Blue Ribbon Panel on March 22-23, 2011 in Albuquerque, New Mexico for a guided discussion on the future of geothermal energy in the United States and the role of the DOE Program. The Geothermal Blue Ribbon Panel Report captures the discussions and recommendations of the experts. An addendum is available here: http://www.eere.energy.gov/geothermal/pdfs/gtp_blue_ribbon_panel_report_addendum10-2011.pdf

  2. Panel discussion: Proposals for improving OCL

    OpenAIRE

    Brucker, Achim D.; Clark, Tony; Dania, Carolina; Georg, Geri; Gogolla, Martin; Jouault, Frederic; Teniente López, Ernest; Wolff, Burkhart

    2014-01-01

    During the panel session at the OCL workshop, the OCL community discussed, stimulated by short presentations by OCL experts, potential future extensions and improvements of the OCL. As such, this panel discussion continued the discussion that started at the OCL meeting in Aachen in 2013 and on which we reported in the proceedings of the last year's OCL workshop. This collaborative paper, to which each OCL expert contributed one section, summarises the panel discussion as well as describes the...

  3. Tabulated pressure measurements of a NASA supercritical-wing research airplane model with and without fuselage area-rule additions at Mach 0.25 to 1.00

    Science.gov (United States)

    Harris, C. D.; Bartlett, D. W.

    1972-01-01

    Basic pressure measurements were made on a 0.087-scale model of a supercritical wing research airplane in the Langley 8 foot transonic pressure tunnel at Mach numbers from 0.25 to 1.00 to determine the effects on the local aerodynamic loads over the wing and rear fuselage of area-rule additions to the sides of the fuselage. In addition, pressure measurements over the surface of the area-rule additions themselves were obtained at angles of sideslip of approximately - 5 deg, 0 deg, and 5 deg to aid in the structural design of the additions. Except for representative figures, results are presented in tabular form without analysis.

  4. Interagency Security Classification Appeals Panel (ISCAP) Decisions

    Data.gov (United States)

    National Archives and Records Administration — This online collection includes documents decided upon by the Interagency Security Classification Appeals Panel (ISCAP) starting in Fiscal Year 2012. The documents...

  5. Development of Electrostatically Clean Solar Array Panels

    Science.gov (United States)

    Stern, Theodore G.

    2000-01-01

    Certain missions require Electrostatically Clean Solar Array (ECSA) panels to establish a favorable environment for the operation of sensitive scientific instruments. The objective of this program was to demonstrate the feasibility of an ECSA panel that minimizes panel surface potential below 100mV in LEO and GEO charged particle environments, prevents exposure of solar cell voltage and panel insulating surfaces to the ambient environment, and provides an equipotential, grounded structure surrounding the entire panel. An ECSA panel design was developed that uses a Front Side Aperture-Shield (FSA) that covers all inter-cell areas with a single graphite composite laminate, composite edge clips for connecting the FSA to the panel substrate, and built-in tabs that interconnect the FSA to conductive coated coverglasses using a conductive adhesive. Analysis indicated the ability of the design to meet the ECSA requirements. Qualification coupons and a 0.5m x 0.5m prototype panel were fabricated and tested for photovoltaic performance and electrical grounding before and after exposure to acoustic and thermal cycling environments. The results show the feasibility of achieving electrostatic cleanliness with a small penalty in mass, photovoltaic performance and cost, with a design is structurally robust and compatible with a wide range of current solar panel technologies.

  6. Summary Report Panel 2: Regulatory Issues.

    Science.gov (United States)

    Johnson, Craig; Dolman, Sarah

    2016-01-01

    The Effects of Noise on Aquatic Life 2013 Conference convened four panels to discuss specific topics related to the effects of anthropogenic noise on aquatic ecosystems. The second of these four panels, the Regulatory Issues Panel, brought together several different perspectives: representatives of agencies responsible for regulating activities that introduce anthropogenic noise into aquatic ecosystems: representatives of the regulated industries, agencies, and consultancies that advise regulators and regulated industries; and nongovernmental organizations and other stakeholders with an interest in anthropogenic noise. The goal of the panel was to help develop a more productive relationship between these groups.

  7. Uncertainties in predicting solar panel power output

    Science.gov (United States)

    Anspaugh, B.

    1974-01-01

    The problem of calculating solar panel power output at launch and during a space mission is considered. The major sources of uncertainty and error in predicting the post launch electrical performance of the panel are considered. A general discussion of error analysis is given. Examples of uncertainty calculations are included. A general method of calculating the effect on the panel of various degrading environments is presented, with references supplied for specific methods. A technique for sizing a solar panel for a required mission power profile is developed.

  8. Bending moment of galvanized iron glass fiber sandwich panel

    Directory of Open Access Journals (Sweden)

    Gurustal Somnath Swamy

    2016-05-01

    Full Text Available The main objective of this project is to prepare a laminated with Galvanized iron thickness fractions, fiber volume fractions and orientation in the layers of GF were fabricated by hand lay-up method and evaluated for their bending moment properties of the sandwich panel using universal testing machine. This paper theoretically calculates the bending behavior of sandwich panel. The recent need to develop a new range of materials has resulted in the development of high performance lightweight composites with excellent properties. Metal– composite systems consist of alternating layers of metal and fiber-reinforced polymer composites which are bonded by an adhesive. Sandwich beams were tested under Air Bending. Stress-strain and stress-displacement were recorded by using AIMIL UTM. The beam face sheets exhibited a softening non-linearity on the bending side. Experimental results were in good agreement with predictions from simple models. On an overall basis, the sandwich panel exhibited better bending moment performance than the monolithic galvanized iron

  9. Laser illuminated flat panel display

    Energy Technology Data Exchange (ETDEWEB)

    Veligdan, J.T.

    1995-12-31

    A 10 inch laser illuminated flat panel Planar Optic Display (POD) screen has been constructed and tested. This POD screen technology is an entirely new concept in display technology. Although the initial display is flat and made of glass, this technology lends itself to applications where a plastic display might be wrapped around the viewer. The display screen is comprised of hundreds of planar optical waveguides where each glass waveguide represents a vertical line of resolution. A black cladding layer, having a lower index of refraction, is placed between each waveguide layer. Since the cladding makes the screen surface black, the contrast is high. The prototype display is 9 inches wide by 5 inches high and approximately I inch thick. A 3 milliwatt HeNe laser is used as the illumination source and a vector scanning technique is employed.

  10. Large Scale Glazed Concrete Panels

    DEFF Research Database (Denmark)

    Bache, Anja Margrethe

    2010-01-01

    Today, there is a lot of focus on concrete surface’s aesthitic potential, both globally and locally. World famous architects such as Herzog De Meuron, Zaha Hadid, Richard Meyer and David Chippenfield challenge the exposure of concrete in their architecture. At home, this trend can be seen...... existing buildings in and around Copenhagen that are covered with mosaic tiles or glazed tiles; buildings such as Nanna Ditzel’s House in Klareboderne, Arne Jacobsen’s gas station, Erik Møller’s Industriens Hus, Bent Helweg Møller’s Berlingske Hus, Arne Jacobsen’s Stellings Hus and Toms Chocolate Factories...... and finally Lene Tranberg and Bøje Lungård’s Elsinore water purification plant. These buildings have qualities that I would like applied, perhaps transformed or most preferably, if possible, interpreted anew, for the large glazed concrete panels I shall develop. The article is ended and concluded...

  11. Microclimate boxes for panel paintings

    DEFF Research Database (Denmark)

    Wadum, Jørgen

    1998-01-01

    The use of microclimate boxes to protect vulnerable panel paintings is, therefore, not a new phenomenon of the past two or three decades. Rather, it has been a concern for conservators and curators to protect these objects of art at home and in transit since the end of the nineteenth century....... The increased number of travelling exhibitions in recent years has heightened the need to protect paintings during circulation (Thomson 1961; Mecklenburg 1991). The use and design of microclimate boxes have been evolving since 1892. These boxes may be divided into three broad groups: those using an active...... buffer material to stabilize the internal RH, a more recent box containing no added buffer material, and, in recent times, boxes with an altered gas content. Another concern is the appearance (aesthetics) of the box....

  12. AQUEOUS HOMOGENEOUS REACTORTECHNICAL PANEL REPORT

    Energy Technology Data Exchange (ETDEWEB)

    Diamond, D.J.; Bajorek, S.; Bakel, A.; Flanagan, G.; Mubayi, V.; Skarda, R.; Staudenmeier, J.; Taiwo, T.; Tonoike, K.; Tripp, C.; Wei, T.; Yarsky, P.

    2010-12-03

    Considerable interest has been expressed for developing a stable U.S. production capacity for medical isotopes and particularly for molybdenum- 99 (99Mo). This is motivated by recent re-ductions in production and supply worldwide. Consistent with U.S. nonproliferation objectives, any new production capability should not use highly enriched uranium fuel or targets. Conse-quently, Aqueous Homogeneous Reactors (AHRs) are under consideration for potential 99Mo production using low-enriched uranium. Although the Nuclear Regulatory Commission (NRC) has guidance to facilitate the licensing process for non-power reactors, that guidance is focused on reactors with fixed, solid fuel and hence, not applicable to an AHR. A panel was convened to study the technical issues associated with normal operation and potential transients and accidents of an AHR that might be designed for isotope production. The panel has produced the requisite AHR licensing guidance for three chapters that exist now for non-power reactor licensing: Reac-tor Description, Reactor Coolant Systems, and Accident Analysis. The guidance is in two parts for each chapter: 1) standard format and content a licensee would use and 2) the standard review plan the NRC staff would use. This guidance takes into account the unique features of an AHR such as the fuel being in solution; the fission product barriers being the vessel and attached systems; the production and release of radiolytic and fission product gases and their impact on operations and their control by a gas management system; and the movement of fuel into and out of the reactor vessel.

  13. Hypervelocity Impact Performance of Open Cell Foam Core Sandwich Panel Structures

    Science.gov (United States)

    Ryan, Shannon; Christiansen, Eric; Lear, Dana

    2009-01-01

    Metallic foams are a relatively new class of materials with low density and novel physical, mechanical, thermal, electrical and acoustic properties. Although incompletely characterized, they offer comparable mechanical performance to traditional spacecraft structural materials (i.e. honeycomb sandwich panels) without detrimental through-thickness channeling cells. There are two competing types of metallic foams: open cell and closed cell. Open cell foams are considered the more promising technology due to their lower weight and higher degree of homogeneity. Leading micrometeoroid and orbital debris shields (MMOD) incorporate thin plates separated by a void space (i.e. Whipple shield). Inclusion of intermediate fabric layers, or multiple bumper plates have led to significant performance enhancements, yet these shields require additional non-ballistic mass for installation (fasteners, supports, etc.) that can consume up to 35% of the total shield weight [1]. Structural panels, such as open cell foam core sandwich panels, that are also capable of providing sufficient MMOD protection, represent a significant potential for increased efficiency in hypervelocity impact shielding from a systems perspective through a reduction in required non-ballistic mass. In this paper, the results of an extensive impact test program on aluminum foam core sandwich panels are reported. The effect of pore density, and core thickness on shielding performance have been evaluated over impact velocities ranging from 2.2 - 9.3 km/s at various angles. A number of additional tests on alternate sandwich panel configurations of comparable-weight have also been performed, including aluminum honeycomb sandwich panels (see Figure 1), Nomex honeycomb core sandwich panels, and 3D aluminum honeycomb sandwich panels. A total of 70 hypervelocity impact tests are reported, from which an empirical ballistic limit equation (BLE) has been derived. The BLE is in the standard form suitable for implementation in

  14. Circuits in the Sun: Solar Panel Physics

    Science.gov (United States)

    Gfroerer, Tim

    2013-01-01

    Typical commercial solar panels consist of approximately 60 individual photovoltaic cells connected in series. Since the usual Kirchhoff rules apply, the current is uniform throughout the circuit, while the electric potential of the individual devices is cumulative. Hence, a solar panel is a good analog of a simple resistive series circuit, except…

  15. Dynamic spatial panels : models, methods, and inferences

    NARCIS (Netherlands)

    Elhorst, J. Paul

    This paper provides a survey of the existing literature on the specification and estimation of dynamic spatial panel data models, a collection of models for spatial panels extended to include one or more of the following variables and/or error terms: a dependent variable lagged in time, a dependent

  16. 49 CFR 845.22 - Technical panel.

    Science.gov (United States)

    2010-10-01

    ... 49 Transportation 7 2010-10-01 2010-10-01 false Technical panel. 845.22 Section 845.22... Technical panel. The Director, Bureau of Accident Investigation, or the Director, Bureau of Field Operations, shall designate members of the Board's technical staff to participate in the hearing and...

  17. Pairwise difference estimation of linear panel data

    NARCIS (Netherlands)

    Aquaro, M.

    2013-01-01

    Panel data sets, also called longitudinal data sets, are sets of data where the same units (for instance individuals, firms, or countries) are observed more than one time. Models that exploit the specific structure of these data sets are called panel data models. One of the main advantage of using t

  18. Panel discussion: The future of IR astronomy

    Science.gov (United States)

    Caroff, Lawrence J.

    1995-01-01

    A panel discussion was held on the future of IR astronomy. The chairman gave a brief introduction to current planned programs for NASA and other space agencies, followed by short contributions from the six panel members on a variety of special topics. After that, a short question and answer session was held.

  19. 7 CFR 2902.19 - Composite panels.

    Science.gov (United States)

    2010-01-01

    ... minimum biobased contents are: (1) Plastic lumber composite panels—23 percent. (2) Acoustical composite... AGRICULTURE GUIDELINES FOR DESIGNATING BIOBASED PRODUCTS FOR FEDERAL PROCUREMENT Designated Items § 2902.19 Composite panels. (a) Definitions. (1) Plastic lumber composite panels. Engineered products suitable for...

  20. MoMLA: From Panel to Gallery

    Science.gov (United States)

    Vitanza, Victor, Ed.; Kuhn, Virginia, Ed.

    2013-01-01

    The work presented here in this "Panel to Gallery" was originally produced and assembled for the 2012 Modern Language Association Conference in Seattle, Washington. Similar to "From Gallery to Webtext", the event Victor curated for the 2006 College Composition and Communication Conference, this "Panel to Gallery" event at MLA set aside the…

  1. 76 FR 23845 - Arts Advisory Panel

    Science.gov (United States)

    2011-04-28

    ... ARTS AND THE HUMANITIES National Endowment for the Arts Arts Advisory Panel Pursuant to Section 10(a)(2... meeting of the Arts Advisory Panel to the National Council on the Arts will be held at the Nancy Hanks..., evaluation, and recommendations on financial assistance under the National Foundation on the Arts and...

  2. 77 FR 27803 - Arts Advisory Panel Meeting

    Science.gov (United States)

    2012-05-11

    ... ARTS AND THE HUMANITIES Arts Advisory Panel Meeting AGENCY: National Endowment for the Arts, National Foundation on the Arts and Humanities. ACTION: Notice of meeting. SUMMARY: Pursuant to Section 10(a)(2) of... meetings of the Arts Advisory Panel to the National Council on the Arts will be held at the Nancy...

  3. 78 FR 17942 - Arts Advisory Panel Meeting

    Science.gov (United States)

    2013-03-25

    ... ARTS AND THE HUMANITIES Arts Advisory Panel Meeting AGENCY: National Endowment for the Arts, National Foundation on the Arts and Humanities. ACTION: Notice of meetings. SUMMARY: Pursuant to Section 10(a)(2) of... meetings of the Arts Advisory Panel to the National Council on the Arts will be held at the Nancy...

  4. 78 FR 5213 - Arts Advisory Panel Meeting

    Science.gov (United States)

    2013-01-24

    ... ARTS AND THE HUMANITIES Arts Advisory Panel Meeting AGENCY: National Endowment for the Arts, National Foundation on the Arts and Humanities. ACTION: Notice of meeting. SUMMARY: Pursuant to Section 10(a)(2) of... meeting of the Arts Advisory Panel to the National Council on the Arts will be held at the Nancy...

  5. 76 FR 3677 - Arts Advisory Panel

    Science.gov (United States)

    2011-01-20

    ... ARTS AND THE HUMANITIES National Endowment for the Arts Arts Advisory Panel Pursuant to Section 10(a)(2... meeting of the Arts Advisory Panel to the National Council on the Arts will be held at the Nancy Hanks..., discussion, evaluation, and recommendations on financial assistance under the National Foundation on the...

  6. 78 FR 59978 - Arts Advisory Panel Meeting

    Science.gov (United States)

    2013-09-30

    ... ARTS AND THE HUMANITIES Arts Advisory Panel Meeting AGENCY: National Endowment for the Arts, National Foundation on the Arts and Humanities. ACTION: Notice of meeting. SUMMARY: Pursuant to Section 10(a)(2) of... meeting of the Arts Advisory Panel to the National Council on the Arts will be held at the Nancy...

  7. 78 FR 42982 - Arts Advisory Panel Meeting

    Science.gov (United States)

    2013-07-18

    ... ARTS AND THE HUMANITIES Arts Advisory Panel Meeting AGENCY: National Endowment for the Arts, National Foundation on the Arts and Humanities. ACTION: Notice of Meetings SUMMARY: Pursuant to Section 10(a)(2) of... the Arts Advisory Panel to the National Council on the Arts will be held at the Nancy Hanks...

  8. 78 FR 28244 - Arts Advisory Panel Meeting

    Science.gov (United States)

    2013-05-14

    ... ARTS AND THE HUMANITIES Arts Advisory Panel Meeting AGENCY: National Endowment for the Arts, National Foundation on the Arts and Humanities. ACTION: Notice of Meetings SUMMARY: Pursuant to Section 10(a)(2) of... meetings of the Arts Advisory Panel to the National Council on the Arts will be held at the Nancy...

  9. 77 FR 41808 - Arts Advisory Panel Meeting

    Science.gov (United States)

    2012-07-16

    ... ARTS AND THE HUMANITIES Arts Advisory Panel Meeting AGENCY: National Endowment for the Arts, National Foundation on the Arts and Humanities. ACTION: Notice of meeting. SUMMARY: Pursuant to Section 10(a)(2) of... meetings of the Arts Advisory Panel to the National Council on the Arts will be held at the Nancy...

  10. 76 FR 50499 - Arts Advisory Panel

    Science.gov (United States)

    2011-08-15

    ... ARTS AND THE HUMANITIES National Endowment for the Arts Arts Advisory Panel Pursuant to Section 10(a)(2... meeting of the Arts Advisory Panel to the National Council on the Arts will be held at the Nancy Hanks... financial assistance under the National Foundation on the Arts and the Humanities Act of 1965, as...

  11. 78 FR 50451 - Arts Advisory Panel Meeting

    Science.gov (United States)

    2013-08-19

    ... ARTS AND THE HUMANITIES Arts Advisory Panel Meeting AGENCY: National Endowment for the Arts, National Foundation on the Arts and Humanities. ACTION: Notice of Meetings. SUMMARY: Pursuant to Section 10(a)(2) of... meeting of the Arts Advisory Panel to the National Council on the Arts will be held at the Nancy...

  12. 78 FR 26399 - Arts Advisory Panel Meeting

    Science.gov (United States)

    2013-05-06

    ... ARTS AND THE HUMANITIES Arts Advisory Panel Meeting AGENCY: National Endowment for the Arts, National Foundation on the Arts and Humanities. ACTION: Notice of Meeting. SUMMARY: Pursuant to Section 10(a)(2) of... meeting of the Arts Advisory Panel to the National Council on the Arts will be held by teleconference...

  13. 76 FR 63664 - Arts Advisory Panel

    Science.gov (United States)

    2011-10-13

    ... Doc No: 2011-26421] NATIONAL FOUNDATION ON THE ARTS AND THE HUMANITIES National Endowment for the Arts Arts Advisory Panel Pursuant to Section 10(a)(2) of the Federal Advisory Committee Act (Pub. L. 92-463), as amended, notice is hereby given that thirteen meetings of the Arts Advisory Panel to the...

  14. 78 FR 21978 - Arts Advisory Panel Meeting

    Science.gov (United States)

    2013-04-12

    ... ARTS AND THE HUMANITIES Arts Advisory Panel Meeting AGENCY: National Endowment for the Arts, National Foundation on the Arts and Humanities. ACTION: Notice of meeting. SUMMARY: Pursuant to Section 10(a)(2) of... meeting of the Arts Advisory Panel to the National Council on the Arts will be held at the Nancy...

  15. 77 FR 49026 - Arts Advisory Panel Meeting

    Science.gov (United States)

    2012-08-15

    ... ARTS AND THE HUMANITIES Arts Advisory Panel Meeting AGENCY: National Endowment for the Arts, National Foundation on the Arts and Humanities. ACTION: Notice of meeting. SUMMARY: Pursuant to Section 10(a)(2) of... meeting of the Arts Advisory Panel to the National Council on the Arts will be held at the Nancy...

  16. 78 FR 68099 - Arts Advisory Panel Meeting

    Science.gov (United States)

    2013-11-13

    ... ARTS AND THE HUMANITIES Arts Advisory Panel Meeting AGENCY: National Endowment for the Arts, National Foundation on the Arts and Humanities. ACTION: Notice of Meeting. SUMMARY: Pursuant to Section 10(a)(2) of...- one meetings of the Arts Advisory Panel to the National Council on the Arts will be held at the...

  17. 78 FR 76660 - Arts Advisory Panel Meeting

    Science.gov (United States)

    2013-12-18

    ... ARTS AND THE HUMANITIES Arts Advisory Panel Meeting AGENCY: National Endowment for the Arts, National Foundation on the Arts and Humanities. ACTION: Notice of Meeting. SUMMARY: Pursuant to Section 10(a)(2) of... meetings of the Arts Advisory Panel to the National Council on the Arts will be held at the Nancy...

  18. 77 FR 75672 - Arts Advisory Panel Meeting

    Science.gov (United States)

    2012-12-21

    ... ARTS AND THE HUMANITIES Arts Advisory Panel Meeting AGENCY: National Endowment for the Arts, National Foundation on the Arts and Humanities. ACTION: Notice of Meeting. SUMMARY: Pursuant to Section 10(a)(2) of... meetings of the Arts Advisory Panel to the National Council on the Arts will be held at the Nancy...

  19. 77 FR 13367 - Arts Advisory Panel Meeting

    Science.gov (United States)

    2012-03-06

    ... ARTS AND THE HUMANITIES Arts Advisory Panel Meeting AGENCY: National Endowment for the Arts, National Foundation on the Arts and Humanities. ACTION: Notice of meeting. SUMMARY: Pursuant to Section 10(a)(2) of... of the Arts Advisory Panel to the National Council on the Arts will be held by teleconference at...

  20. 77 FR 61643 - Arts Advisory Panel Meeting

    Science.gov (United States)

    2012-10-10

    ... ARTS AND THE HUMANITIES Arts Advisory Panel Meeting AGENCY: National Endowment for the Arts, National Foundation on the Arts and Humanities. ACTION: Notice of meeting. SUMMARY: Pursuant to Section 10(a)(2) of... meetings of the Arts Advisory Panel to the National Council on the Arts will be held at the Nancy...

  1. 78 FR 38410 - Arts Advisory Panel Meeting

    Science.gov (United States)

    2013-06-26

    ... ARTS AND THE HUMANITIES Arts Advisory Panel Meeting AGENCY: National Endowment for the Arts, National Foundation on the Arts and Humanities. ACTION: Notice of Meetings. SUMMARY: Pursuant to Section 10(a)(2) of... meetings of the Arts Advisory Panel to the National Council on the Arts will be held at the Nancy...

  2. 77 FR 67836 - Arts Advisory Panel Meeting

    Science.gov (United States)

    2012-11-14

    ... ARTS AND THE HUMANITIES Arts Advisory Panel Meeting AGENCY: National Endowment for the Arts, National Foundation on the Arts and Humanities. ACTION: Notice of Meeting. SUMMARY: Pursuant to Section 10(a)(2) of... meetings of the Arts Advisory Panel to the National Council on the Arts will be held at the Nancy...

  3. 77 FR 56875 - Arts Advisory Panel Meeting

    Science.gov (United States)

    2012-09-14

    ... ARTS AND THE HUMANITIES Arts Advisory Panel Meeting AGENCY: National Endowment for the Arts, National Foundation on the Arts and Humanities. ACTION: Notice of meeting. SUMMARY: Pursuant to Section 10(a)(2) of... meetings of the Arts Advisory Panel to the National Council on the Arts will be held by teleconference...

  4. 77 FR 35067 - Arts Advisory Panel Meeting

    Science.gov (United States)

    2012-06-12

    ... ARTS AND THE HUMANITIES Arts Advisory Panel Meeting AGENCY: National Endowment for the Arts, National Foundation on the Arts and Humanities. ACTION: Notice of meeting. SUMMARY: Pursuant to Section 10(a)(2) of... meetings of the Arts Advisory Panel to the National Council on the Arts will be held at the Nancy...

  5. 75 FR 56146 - Arts Advisory Panel; Meetings

    Science.gov (United States)

    2010-09-15

    ... ARTS AND THE HUMANITIES National Endowment for the Arts Arts Advisory Panel; Meetings Pursuant to... given that four meetings of the Arts Advisory Panel to the National Council on the Arts will be held at... are approximate): Arts Education (application review): October 4-5, 2010 in Room 716. A portion...

  6. 77 FR 22613 - Arts Advisory Panel Meeting

    Science.gov (United States)

    2012-04-16

    ... ARTS AND THE HUMANITIES Arts Advisory Panel Meeting AGENCY: National Endowment for the Arts, National Foundation on the Arts and the Humanities. ACTION: Notice of meeting. SUMMARY: Pursuant to Section 10(a)(2... meetings of the Arts Advisory Panel to the National Council on the Arts will be held at the Nancy...

  7. 78 FR 64026 - Arts Advisory Panel Meeting

    Science.gov (United States)

    2013-10-25

    ... ARTS AND THE HUMANITIES Arts Advisory Panel Meeting AGENCY: National Endowment for the Arts, National Foundation on the Arts and Humanities. ACTION: Notice of Meeting SUMMARY: Pursuant to Section 10(a)(2) of the... of the Arts Advisory Panel to the National Council on the Arts will be held at the Nancy Hanks...

  8. Circuits in the Sun: Solar Panel Physics

    Science.gov (United States)

    Gfroerer, Tim

    2013-01-01

    Typical commercial solar panels consist of approximately 60 individual photovoltaic cells connected in series. Since the usual Kirchhoff rules apply, the current is uniform throughout the circuit, while the electric potential of the individual devices is cumulative. Hence, a solar panel is a good analog of a simple resistive series circuit, except…

  9. Air loads on solar panels during launch

    NARCIS (Netherlands)

    Beltman, W.M.; van der Hoogt, Peter; Spiering, R.M.E.J.; Tijdeman, H.

    1996-01-01

    The dynamical behaviour of solar panels during launch is significantly affected by the thin layers of air trapped between the panels. For narrow gaps the air manifests itself not only as a considerable added mass, but its viscosity can result in a substantial amount of damping. A model has been

  10. Switched mode piezo-panel driver

    NARCIS (Netherlands)

    Slakhorst, R.J.

    2007-01-01

    Abstract The subject of this thesis is the design of a system which can drive piezo-panels. This system is called the piezo driver. The piezo-panels are used for an Active Noise Cancelling (ANC) system which is being developed to be used inside the cabin of airplanes. The piezo driver fills the gap

  11. Computer aided pantograph design for garment panels

    Institute of Scientific and Technical Information of China (English)

    2001-01-01

    Discusses the difficulties and problems with manual pantograph ofgarment panels, introduces several typical pantographic ways and their characteristics both at home and abroad, presents a new pantographic method based on similar figures developed to overcome the deficiency of those methods, so as to realize computer aid automatic panel pantograph.

  12. Research challenges for energy data management (panel)

    DEFF Research Database (Denmark)

    Pedersen, Torben Bach; Lehner, Wolfgang

    2013-01-01

    This panel paper aims at initiating discussion at the Second International Workshop on Energy Data Management (EnDM 2013) about the important research challenges within Energy Data Management. The authors are the panel organizers, extra panelists will be recruited before the workshop...

  13. Transparent metals for ultrabroadband electromagnetic waves.

    Science.gov (United States)

    Fan, Ren-Hao; Peng, Ru-Wen; Huang, Xian-Rong; Li, Jia; Liu, Yongmin; Hu, Qing; Wang, Mu; Zhang, Xiang

    2012-04-17

    Making metals transparent, which could lead to fascinating applications, has long been pursued. Here we demonstrate that with narrow slit arrays metallic plates become transparent for extremely broad bandwidths; the high transmission efficiency is insensitive to the metal thickness. This work provides a guideline to develop novel devices, including transparent conducting panels, broadband metamaterials, and antireflective solar cells. Copyright © 2012 WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim.

  14. Reliability of stiffened structural panels: Two examples

    Science.gov (United States)

    Stroud, W. Jefferson; Davis, D. Dale, Jr.; Maring, Lise D.; Krishnamurthy, Thiagaraja; Elishakoff, Isaac

    1992-12-01

    The reliability of two graphite-epoxy stiffened panels that contain uncertainties is examined. For one panel, the effect of an overall bow-type initial imperfection is studied. The size of the bow is assumed to be a random variable. The failure mode is buckling. The benefits of quality control are explored by using truncated distributions. For the other panel, the effect of uncertainties in a strain-based failure criterion is studied. The allowable strains are assumed to be random variables. A geometrically nonlinear analysis is used to calculate a detailed strain distribution near an elliptical access hole in a wing panel that was tested to failure. Calculated strains are used to predict failure. Results are compared with the experimental failure load of the panel.

  15. PV panel model based on datasheet values

    DEFF Research Database (Denmark)

    Sera, Dezso; Teodorescu, Remus; Rodriguez, Pedro

    2007-01-01

    This work presents the construction of a model for a PV panel using the single-diode five-parameters model, based exclusively on data-sheet parameters. The model takes into account the series and parallel (shunt) resistance of the panel. The equivalent circuit and the basic equations of the PV cell....../panel in Standard Test Conditions (STC) are shown, as well as the parameters extraction from the data-sheet values. The temperature dependence of the cell dark saturation current is expressed with an alternative formula, which gives better correlation with the datasheet values of the power temperature dependence....... Based on these equations, a PV panel model, which is able to predict the panel behavior in different temperature and irradiance conditions, is built and tested....

  16. Report of the Federal Internetworking Requirements Panel

    Energy Technology Data Exchange (ETDEWEB)

    NONE

    1994-05-31

    The Federal Internetworking Requirements Panel (FIRP) was established by the National Institute of Standards and Technology (NIST) to reassess Federal requirements for open systems networks and to recommend policy on the Government`s use of networking standards. The Panel was chartered to recommend actions which the Federal Government can take to address the short and long-term issues of interworking and convergence of networking protocols--particularly the Internet Protocol Suite (IPS) and Open Systems Interconnection (OSI) protocol suite and, when appropriate, proprietary protocols. The Panel was created at the request of the Office of Management and Budget in collaboration with the Federal Networking Council and the Federal Information Resources Management Policy Council. The Panel`s membership and charter are contained in an appendix to this report.

  17. Methodology for Selection of Optimum Light Stringers in Functionally Graded Panels Designed for Prescribed Fundamental Frequency or Buckling Load

    Science.gov (United States)

    Birman, Victor; Byrd, Larry W.

    2008-02-01

    The interest to functionally graded materials (FGM) and structures has been generated by their potential advantages, including enhanced thermal properties, reduced or eliminated delamination concerns, a potential for an improved stress distribution, etc. Various aspects of the processing, design, micromechanics and analysis of FGM have been outlined in a number of reviews, mentioned here are [1-3]. In particular, functionally graded panels may be advantageous compared to their conventional counterparts in numerous applications. However, a typical FGM panel is asymmetric about its middle plane resulting in lower buckling loads and fundamental frequencies as well as higher stresses and deformations than the counterpart with a symmetric distribution of the same constituents. The reduced stiffness of FGM panels can be compensated by reinforcing them with stringers. For example, metallic stringers at the metal-rich surface of a FGM ceramic-metal panel may provide an efficient solution enabling a designer to increase both buckling loads as well as natural frequencies. The list of studies on optimization of FGM is extensive as could be anticipated for such tailored structural elements. For example, recent papers by Batra and his collaborators present optimization of the natural frequencies of a FGM plate through material grading [4] and through the graded fiber orientation [5]. The present paper is concerned with an optimum design of the system of stringers for a specified FGM panel. The task is to design the lightest system of stringers enabling the panel to achieve prescribed buckling loads or fundamental frequency.

  18. Contact analysis of wing-fuselage connection joint lug%机翼机身接头耳片接触分析

    Institute of Scientific and Technical Information of China (English)

    牛一虹; 刘波; 丁同超; 贾宏光

    2012-01-01

    Wing-fuselage connection joint is an important part of the aircraft. Therefore, strength check of wing-fuselage joints is an indispensable step in the airplane design. In this paper, contact analysis of a certain type of wing-fuselage connection joints was conducted by FEM software. The analysis results showed that, the maximum equivalent stress of bolt was 1610MPa, and the maximum equivalent stress of lug was 2140MPa which was generated inside the hole wall, exceeded the elastic limit of the material and entered into the plastic zone. Error between the numerical and experimental results was less than 30%, which is acceptable in engineering. The stress distributions in various components of the joint were consistent with the theoretical analysis. The method used in this paper laid out a theoretical basis for the application of its structure and materials in the design, and provided critical data for design improvements.%机翼-机身连接接头是飞机的重要部分,在飞机设计时,必须对其进行强度校核.文章针对某型机翼-机身接头,利用有限元软件进行接触分析.分析结果表明,螺栓所受最大等效应力为1610MPa,耳片所受最大应力产生在耳片内侧孔壁,最大等效应力为2140MPa,超过材料的弹性极限,材料进入塑性区.实验结果与分析结果误差在30%以内,为工程的认可范围,而且接头各部件的应力分布与理论分析相符.文中采用的方法可为机翼-机身连接接头结构及材料在设计中的应用提供理论依据,并为设计的改进提供关键数据.

  19. Graphite Composite Panel Polishing Fixture

    Science.gov (United States)

    Hagopian, John; Strojny, Carl; Budinoff, Jason

    2011-01-01

    The use of high-strength, lightweight composites for the fixture is the novel feature of this innovation. The main advantage is the light weight and high stiffness-to-mass ratio relative to aluminum. Meter-class optics require support during the grinding/polishing process with large tools. The use of aluminum as a polishing fixture is standard, with pitch providing a compliant layer to allow support without deformation. Unfortunately, with meter-scale optics, a meter-scale fixture weighs over 120 lb (.55 kg) and may distort the optics being fabricated by loading the mirror and/or tool used in fabrication. The use of composite structures that are lightweight yet stiff allows standard techniques to be used while providing for a decrease in fixture weight by almost 70 percent. Mounts classically used to support large mirrors during fabrication are especially heavy and difficult to handle. The mount must be especially stiff to avoid deformation during the optical fabrication process, where a very large and heavy lap often can distort the mount and optic being fabricated. If the optic is placed on top of the lapping tool, the weight of the optic and the fixture can distort the lap. Fixtures to support the mirror during fabrication are often very large plates of aluminum, often 2 in. (.5 cm) or more in thickness and weight upwards of 150 lb (68 kg). With the addition of a backing material such as pitch and the mirror itself, the assembly can often weigh over 250 lb (.113 kg) for a meter-class optic. This innovation is the use of a lightweight graphite panel with an aluminum honeycomb core for use as the polishing fixture. These materials have been used in the aerospace industry as structural members due to their light weight and high stiffness. The grinding polishing fixture consists of the graphite composite panel, fittings, and fixtures to allow interface to the polishing machine, and introduction of pitch buttons to support the optic under fabrication. In its

  20. Microspheres in Plasma Display Panels

    Science.gov (United States)

    2006-01-01

    Filling small bubbles of molten glass with gases is just as difficult as it sounds, but the technical staff at NASA is not known to shy away from a difficult task. When Microsphere Systems, Inc. (MSI), of Ypsilanti, Michigan, and Imaging Systems Technology, Inc. (IST), of Toledo, Ohio, were trying to push the limits of plasma displays but were having difficulty with the designs, NASA s Glenn Garrett Morgan Commercialization Initiative (GMCI) assembled key personnel at Glenn Research Center and Ohio State University for a brainstorming session to come up with a solution for the companies. They needed a system that could produce hollow, glass micro-sized spheres (microspheres) that could be filled with a variety of gasses. But the extremely high temperature required to force the micro-sized glass bubbles to form at the tip of a metal nozzle resulted in severe discoloration of the microspheres. After countless experiments on various glass-metal combinations, they had turned to the GMCI for help. NASA experts in advanced metals, ceramics, and glass concluded that a new design approach was necessary. The team determined that what was needed was a phosphate glass composition that would remain transparent, and they went to work on a solution. Six weeks later, using the design tips from the NASA team, Tim Henderson, president of MSI, had designed a new system in which all surfaces in contact with the molten glass would be ceramic instead of metal. Meanwhile, IST was able to complete a Phase I Small Business Innovation Research (SBIR) grant supported by the National Science Foundation (NSF) and supply a potential customer with samples of the microspheres for evaluation as filler materials for high-performance insulations.

  1. Wing-fuselage Joint Posture Error Analysis for Aircraft Digital Assembly%飞机数字化总装中的翼身接头位姿误差分析

    Institute of Scientific and Technical Information of China (English)

    刘楚辉; 鹿业波

    2014-01-01

    To guarantee the security of finish machining of wing-fuselage connecting holes in aircraft digital assembly, a posture error analysis method of wing-fuselage joints is put forward relative to the reference frame of assembly system. The posture error model of wing-fuselage joints is built by using matrix perturbation method. The spans of each source error are determined according to results of fuselage posture alignment experiment and performance parameters of correlative equipments. Distribution of posture error of wing-fuselage joints is learned by Monte Carlo simulation. Cutting allowance of wing-fuselage connecting hole in the worst case is calculated by using extreme value analysis method. According to the calculation results, a qualitative conclusion was got and it's a possibility that allowance of some wing-fuselage connecting holes is insufficient for finish machining.%为了提高飞机数字化装配过程中翼身交点孔精加工的安全性,提出一种分析翼身接头相对装配参考坐标系的位姿误差的方法。采用矩阵摄动法建立了相应的误差模型,根据飞机大部件调姿试验的结果和相关工艺装备的性能参数,确定各项原始误差的取值范围。通过蒙特卡洛模拟求出翼身接头位姿误差的分布特性,在此基础上采用极值法定性分析极端情况下翼身交点孔的切削余量,获得了有可能出现翼身交点孔加工余量不足的定性结论。

  2. PERBANDINGAN UNJUK KERJA ANTARA PANEL SEL SURYA BERPENJEJAK DENGAN PANEL SEL SURYA DIAM

    Directory of Open Access Journals (Sweden)

    Syafaruddin Ch

    2010-07-01

    Full Text Available The ability to produce electrical energy at Solar Power Plant  is highly dependent on the magnitude and duration of sun exposure on the solar cell panels. The movement of the sun from east to west that periodicity in every day is a problem at  the  optimization generation of electricity at  Solar Power Plant   if using solar panel that motionless. This is because the solar cell panel can not catch the maximum sun exposure. To solve the above problem then designed a solar cell panel  tracker  capable of follo-wing the movements of the sun. Then conducted a test to see the performance of solar cell pa-nel  tracker  and compare it with the performance of solar cell panel was motionless. The testing doing along 6 days, with way to irradiate the panel of solar cells  tracker  and panels of solar cell motionless with sun exposure  along a  full day. Then the electric current generated each panel were recorded. The comparison of current then generating comparison of electric power delivery. The result show that the solar cell panel  tracker  produce the average current is 2.19 A whereas solar-cell panel still 1.97 A.  This result   indicate that average power for solar cell panel  tracker  39.41 W while for solar cell panel that motionless is  35.46 W. These results indicate that the performance of solar cell panel  tracker  better than  solar cell panel motionless.

  3. 78 FR 73586 - Taxpayer Advocacy Panel Meeting Cancellation

    Science.gov (United States)

    2013-12-06

    ... Internal Revenue Service Taxpayer Advocacy Panel Meeting Cancellation AGENCY: Internal Revenue Service (IRS... the open meeting of the Taxpayer Advocacy Panel Taxpayer Assistance Center Improvements Project..., Taxpayer Advocacy Panel. BILLING CODE 4830-01-P...

  4. 78 FR 73587 - Taxpayer Advocacy Panel Meeting Cancellation

    Science.gov (United States)

    2013-12-06

    ... Internal Revenue Service Taxpayer Advocacy Panel Meeting Cancellation AGENCY: Internal Revenue Service (IRS... the open meeting of the Taxpayer Advocacy Panel Notices and Correspondence Project Committee scheduled... Advocacy Panel. BILLING CODE 4830-01-P...

  5. 78 FR 73587 - Taxpayer Advocacy Panel; Meeting Cancellation.

    Science.gov (United States)

    2013-12-06

    ... Internal Revenue Service Taxpayer Advocacy Panel; Meeting Cancellation. AGENCY: Internal Revenue Service... cancellation of the open meeting of the Taxpayer Advocacy Panel Taxpayer Communications Project Committee..., Acting Director, Taxpayer Advocacy Panel. BILLING CODE 4830-01-P...

  6. Behavioral Model of Photovoltaic Panel in Simulink

    Directory of Open Access Journals (Sweden)

    ZAPLATILEK, K.

    2011-11-01

    Full Text Available This article deals with creation and application of a model of photovoltaic panel in the MATLAB and Simulink environments. An original model of the real PV panel is applied using the model based design technique. A so-called physical model is also developed using the SimPowerSystems library. The described PV panel model is applied for maximum power optimization in the one-shot and the continuous modes. A few illustrating examples and source code parts are also presented.

  7. Development of a plasma panel muon detector

    Science.gov (United States)

    Levin, D. S.; Ball, R.; Beene, J. R.; Benhammou, Y.; Chapman, J. W.; Dai, T.; Etzion, E.; Friedman, P. S.; Ben Moshe, M.; Silver, Y.; Varner, R. L.; Weaverdyck, C.; White, S.; Zhou, B.

    2011-10-01

    A radiation detector technology based on plasma display panels (PDPs), the underlying engine of panel plasma television displays, is being investigated. Emerging from this well-established television technology is the Plasma Panel Sensor (PPS), a novel variant of the micro-pattern radiation detector. The PPS is fundamentally a fast, high-resolution detector comprised of an array of plasma discharge cells, operating in a hermetically sealed gas mixture. We report on the PPS development effort, including proof-of-principle results of laboratory signal observations.

  8. Slewing control experiment for a flexible panel

    Science.gov (United States)

    Juang, Jer-Nan

    1987-01-01

    Technology areas are identified in which better analytical and/or experimental methods are needed to adequately and accurately control the dynamic responses of multibody space platforms such as the space station. A generic space station solar panel is used to experimentally evaluate current control technologies. Active suppression of solar panel vibrations induced by large angle maneuvers is studied with a torque actuator at the root of the solar panel. These active suppression tests will identify the hardware requirements and adequacy of various controller designs.

  9. Underwater Explosion Damage of Ship Hull Panels

    OpenAIRE

    K. Rarnajeyathilagam; Vendhan, C.P.

    2003-01-01

    Underwater explosion is a major threat to ships and submarines in a war environment. The prediction of the mode and the extent of the failure is an essential step in designing for shock loading. The localised failure in a hull panel is severe compared to the global response of the ship. In this study, an attempt has been made to predict the response and failure modes of three types of hull panels (flat, concave, and convex). The shock loading on the hull panel has been estimated based on the ...

  10. Initial report from the ICFA Neutrino Panel

    CERN Document Server

    Cao, J; Duchesneau, D; Funchal, R; Geer, S; Kim, S B; Kobayashi, T; Long, K; Maltoni, M; Mezzetto, M; Mondal, N; Shiozawa, M; Sobczyk, J; Tanaka, H A; Wascko, M; Zeller, G

    2014-01-01

    In July 2013 ICFA established the Neutrino Panel with the mandate "To promote international cooperation in the development of the accelerator-based neutrino-oscillation program and to promote international collaboration in the development a neutrino factory as a future intense source of neutrinos for particle physics experiments". This, the Panel's Initial Report, presents the conclusions drawn by the Panel from three regional "Town Meetings" that took place between November 2013 and February 2014. After a brief introduction and a short summary of the status of the knowledge of the oscillation parameters, the report summarises the approved programme and identifies opportunities for the development of the field. In its conclusions, the Panel recognises that to maximise the discovery potential of the accelerator-based neutrino-oscillation programme it will be essential to exploit the infrastructures that exist at CERN, FNAL and J-PARC and the expertise and resources that reside in laboratories and institutes ar...

  11. Panel backs next-generation synchrotron

    CERN Multimedia

    Service, R F

    1999-01-01

    A key federal panel recommended continued research into development of a fourth-generation synchrotron. It would be capable of creating x-ray pulses billions of times more intense than current designs (1 page).

  12. Study on noise of precision panel saw

    Institute of Scientific and Technical Information of China (English)

    HUWan-yi; QIYing-jie; ZHANGZhao-hao; QIXiao-jie

    2003-01-01

    According to ZBJ65015-89 standard about noise level testing method of woodworking toot, the noise testing for MJg0# and MJCl125 precision panel saws was conducted by using model ND2 precision soundqevel apparatus and double frequency wave filter. The testing results showed that the unloaded running noise source of precision panel saw was mainly from main saw blade and its aeromechanic noise was the largest. The rotating speed was determined as an important factor to impact dynamic characters of precision panel saw as the unloaded running noise increased along with speed increasing. For reducing noise of precision panel saw, the first important way is to reduce the aeromechanic noise produced by main saw blade rotating at high speed; based on assuring the processing precision, choosing tow speed is a better way to drop dawn noise; from the view of design, the diameter of clamping lid is better of half of outer diameter of main saw blade.

  13. Increasing the efficiency of solar thermal panels

    Science.gov (United States)

    Dobrnjac, M.; Latinović, T.; Dobrnjac, S.; Živković, P.

    2016-08-01

    The popularity of solar heating systems is increasing for several reasons. These systems are reliable, adaptable and pollution-free, because the renewable solar energy is used. There are many variants of solar systems in the market mainly constructed with copper pipes and absorbers with different quality of absorption surface. Taking into account the advantages and disadvantages of existing solutions, in order to increase efficiency and improve the design of solar panel, the innovative solution has been done. This new solar panel presents connection of an attractive design and the use of constructive appropriate materials with special geometric shapes. Hydraulic and thermotechnical tests that have been performed on this panel showed high hydraulic and structural stability. Further development of the solar panel will be done in the future in order to improve some noticed disadvantages.

  14. The Panel Study of Income Dynamics (PSID)

    Data.gov (United States)

    U.S. Department of Health & Human Services — The Panel Study of Income Dynamics (PSID) began in 1968 with a nationally representative sample of over 18,000 individuals living in 5,000 families in the United...

  15. Characteristics of DSSC Panels with Silicone Encapsulant

    Directory of Open Access Journals (Sweden)

    Jun-Gu Kang

    2015-01-01

    Full Text Available Dye-sensitized solar cells (DSSC allow light transmission and the application of various colors that make them especially suitable for building-integrated PV (BIPV application. In order to apply DSSC modules to windows, the module has to be panelized: a DSSC module should be protected with toughened glass on the entire surface. Up to the present, it seems to be common to use double glazing with DSSC modules, with air gaps between the glass pane and the DSSC modules. Few studies have been conducted on the characteristics of various glazing methods with DSSC modules. This paper proposes a paneling method that uses silicone encapsulant, analyzing the performance through experimentation. Compared to a multilayered DSSC panel with an air gap, the encapsulant-applied panel showed 6% higher light transmittance and 7% higher electrical efficiency. The encapsulant also prevented electrolyte leakage by strengthening the seals in the DSSC module.

  16. Moonshot Panel Moving Toward Final Report

    Science.gov (United States)

    An NCI Cancer Currents blog from acting NCI Director Dr. Doug Lowy providing an update on the activities of the National Cancer Moonshot Initiative’s Blue Ribbon Panel and its work to develop a final report.

  17. Medical Expenditure Panel Survey Household Component

    Data.gov (United States)

    U.S. Department of Health & Human Services — The Medical Expenditure Panel Survey (MEPS) Household Component (HC) collects data from a sample of families and individuals in selected communities across the...

  18. ATR FTIR Mapping of Leather Fiber Panels

    Science.gov (United States)

    Tondi, G.; Grünewald, T.; Petutschnigg, A.; Schnabel, T.

    2015-01-01

    Leather fiber panels are very promising materials for many applications, not only for the easy availability of the constituents but also for their outstanding fi re-retardant properties. These innovative composite panels can be an excellent material for building insulation, and in recent times, the interest of industries in this composite board has considerably arisen. For this reason the discrimination of the components in the leather fiber panels is becoming fundamental in order to ensure their homogeneous properties. A method to characterize the surface of these materials is then required. An ATR FTIR mapping system for the leather fiber panels has been performed with a Perkin-Elmer microscope coupled with a Frontier FTIR spectrometer. The system has successfully allowed transforming the optical image to a chemical one. This technique can be considered as a right tool for routine controls of the surface quality, especially when the leather shavings cannot be optically distinguished.

  19. Robust estimation procedure in panel data model

    Energy Technology Data Exchange (ETDEWEB)

    Shariff, Nurul Sima Mohamad [Faculty of Science of Technology, Universiti Sains Islam Malaysia (USIM), 71800, Nilai, Negeri Sembilan (Malaysia); Hamzah, Nor Aishah [Institute of Mathematical Sciences, Universiti Malaya, 50630, Kuala Lumpur (Malaysia)

    2014-06-19

    The panel data modeling has received a great attention in econometric research recently. This is due to the availability of data sources and the interest to study cross sections of individuals observed over time. However, the problems may arise in modeling the panel in the presence of cross sectional dependence and outliers. Even though there are few methods that take into consideration the presence of cross sectional dependence in the panel, the methods may provide inconsistent parameter estimates and inferences when outliers occur in the panel. As such, an alternative method that is robust to outliers and cross sectional dependence is introduced in this paper. The properties and construction of the confidence interval for the parameter estimates are also considered in this paper. The robustness of the procedure is investigated and comparisons are made to the existing method via simulation studies. Our results have shown that robust approach is able to produce an accurate and reliable parameter estimates under the condition considered.

  20. Panel Resource Management (PRM) Implementation and Effects within Safety Review Panel Settings and Dynamics

    Science.gov (United States)

    Taylor, Robert W.; Nash, Sally K.

    2007-01-01

    While technical training and advanced degree's assure proficiency at specific tasks within engineering disciplines, they fail to address the potential for communication breakdown and decision making errors familiar to multicultural environments where language barriers, intimidating personalities and interdisciplinary misconceptions exist. In an effort to minimize these pitfalls to effective panel review, NASA's lead safety engineers to the ISS Safety Review Panel (SRP), and Payload Safety Review Panel (PSRP) initiated training with their engineers, in conjunction with the panel chairs, and began a Panel Resource Management (PRM) program. The intent of this program focuses on the ability to reduce the barriers inhibiting effective participation from all panel attendees by bolstering participants confidence levels through increased communication skills, situational awareness, debriefing, and a better technical understanding of requirements and systems.

  1. Development of a plasma panel radiation detector: recent progress and key issues

    CERN Document Server

    Silver, Yiftah; Beene, James R; Benhammou, Yan; Ben-Moshe, Meny; Chapman, J W; Dai, Tiesheng; Etzion, Erez; Ferretti, Claudio; Guttman, Nir; Friedman, Peter S; Levin, Daniel S; Ritt, S; Varner, Robert L; Weaverdyck, Curtis; Zhou, Bing

    2012-01-01

    A radiation detector based on plasma display panel technology, which is the principal component of plasma television displays is presented. Plasma Panel Sensor (PPS) technology is a variant of micropattern gas radiation detectors. The PPS is conceived as an array of sealed plasma discharge gas cells which can be used for fast response (O(5ns) per pixel), high spatial resolution detection (pixel pitch can be less than 100 micrometer) of ionizing and minimum ionizing particles. The PPS is assembled from non-reactive, intrinsically radiation-hard materials: glass substrates, metal electrodes and inert gas mixtures. We report on the PPS development program, including simulations and design and the first laboratory studies which demonstrate the usage of plasma display panels in measurements of cosmic ray muons, as well as the expansion of experimental results on the detection of betas from radioactive sources.

  2. Panel-basierte Mixed-Methods-Studien

    OpenAIRE

    Legewie, Nicolas; Tucci, Ingrid

    2016-01-01

    Mixed-Methods-Studien erfreuen sich wachsender Beliebtheit. Immer mehr Studien nutzen dabei auch Panel-basierte Mixed-Methods-Designs, in denen bestehende Längsschnittstudien durch qualitative Befragungsformen ergänzt werden. Innerhalb der reichhaltigen Veröffentlichungen zum Thema Mixed-Methods-Forschung finden sich bisher aber kaum Diskussionen solcher Mixed-Methods-Designs. Im vorliegenden Artikel diskutieren wir Design, Durchführung, sowie Potenzialeund Herausforderungen von Panel-basiert...

  3. Aerosol Deposition and Solar Panel Performance

    Science.gov (United States)

    Arnott, W. P.; Rollings, A.; Taylor, S. J.; Parks, J.; Barnard, J.; Holmes, H.

    2015-12-01

    Passive and active solar collector farms are often located in relatively dry desert regions where cloudiness impacts are minimized. These farms may be susceptible to reduced performance due to routine or episodic aerosol deposition on collector surfaces. Intense episodes of wind blown dust deposition may negatively impact farm performance, and trigger need to clean collector surfaces. Aerosol deposition rate depends on size, morphology, and local meteorological conditions. We have developed a system for solar panel performance testing under real world conditions. Two identical 0.74 square meter solar panels are deployed, with one kept clean while the other receives various doses of aerosol deposition or other treatments. A variable load is used with automation to record solar panel maximum output power every 10 minutes. A collocated sonic anemometer measures wind at 10 Hz, allowing for both steady and turbulent characterization to establish a link between wind patterns and particle distribution on the cells. Multispectral photoacoustic instruments measure aerosol light scattering and absorption. An MFRSR quantifies incoming solar radiation. Solar panel albedo is measured along with the transmission spectra of particles collected on the panel surface. Key questions are: At what concentration does aerosol deposition become a problem for solar panel performance? What are the meteorological conditions that most strongly favor aerosol deposition, and are these predictable from current models? Is it feasible to use the outflow from an unmanned aerial vehicle hovering over solar panels to adequately clean their surface? Does aerosol deposition from episodes of nearby forest fires impact performance? The outlook of this research is to build a model that describes environmental effects on solar panel performance. Measurements from summer and fall 2015 will be presented along with insights gleaned from them.

  4. Phosphors for flat panel emissive displays

    Energy Technology Data Exchange (ETDEWEB)

    Anderson, M.T.; Walko, R.J.; Phillips, M.L.F.

    1995-07-01

    An overview of emissive display technologies is presented. Display types briefly described include: cathode ray tubes (CRTs), field emission displays (FEDs), electroluminescent displays (ELDs), and plasma display panels (PDPs). The critical role of phosphors in further development of the latter three flat panel emissive display technologies is outlined. The need for stable, efficient red, green, and blue phosphors for RGB fall color displays is emphasized.

  5. Study on the performance of infrared thermal imaging light source for detection of impact defects in CFRP composite sandwich panels

    Energy Technology Data Exchange (ETDEWEB)

    Park, Hee Sang [R and D, Korea Research Institute of Smart Material and Structures System Association, Daejeon (Korea, Republic of); Choi, Man Yong; Kwon, Koo Ahn; Park, Jeong Hak; Choi, Won Jae [Safety measurement center, Korea research Institute of Standards and Science, Daejeon (Korea, Republic of); Jung, Hyun Chul [Dept. of Mechanical Engineering Chosun University, Gwangju (Korea, Republic of)

    2017-04-15

    Recently, composite materials have been mainly used in the main wings, ailerons, and fuselages of aircraft and rotor blades of helicopters. Composite materials used in rapid moving structures are subject to impact by hail, lightning, and bird strike. Such an impact can destroy fiber tissues in the composite materials as well as deform the composite materials, resulting in various problems such as weakened rigidity of the composite structure and penetration of water into tiny cracks. In this study, experiments were conducted using a 2 kW halogen lamp which is most frequently used as a light source, a 2 kW near-infrared lamp, which is used for heating to a high temperature, and a 6 kW xenon flash lamp which emits a large amount of energy for a moment. CFRP composite sandwich panels using Nomex honeycomb core were used as the specimens. Experiments were carried out under impact damages of 1, 4 and 8 J. It was found that the detection of defects was fast when the xenon flash lamp was used. The detection of damaged regions was excellent when the halogen lamp was used. Furthermore, the near-infrared lamp is an effective technology for showing the surface of a test object.

  6. Planarity certification of ATLAS Micromegas detector panels

    Energy Technology Data Exchange (ETDEWEB)

    Mueller, Ralph; Biebel, Otmar; Bortfeldt, Jonathan; Flierl, Bernhard; Hertenberger, Ralf; Loesel, Philipp; Herrmann, Maximilian [LMU Muenchen (Germany); Zibell, Andre [JMU Wuerzburg (Germany)

    2016-07-01

    During the second long LHC shutdown, 2019/20, the precision tracking detectors of the ATLAS muon spectrometer in the inner end caps will be replaced using Micromegas, a planar gas-detector technology. Modules of 2 m{sup 2} area are built in quadruplets from five precisely planar sandwich panels that define the anodes and the cathodes of the four active detector planes. A panel is composed of three consecutive layers FR4 - aluminum honeycomb - FR4. Single plane spatial particle resolution below 100 μm is achievable when the deviations from planarity of the strip-anodes do not exceed 80 μm RMS over the whole active area and the parallelism of the readout strips is within 30 μm. In order to measure the dimensional accuracy of each panel, laser distance sensors combined with a coordinate measurement system have been investigated. The sensor requirements to measure the planarity of the panels are a resolution of 0.3 μm and a beam spot diameter of ∼20 μm, well below 100 μ m the size of the smallest structures. We report on achieved planarities of the panels and the performance of the laser sensor system. A panel with an RMS better than 30 μm was build and the evolution of its planarity due to humidity and temperature effects is shown.

  7. Development and Evaluation of Stitched Sandwich Panels

    Science.gov (United States)

    Stanley, Larry E.; Adams, Daniel O.; Reeder, James R. (Technical Monitor)

    2001-01-01

    This study explored the feasibility and potential benefits provided by the addition of through-the-thickness reinforcement to sandwich structures. Through-the-thickness stitching is proposed to increase the interlaminar strength and damage tolerance of composite sandwich structures. A low-cost, out-of-autoclave processing method was developed to produce composite sandwich panels with carbon fiber face sheets, a closed-cell foam core, and through-the-thickness Kevlar stitching. The sandwich panels were stitched in a dry preform state, vacuum bagged, and infiltrated using Vacuum Assisted Resin Transfer Molding (VARTM) processing. For comparison purposes, unstitched sandwich panels were produced using the same materials and manufacturing methodology. Test panels were produced initially at the University of Utah and later at NASA Langley Research Center. Four types of mechanical tests were performed: flexural testing, flatwise tensile testing, core shear testing, and edgewise compression testing. Drop-weight impact testing followed by specimen sectioning was performed to characterize the damage resistance of stitched sandwich panels. Compression after impact (CAI) testing was performed to evaluate the damage tolerance of the sandwich panels. Results show significant increases in the flexural stiffness and strength, out-of-plane tensile strength, core shear strength, edgewise compression strength, and compression-after-impact strength of stitched sandwich structures.

  8. PERBANDINGAN UNJUK KERJA ANTARA PANEL SEL SURYA BERPENJEJAK DENGAN PANEL SEL SURYA DIAM

    OpenAIRE

    Syafaruddin Ch

    2010-01-01

    The ability to produce electrical energy at Solar Power Plant  is highly dependent on the magnitude and duration of sun exposure on the solar cell panels. The movement of the sun from east to west that periodicity in every day is a problem at  the  optimization generation of electricity at  Solar Power Plant   if using solar panel that motionless. This is because the solar cell panel can not catch the maximum sun exposure. To solve the above problem then designed a solar cell panel  tracker...

  9. PERBANDINGAN UNJUK KERJA ANTARA PANEL SEL SURYA BERPENJEJAK DENGAN PANEL SEL SURYA DIAM

    OpenAIRE

    Syafaruddin Ch

    2010-01-01

    The ability to produce electrical energy at Solar Power Plant  is highly dependent on the magnitude and duration of sun exposure on the solar cell panels. The movement of the sun from east to west that periodicity in every day is a problem at  the  optimization generation of electricity at  Solar Power Plant   if using solar panel that motionless. This is because the solar cell panel can not catch the maximum sun exposure. To solve the above problem then designed a solar cell panel  tracker...

  10. Metallated metal-organic frameworks

    Energy Technology Data Exchange (ETDEWEB)

    Bury, Wojciech; Farha, Omar K.; Hupp, Joseph T.; Mondloch, Joseph E.

    2017-08-22

    Porous metal-organic frameworks (MOFs) and metallated porous MOFs are provided. Also provided are methods of metallating porous MOFs using atomic layer deposition and methods of using the metallated MOFs as catalysts and in remediation applications.

  11. Metallated metal-organic frameworks

    Energy Technology Data Exchange (ETDEWEB)

    Bury, Wojciech; Farha, Omar K.; Hupp, Joseph T.; Mondloch, Joseph E.

    2017-02-07

    Porous metal-organic frameworks (MOFs) and metallated porous MOFs are provided. Also provided are methods of metallating porous MOFs using atomic layer deposition and methods of using the metallated MOFs as catalysts and in remediation applications.

  12. Experimental investigation on dynamic response of aircraft panels excited by high-intensity acoustic loads in thermal environment

    Science.gov (United States)

    WU, Z. Q.; LI, H. B.; ZHANG, W.; CHENG, H.; KONG, F. J.; LIU, B. R.

    2016-09-01

    Metallic and composite panels are the major components for thermal protection system of aircraft vehicles, which are exposed to a severe combination of aerodynamic, thermal and acoustic environments during hypersonic flights. A thermal-acoustic testing apparatus which simulates thermal and acoustic loads was used to validate the integrity and the reliability of these panels. Metallic and ceramic matrix composite flat panels were designed. Dynamic response tests of these panels were carried out using the thermal acoustic apparatus. The temperature of the metallic specimen was up to 400 °C, and the temperature of the composite specimen was up to 600 °C. Moreover, the acoustic load was over 160 dB. Acceleration responses of these testing panels were measured using high temperature instruments during the testing process. Results show that the acceleration root mean square values are dominated by sound pressure level of acoustic loads. Compared with testing data in room environment, the peaks of the acceleration dynamic response shifts obviously to the high frequency in thermal environment.

  13. Photovoltaic solar panels of crystalline silicon: Characterization and separation.

    Science.gov (United States)

    Dias, Pablo Ribeiro; Benevit, Mariana Gonçalves; Veit, Hugo Marcelo

    2016-03-01

    Photovoltaic panels have a limited lifespan and estimates show large amounts of solar modules will be discarded as electronic waste in a near future. In order to retrieve important raw materials, reduce production costs and environmental impacts, recycling such devices is important. Initially, this article investigates which silicon photovoltaic module's components are recyclable through their characterization using X-ray fluorescence, X-ray diffraction, energy dispersion spectroscopy and atomic absorption spectroscopy. Next, different separation methods are tested to favour further recycling processes. The glass was identified as soda-lime glass, the metallic filaments were identified as tin-lead coated copper, the panel cells were made of silicon and had silver filaments attached to it and the modules' frames were identified as aluminium, all of which are recyclable. Moreover, three different components segregation methods have been studied. Mechanical milling followed by sieving was able to separate silver from copper while chemical separation using sulphuric acid was able to detach the semiconductor material. A thermo gravimetric analysis was performed to evaluate the use of a pyrolysis step prior to the component's removal. The analysis showed all polymeric fractions present degrade at 500 °C.

  14. Crack Repair in Aerospace Aluminum Alloy Panels by Cold Spray

    Science.gov (United States)

    Cavaliere, P.; Silvello, A.

    2017-02-01

    The cold-spray process has recently been recognized as a very useful tool for repairing metallic sheets, achieving desired adhesion strengths when employing optimal combinations of material process parameters. We present herein the possibility of repairing cracks in aluminum sheets by cold spray. A 2099 aluminum alloy panel with a surface 30° V notch was repaired by cold spraying of 2198 and 7075 aluminum alloy powders. The crack behavior of V-notched sheets subjected to bending loading was studied by finite-element modeling (FEM) and mechanical experiments. The simulations and mechanical results showed good agreement, revealing a remarkable K factor reduction, and a consequent reduction in crack nucleation and growth velocity. The results enable prediction of the failure initiation locus in the case of repaired panels subjected to bending loading and deformation. The stress concentration was quantified to show how the residual stress field and failure are affected by the mechanical properties of the sprayed materials and by the geometrical and mechanical properties of the interface. It was demonstrated that the crack resistance increases more than sevenfold in the case of repair using AA2198 and that cold-spray repair can contribute to increased global fatigue life of cracked structures.

  15. 45 CFR 1801.23 - Recommendation by panel.

    Science.gov (United States)

    2010-10-01

    ... 45 Public Welfare 4 2010-10-01 2010-10-01 false Recommendation by panel. 1801.23 Section 1801.23... HARRY S. TRUMAN SCHOLARSHIP PROGRAM The Competition § 1801.23 Recommendation by panel. (a) Each Panel is... recommend additional Scholars from the States in its region. (b) A panel's recommendations are based on...

  16. Overview of Wood-based Panel Industry in China

    Institute of Scientific and Technical Information of China (English)

    2008-01-01

    The production of wood-based panel was presented firstly in this paper. Some features of China’s wood-based panel industry were reviewed, including production bases, raw materials and main markets of wood-based panel. In addition, the trade flow of wood-based panel was described in the end.

  17. Peak-power-point monitor for solar panel

    Science.gov (United States)

    Schloss, A. I.

    1972-01-01

    Attempt was made to determine solar cell panel peak power capability without disrupting power flow from panel. Separate solar cell strings were switched from panel circuits, and increasingly larger loads were added rapidly until peak power points were transversed. String wattage output was recorded and all stored string measurements summed together indicate peak power point in panel.

  18. Intermediate-scale Fire Performance of Composite Panels under Varying Loads

    Energy Technology Data Exchange (ETDEWEB)

    Brown, Alexander [Sandia National Lab. (SNL-NM), Albuquerque, NM (United States); Jernigan, Dann A. [Sandia National Lab. (SNL-NM), Albuquerque, NM (United States); Dodd, Amanda B. [Sandia National Lab. (SNL-NM), Albuquerque, NM (United States)

    2015-04-01

    New aircraft are being designed with increasing quantities of composite materials used in their construction. Different from the more traditional metals, composites have a higher propensity to burn. This presents a challenge to transportation safety analyses, as the aircraft structure now represents an additional fuel source involved in the fire scenario. Most of the historical fire testing of composite materials is aime d at studying kinetics, flammability or yield strength under fire conditions. Most of this testing is small - scale. Heterogeneous reactions are often length - scale dependent, and this is thought to be particularly true for composites which exhibit signific ant microscopic dynamics that can affect macro - scale behavior. We have designed a series of tests to evaluate composite materials under various structural loading conditions with a consistent thermal condition. We have measured mass - loss , heat flux, and temperature throughout the experiments. Several types of panels have been tested, including simple composite panels, and sandwich panels. The main objective of the testing was to understand the importance of the structural loading on a composite to its b ehavior in response to fire - like conditions. During flaming combustion at early times, there are some features of the panel decomposition that are unique to the type of loading imposed on the panels. At load levels tested, fiber reaction rates at later t imes appear to be independent of the initial structural loading.

  19. Design and Analysis of Bus Front Panel Usin G FRP

    Directory of Open Access Journals (Sweden)

    G. Adinarayana

    2014-10-01

    Full Text Available Recently, Advance composite materials have taken the significant share with other engineering materials due to its mechanical properties and high strength to weight ratio. Advance composite like E-glass, S-glass, Carbon fiber, Kevlar are not yet confined at the aerospace industry but gradually these are taking over the position of other industries as well. Because of its attaining high intricacy in designing factors and as well as cheaper mould design and also less cost in production of few numbers. The applications of FRPs are spirally increasing. The aim of this project is to develop a BUS FRONT PANEL with a help of FRPs in order to sustain all the mechanical properties which are equivalent to the metals with the help of advanced computer aided software designs like ANSYS. In computer aided engineering to make the product proven in the realistic market.

  20. Compressive and bending behavior of sandwich panels with Octet truss core fabricated from wires

    Energy Technology Data Exchange (ETDEWEB)

    Lim, Ji Hyun; Nah, Seong Jun; Kang, Ki Ju [Chonnam National Univ., Gwangju (Korea, Republic of); Koo, Man Hoe [Agency for Defense Development, Daejeon (Korea, Republic of)

    2005-03-01

    Ultra light metal structures have been studied for several years because of their superior specific stiffness, strength and potential of multi functions. Many studies have been focused on how to manufacture ultra light metal structures and optimize them. In this study, we introduced a new idea to make sandwich panels having Octet truss cores. Wires bent in a shape of triangular wave were assembled to construct an Octet truss core and it was bonded with two face sheets to be a sandwich panel. The bending and compressive strength and stiffness were estimated through elementary mechanics for the sandwich specimens with two kinds of face sheets and the results were compared with the ones measured by experiments. Some aspects of assembling and mechanical behavior were discussed compared with Kagome core fabricated from wire, which had been introduced in the authors' previous work.

  1. 5 CFR 2471.1 - Request for Panel consideration; request for Panel approval of binding arbitration.

    Science.gov (United States)

    2010-01-01

    ... for Panel approval of binding arbitration. 2471.1 Section 2471.1 Administrative Personnel FEDERAL... consideration; request for Panel approval of binding arbitration. If voluntary arrangements, including the... procedure, which they have agreed to adopt, for binding arbitration of the negotiation impasse by filing...

  2. Performance comparison between silicon solar panel and dye-sensitized solar panel in Malaysia

    Science.gov (United States)

    Hamed, N. K. A.; Ahmad, M. K.; Urus, N. S. T.; Mohamad, F.; Nafarizal, N.; Ahmad, N.; Soon, C. F.; Ameruddin, A. S.; Faridah, A. B.; Shimomura, M.; Murakami, K.

    2017-09-01

    In carrying out experimental research in performance between silicon solar panel and dye-sensitive solar panel, we have been developing a device and a system. This system has been developed consisting of controllers, hardware and software. This system is capable to get most of the input sources. If only need to change the main circuit and coding for a different source input value. This device is able to get the ambient temperature, surface temperature, surrounding humidity, voltage with load, current with load, voltage without load and current without load and save the data into external memory. This device is able to withstand the heat and rain as it was fabricated in a waterproof box. This experiment was conducted to examine the performance of both the solar panels which are capable to maintain their stability and performance. A conclusion based on data populated, the distribution of data for dye-sensitized solar panel is much better than silicon solar panel as dye-sensitized solar panel is very sensitive to heat and not depend only on midday where is that is the maximum ambient temperature for both solar panel as silicon solar panel only can give maximum and high output only when midday.

  3. Data quality in probability-based online panels: Nonresponse, attrition, and panel conditioning

    NARCIS (Netherlands)

    Struminskaya, B.; Methodology and statistics for the behavioural and social sciences

    2014-01-01

    Online panels – surveys administered over the Internet in which persons are asked to complete surveys regularly – offer cost reductions compared to surveys that use more traditional modes of data collection (face-to-face, telephone, and mail). However, some characteristics of online panels may cause

  4. Data quality in probability-based online panels: Nonresponse, attrition, and panel conditioning

    NARCIS (Netherlands)

    Struminskaya, B.; Methodology and statistics for the behavioural and social sciences

    2014-01-01

    Online panels – surveys administered over the Internet in which persons are asked to complete surveys regularly – offer cost reductions compared to surveys that use more traditional modes of data collection (face-to-face, telephone, and mail). However, some characteristics of online panels may cause

  5. Immigration and Housing Rents in Canada: A Panel Data Analysis

    OpenAIRE

    Latif, E.

    2015-01-01

    This study examines the impact of new immigration on housing rent, using Canadian province-level panel data from 1983 to 2010. In its estimations, it utilises econometric methods such as panel unit roots, panel co-integration regressions and panel vector error correction models. Both fully-modified ordinary least squares and dynamic ordinary least squares models suggest that immigration flow has a significant positive impact on housing rent in the long run. The panel vector error correction m...

  6. Qualification test results for DOE solar photovoltaic flat panel procurement - PRDA 38

    Science.gov (United States)

    Griffith, J. S.

    1980-01-01

    Twelve types of prototypes modules for the DOE Photovoltaic Flat Panel Procurement (PRDA 38) were subjected to qualification tests at the Jet Propulsion Laboratory according to a new specification. Environmental exposures were carried out separately and included temperature cycling, humidity, wind simulation, and hail. The most serious problems discovered were reduced insulation resistance to ground and ground continuity of the metal frames, electrical degradation, erratic power readings, and delamination. The electrical and physical characteristics of the newly received modules are also given.

  7. Process for Design Optimization of Honeycomb Core Sandwich Panels for Blast Load Mitigation

    Science.gov (United States)

    2012-12-01

    damage causing potential of the blast impulse. Though metal sandwich panels have been used for a long time in aircraft and other light weight struc...aluminum alloy with bilinear isotropic-hardening elastoplastic material model is used for the foil. Since the yield and ultimate strength of the AL5052...foil are very close, bilinear elastoplastic mate- rial model with very low tangent modulus is a reasonable approximation. The adhesive is modeled as

  8. Automatic outdoor monitoring system for photovoltaic panels

    Science.gov (United States)

    Stefancich, Marco; Simpson, Lin; Chiesa, Matteo

    2016-05-01

    Long-term acquisition of solar panel performance parameters, for panels operated at maximum power point in their real environment, is of critical importance in the photovoltaic research sector. However, few options exist for the characterization of non-standard panels such as concentrated photovoltaic systems, heavily soiled or shaded panels or those operating under non-standard spectral illumination; certainly, it is difficult to find such a measurement system that is flexible and affordable enough to be adopted by the smaller research institutes or universities. We present here an instrument aiming to fill this gap, autonomously tracking and maintaining any solar panel at maximum power point while continuously monitoring its operational parameters and dissipating the produced energy without connection to the power grid. The instrument allows periodic acquisition of current-voltage curves to verify the employed maximum power point tracking approach. At the same time, with hardware schematics and software code being provided, it provides a flexible open development environment for the monitoring of non-standard generators like concentrator photovoltaic systems and to test novel power tracking approaches. The key issues, and the corresponding solutions, encountered in the design are analyzed in detail and the relevant schematics presented.

  9. Automatic outdoor monitoring system for photovoltaic panels.

    Science.gov (United States)

    Stefancich, Marco; Simpson, Lin; Chiesa, Matteo

    2016-05-01

    Long-term acquisition of solar panel performance parameters, for panels operated at maximum power point in their real environment, is of critical importance in the photovoltaic research sector. However, few options exist for the characterization of non-standard panels such as concentrated photovoltaic systems, heavily soiled or shaded panels or those operating under non-standard spectral illumination; certainly, it is difficult to find such a measurement system that is flexible and affordable enough to be adopted by the smaller research institutes or universities. We present here an instrument aiming to fill this gap, autonomously tracking and maintaining any solar panel at maximum power point while continuously monitoring its operational parameters and dissipating the produced energy without connection to the power grid. The instrument allows periodic acquisition of current-voltage curves to verify the employed maximum power point tracking approach. At the same time, with hardware schematics and software code being provided, it provides a flexible open development environment for the monitoring of non-standard generators like concentrator photovoltaic systems and to test novel power tracking approaches. The key issues, and the corresponding solutions, encountered in the design are analyzed in detail and the relevant schematics presented.

  10. Automatic outdoor monitoring system for photovoltaic panels

    Energy Technology Data Exchange (ETDEWEB)

    Stefancich, Marco [Consiglio Nazionale delle Ricerce, Istituto dei Materiali per l’Elettronica ed il Magnetismo (CNR-IMEM), Parco Area delle Scienze 37/A, 43124 Parma, Italy; Simpson, Lin [National Renewable Energy Laboratory, 15013 Denver West Parkway, Golden, Colorado 80401, USA; Chiesa, Matteo [Masdar Institute of Science and Technology, P.O. Box 54224, Masdar City, Abu Dhabi, United Arab Emirates

    2016-05-01

    Long-term acquisition of solar panel performance parameters, for panels operated at maximum power point in their real environment, is of critical importance in the photovoltaic research sector. However, few options exist for the characterization of non-standard panels such as concentrated photovoltaic systems, heavily soiled or shaded panels or those operating under non-standard spectral illumination; certainly, it is difficult to find such a measurement system that is flexible and affordable enough to be adopted by the smaller research institutes or universities. We present here an instrument aiming to fill this gap, autonomously tracking and maintaining any solar panel at maximum power point while continuously monitoring its operational parameters and dissipating the produced energy without connection to the power grid. The instrument allows periodic acquisition of current-voltage curves to verify the employed maximum power point tracking approach. At the same time, with hardware schematics and software code being provided, it provides a flexible open development environment for the monitoring of non-standard generators like concentrator photovoltaic systems and to test novel power tracking approaches. The key issues, and the corresponding solutions, encountered in the design are analyzed in detail and the relevant schematics presented.

  11. The Atomic Safety and Licensing Board Panel

    Energy Technology Data Exchange (ETDEWEB)

    NONE

    1998-03-01

    Through the Atomic Energy Act, Congress made is possible for the public to get a full and fair hearing on civilian nuclear matters. Individuals who are directly affected by any licensing action involving a facility producing or utilizing nuclear materials may participate in a formal hearing, on the record, before independent judges on the Atomic Safety and Licensing Board Panel (ASLBP or Panel). Frequently, in deciding whether a license, permit, amendment, or extension should be granted to a particular applicant, the Panel members must be more than mere umpires. If appropriate, they are authorized to go beyond the issues the parties place before them in order to identify, explore, and resolve significant questions involving threats to the public health and safety that come to a board`s attention during the proceedings. This brochure explains the purpose of the panel. Also addressed are: type of hearing handled; method of public participation; formality of hearings; high-level waste; other panel responsibilities and litigation technology.

  12. Penentuan Nilai Penyerapan Suara Pada Panel Dinding Beton Busa Sebagai Panel Alternatif Yang Ramah Lingkungan

    Directory of Open Access Journals (Sweden)

    Zulfian Zulfian

    2011-06-01

    Full Text Available Panel of foam concrete wall is a type of membrane panel which has maximum sound absorption and can create quite and environmentally friendly room. The purpose of this study was to determine the magnitudeof the sound absorption value using the Sabine formula in Reverberation Chamber at Syiah Kuala University acoustic laboratory. The result of this study show that peak value curve sound absorption of 0.67 accurs at the frequency of 250 Hz, and painting of the panel surface can increase the value of sound absorption to be 0.76 at the frequency of 250 Hz,but the slope of sound absorption value sharply decreased to be 0.07at the frequency of 1000 Hz. Treatment on the panel surface can increase or decrease the value of sound absorption especially at the low frequency regions. Keywords: Panel of foam concrete wall, Sabine formula, The value of sound absorption

  13. APPLIED ORIGAMI. Origami of thick panels.

    Science.gov (United States)

    Chen, Yan; Peng, Rui; You, Zhong

    2015-07-24

    Origami patterns, including the rigid origami patterns in which flat inflexible sheets are joined by creases, are primarily created for zero-thickness sheets. In order to apply them to fold structures such as roofs, solar panels, and space mirrors, for which thickness cannot be disregarded, various methods have been suggested. However, they generally involve adding materials to or offsetting panels away from the idealized sheet without altering the kinematic model used to simulate folding. We develop a comprehensive kinematic synthesis for rigid origami of thick panels that differs from the existing kinematic model but is capable of reproducing motions identical to that of zero-thickness origami. The approach, proven to be effective for typical origami, can be readily applied to fold real engineering structures.

  14. Recycling Wood Composite Panels: Characterizing Recycled Materials

    Directory of Open Access Journals (Sweden)

    Hui Wan

    2014-10-01

    Full Text Available Downgraded medium density fiberboard (MDF, particleboard (PB, and oriented strandboard (OSB panels were individually subjected to steam explosion treatment. Downgraded MDF and PB panels were separately treated with thermal chemical impregnation using 0.5% butanetetracarboxylic acid (BTCA. And downgraded PB panels were processed with mechanical hammermilling. The pH, buffer capacity, fiber length, and particle size of these recycled materials were evaluated. After the steam explosion and thermal chemical impregnation treatments, the pH and buffer capacity of recycled urea formaldehyde resin (UF-bonded MDF and PB furnishes increased and the fiber length decreased. The hammermilling of recycled PB was less likely to break particles down into sizes less than 1 mm2.

  15. High Performance OLED Panel and Luminaire

    Energy Technology Data Exchange (ETDEWEB)

    Spindler, Jeffrey [OLEDWorks LLC, Rochester, NY (United States)

    2017-02-20

    In this project, OLEDWorks developed and demonstrated the technology required to produce OLED lighting panels with high energy efficiency and excellent light quality. OLED panels developed in this program produce high quality warm white light with CRI greater than 85 and efficacy up to 80 lumens per watt (LPW). An OLED luminaire employing 24 of the high performance panels produces practical levels of illumination for general lighting, with a flux of over 2200 lumens at 60 LPW. This is a significant advance in the state of the art for OLED solid-state lighting (SSL), which is expected to be a complementary light source to the more advanced LED SSL technology that is rapidly replacing all other traditional forms of lighting.

  16. Optimal time lags in panel studies.

    Science.gov (United States)

    Dormann, Christian; Griffin, Mark A

    2015-12-01

    Cross-lagged regression coefficients are frequently used to test hypotheses in panel designs. However, these coefficients have particular properties making them difficult to interpret. In particular, cross-lagged regression coefficients may vary, depending on the respective time lags between different sets of measurement occasions. This article introduces the concept of an optimal time lag. Further, it is demonstrated that optimal time lags in panel studies are related to the stabilities of the variables investigated, and that in unidirectional systems, they may be unrelated to the size of possible true effects. The results presented also suggest that optimal time lags for panel designs are usually quite short. Implications are (a) that interpreting cross-lagged regression coefficients requires taking the time lag between measurement occasions into account, and (b) that in much research, far shorter time lags than those frequently found in the literature are justifiable, and we call for more "shortitudinal" studies in the future. (c) 2015 APA, all rights reserved).

  17. Case Study - Monitoring the Photovoltaic Panels

    Directory of Open Access Journals (Sweden)

    PACURAR Ana Talida

    2014-05-01

    Full Text Available The photovoltaic cell represents one of the most dynamic and attractive way to converts renewable energy sources in electricity production. That means to convert solar energy into electricity. In this paper is presented a analogy between two types of photovoltaic panels installed, with educational role for students. Also the objective of this paper is to estimate the performance of photovoltaic panels and to provide the best solution for industry. These two types of photovoltaic panels were monitored at the same time and taking into account the same weather conditions. In introduction of this paper is a short description regarding the silicon, because it is considered to be the most frequently used material for photovoltaic cell production at industrial level. In this context are mentioned below photovoltaic cells: mono-crystalline, polycrystalline, ribbon silicon and amorphous silicon (thin film cells. It is also presented for all these types of cells the structure, the function, the advantages and the disadvantages.

  18. Utilization of Bamboo as Lightweight Sandwich Panels

    Directory of Open Access Journals (Sweden)

    Suthon SRIVARO

    2016-05-01

    Full Text Available Lightweight sandwich panels consisting of bamboo faces and oil palm trunk core were manufactured using melamine urea formaldehyde with the resin content of 250 g/m2 (solid basis. The parameters examined were node and density of bamboo faces. Physical (board density, thickness swelling and water absorption and mechanical (modulus of elasticity and modulus of rupture properties of the sandwich board obtained were investigated and compared with other bamboo products and commercial wood based products. Result showed that this panel had better dimensional stability than those of other bamboo products but lower bending strength. Node of bamboo had no significant effect on any board properties examined. Most of board properties were influenced by bamboo face density. Comparing the properties to commercial wood based products, this panel could be used as wall/floor applications.

  19. Utilization of Bamboo as Lightweight Sandwich Panels

    Directory of Open Access Journals (Sweden)

    Suthon SRIVARO

    2016-05-01

    Full Text Available Lightweight sandwich panels consisting of bamboo faces and oil palm trunk core were manufactured using melamine urea formaldehyde with the resin content of 250 g/m2 (solid basis. The parameters examined were node and density of bamboo faces. Physical (board density, thickness swelling and water absorption and mechanical (modulus of elasticity and modulus of rupture properties of the sandwich board obtained were investigated and compared with other bamboo products and commercial wood based products. Result showed that this panel had better dimensional stability than those of other bamboo products but lower bending strength. Node of bamboo had no significant effect on any board properties examined. Most of board properties were influenced by bamboo face density. Comparing the properties to commercial wood based products, this panel could be used as wall/floor applications.

  20. Underwater Explosion Damage of Ship Hull Panels

    Directory of Open Access Journals (Sweden)

    K. Rarnajeyathilagam

    2003-10-01

    Full Text Available Underwater explosion is a major threat to ships and submarines in a war environment. The prediction of the mode and the extent of the failure is an essential step in designing for shock loading. The localised failure in a hull panel is severe compared to the global response of the ship. In this study, an attempt has been made to predict the response and failure modes of three types of hull panels (flat, concave, and convex. The shock loading on the hull panel has been estimated based on the Taylor's plate theory. The numerical analysis has been carried out using the CSAIGENSA (DYNA3D code that employs nonlinear finite element model.

  1. 基于机体振动的直升机桨毂阻尼故障诊断%DIAGNOSIS OF DAMPING FAULTS IN HELICOPTER ROTOR HUB BASED ON FUSELAGE VIBRATIONS

    Institute of Scientific and Technical Information of China (English)

    高亚东; 张曾锠

    2006-01-01

    研究了仅用机体振动信号诊断旋翼减摆器阻尼失效、轴向铰卡涩和水平铰卡涩3种桨毂阻尼故障的可行性.在旋翼试验台上分别设置上述3种阻尼故障,测取机体振动响应,利用快速傅立叶变换分析其频谱特征.分析表明,3种阻尼故障引起的机体振动谱图互不相同.采用概率神经网络实现了3种阻尼故障的正确分类.研究表明,仅用机体振动响应实现旋翼阻尼故障诊断是可行的.%Damping faults in a helicopter rotor hub are diagnosed by using vibration signals from the fuselage. Faults include the defective lag damper and raspings in its flap and feathering hinges. Experiments on the diagnosis of three faults are carried out on a rotor test rig with the chosen fault each time. Fuselage vibration signals from specified locations are measured and analyzed by the fast Fourier transform in the frequency domain. It is demonstrated that fuselage vibration frequency spectra induced by three faults are different fromeach other. The probabilistic neural network (PNN) is adopted to detect three faults. Results show that it is feasible to diagnose three faults only using fuselage vibration data.

  2. Quantitative Measurements of the Effects of Variations in Panel Density and Distributions for Panel Method Computer Programs

    Science.gov (United States)

    1980-01-01

    chosen for panel methods is NP, the total number of panels. The tacit assumption is that convergenre results as NP- 0. This choice presents great ...little evi- dence that other parameters such as panel taper ratio, Xp, or panel sweep -11 NADC-80029-60 angle, Ap, had as great an effect as PAR. PAR can...independent surface or one segment of a wing which is devided into several trapezoidal panels. WING Variables ROOTLE X coordinate of wing root leading edge

  3. Fire Resistant Panels for the Tunnel Linings

    Directory of Open Access Journals (Sweden)

    Gravit Marina

    2016-01-01

    Full Text Available Presents the results of studies of innovative materials in the field of experimental and theoretical research fire resistance fireproof panels Pyro-Safe Aestuver T. Owing to the assembly simplicity, materials cheapness, high ecological standard, recycling, reuse potential, are benefit. Research work is running to improve the knowledge about fireproof panels Pyro-Safe Aestuver T for tunnel lining, its basic performance, its long term behavior and in particular also its fire proof for example when used for the lining of road tunnels.

  4. Report of the Environmental Legislation Review Panel

    Energy Technology Data Exchange (ETDEWEB)

    1991-01-01

    A review panel was established in October 1990 to hold public meetings throughout Alberta for providing the public with opportunities to express their views on draft environmental legislation. Overviews of public comments and review panel recommendations regarding the draft legislation are summarized in such categories as sustainable development, discretionary powers, environmental impact assessments, approvals, contaminant releases, conservation and reclamation, waste minimization and recycling, the polluter-pays concept, the role of local government, dispute resolution mechanisms, protected areas, environmental protection orders, and enforcement of the legislation.

  5. Compressive strength of thick composite panels

    DEFF Research Database (Denmark)

    Branner, Kim; Berring, Peter

    2011-01-01

    The aim of this study is to investigate how much the compressive strength of thick composite panels is reduced due to delaminations and to investigate under which conditions a delamination will grow. Understanding of this is essential in order to move forward the design limits used in the structu......The aim of this study is to investigate how much the compressive strength of thick composite panels is reduced due to delaminations and to investigate under which conditions a delamination will grow. Understanding of this is essential in order to move forward the design limits used...

  6. Supersonic Flutter of Laminated Curved Panels

    Directory of Open Access Journals (Sweden)

    M. Ganapathi

    1995-04-01

    Full Text Available Supersonic flutter analysis of laminated composite curved panels is investigated using doubly-curved, quadrilateral, shear flexible, shell element based on field-consistency approach. The formulation includes transverse shear deformation, in-plane and rotary inertias. The aerodynamic force is evaluated using two-dimensional static aerodynamic approximation for high supersonic flow. Initially, the model developed here is verified for the flutter analysis of flat plates. Numerical results are presented for isotropic, orthotropic and laminated anisotropic curved panels. A detailed parametric study is carried out to observe the effects of aspect and thickness ratios, number of layers, lamination scheme, and boundary conditions on flutter boundary.

  7. Pantex Falling Man - Independent Review Panel Report.

    Energy Technology Data Exchange (ETDEWEB)

    Brannon, Nathan Gregory; L. Bertolini, N. Brannon, J. Olsen, B. Price, M. Steinzig, R. Wardle, & M. Winfield

    2014-11-01

    Consolidated Nuclear Security (CNS) Pantex took the initiative to organize a Review Panel of subject matter experts to independently assess the adequacy of the Pantex Tripping Man Analysis methodology. The purpose of this report is to capture the details of the assessment including the scope, approach, results, and detailed Appendices. Along with the assessment of the analysis methodology, the panel evaluated the adequacy with which the methodology was applied as well as congruence with Department of Energy (DOE) standards 3009 and 3016. The approach included the review of relevant documentation, interactive discussion with Pantex staff, and the iterative process of evaluating critical lines of inquiry.

  8. Nonlinear dynamic analysis of sandwich panels

    Science.gov (United States)

    Lush, A. M.

    1984-01-01

    Two analytical techniques applicable to large deflection dynamic response calculations for pressure loaded composite sandwich panels are demonstrated. One technique utilizes finite element modeling with a single equivalent layer representing the face sheets and core. The other technique utilizes the modal analysis computer code DEPROP which was recently modified to include transverse shear deformation in a core layer. The example problem consists of a simply supported rectangular sandwich panel. Included are comparisons of linear and nonlinear static response calculations, in addition to dynamic response calculations.

  9. Sustainable Absorption Panels from Agricultural Wastes

    Directory of Open Access Journals (Sweden)

    Ismail F.Z.

    2014-01-01

    Full Text Available Noise has become a serious environmental problem and there are demands for alternative sustainable materials which capable to reduce the noise level at various frequency ranges. Therefore, the aim of this research is to study the potential of turning the agricultural waste and waste paper into a sound absorption panel. For the purpose of this study, combination of two materials was under studied; coconut coir fibre from agriculture waste and shredded waste paper from the office. There were two main objective of the research; first is to develop absorption panels from coconut coir powder that available locally with a combination of shredded paper at different percentage of mixture. Second objective is to identify the absorption rate of the panels. The study encompasses the fabrication of the particle board using the coconut husk powder mix with shredded waste paper and using the gypsum powder as the binder for the two materials. Four acoustic panels of size 0.5m x 0.5m and 0.012 m thick were fabricated with different mix ratio; 25% of coconut coir powder mixed with 75% of shredded waste papers for sample 1, 50% both of the material for sample 2, 75% of coconut coir powder mixed with 25% of shredded waste paper for sample 3, and lastly 100% of coconut coir powder for sample 4. The absorption coefficient of the panels was tested in a reverberation chamber and in accordance with ISO 354:1985 standards. Based on the results, sample 1 gave the highest absorption coefficient compared to sample 2, 3 and 4. It can be concluded that the acoustic panel made from a mixture of 25% coconut coir powder with 75% shredded waste paper provided higher absorption coefficient compared to the performance of the other samples. This might be caused by the size of the coir powder which is very small, creating less void space in between the panel and thus causing it to absorb less sound. Since sound absorption is very much affected by the availability of void space of

  10. Experimental static aerodynamic forces and moments at high subsonic speeds on a missile model during simulated launching from the midsemispan location of a 45 degree sweptback wing-fuselage-pylon combination

    Science.gov (United States)

    Alford, William J; King, Thomas, Jr

    1957-01-01

    An investigation was made at high subsonic speeds in the Langley high-speed 7- by 10-foot tunnel to determine the static aerodynamic forces and moments on a missile model during simulated launching from the midsemispan location of a 45 degree sweptback wing-fuselage-pylon combination. The results indicated significant variations in all the aerodynamic components with changes in chordwise location of the missile. Increasing the angle of attack caused increases in the induced effects on the missile model because of the wing-fuselage-pylon combination. Increasing the Mach number had little effect on the variations of the missile aerodynamic characteristics with angle of attack except that nonlinearities were incurred at smaller angles of attack for the higher Mach numbers. The effects of finite wing thickness on the missile characteristics, at zero angle of attack, increase with increasing Mach number. The effects of the pylon on the missile characteristics were to causeincreases in the rolling-moment variation with angle of attack and a negative displacement of the pitching-moment curves at zero angle of attack. The effects of skewing the missile in the lateral direction relative to and sideslipping the missile with the wing-fuselage-pylon combination were to cause additional increments in side force at zero angle of attack. For the missile yawing moments the effects of changes in skew or sideslip angles were qualitatively as would be expected from consideration of the isolated missile characteristics, although there existed differences in theyawing-moment magnitudes.

  11. Environmental challenges of anthropogenic metals flows and cycles

    DEFF Research Database (Denmark)

    van der Voet, Ester; Salminen, Reijo; Eckelman, Matthew;

    This report from the UNEP-hosted International Resource Panel, Environmental Risk and Challenges of Anthropogenic Metals Flows and Cycles, gives a clear picture of the potential environmental impacts of metals at different stages of the life-cycle while linking with other areas of resource use...... such as water, food production and energy....

  12. Navier-Stokes solutions about the F/A-18 wing-LEX-fuselage configuration with multi-block structured grids

    Science.gov (United States)

    Ghaffari, Farhad; Luckring, James M.; Thomas, James L.; Bates, Brent L.; Biedron, Robert T.

    1991-01-01

    Three-dimensional thin-layer Navier-Stokes computations are presented for the F/A-18 configuration. The modeled configuration includes an accurate surface representation of the fuselage, leading-edge-extension, as well as the wing with and without leading-edge-flap deflection. A multi-block structured volume grid with various topologies is generated using transfinite interpolation technique. The flowfield domain is divided into twenty blocks, each representing a particular geometrical complexity of the configuration. The results are obtained from an algorithm for solving the compressible Navier-Stokes equations that incorporates an upwind-biased, flux-difference-splitting approach. In addition, a newly developed capability that allows for generalized surface patching among blocks is employed. Turbulent results are presented for flow conditions that correspond to recent NASA F/A-18 High Alpha Research Vehicle flight experiments. Good correlations between the computations and the flight test results are disclosed for both surface flow patterns as well as surface pressure distributions.

  13. Pressure distributions on a 0.04-scale model of the Space Shuttle Orbiter's forward fuselage in the Langley unitary plan wind tunnel

    Science.gov (United States)

    Bradley, P. F.; Siemers, P. M., III; Flanagan, P. F.; Henry, M. W.

    1983-01-01

    Pressure distribution tests on a 0.04-scale model of the forward fuselage of the Space Shuttle Orbiter are presented without analysis. The tests were completed in the Langley Unitary Plan Wind Tunnel (UPWT). The UPWT has two different test sections operating in the continuous mode. Each test section has its own Mach number range. The model was tested at angles of attack from -2.5 deg to 30 deg and angles of sideslip from -5 deg to 5 deg in both test sections. The test Reynolds number was 6.6 x 10 to the 6th power per meter. The tests were conducted in support of the development of the Shuttle Entry Air Data System (SEADS). In addition to modeling the 20 SEADS pressure orifices, the wind-tunnel model was also instrumented with orifices to match Development Flight Instrumentation (DFI) port locations currently existing on the Space Shuttle Orbiter Columbia (OV-102). This DFI simulation has provided a means for comparisons between reentry flight pressure data and wind-tunnel data.

  14. Analysing sensory panel performance in a proficiency test using the PanelCheck software

    DEFF Research Database (Denmark)

    Tomic, O.; Luciano, G.; Nilsen, A.

    2010-01-01

    results plays an important role as this provides a time saving and efficient way of screening and investigating sensory panel performances. Most of the statistical methods used in this paper are available in the open source software PanelCheck, which may be downloaded and used for free.......Check software, a workflow is proposed that guides the user through the data analysis process. This allows practitioners and non-statisticians to get an overview over panel performances in a rapid manner without the need to be familiar with details on the statistical methods. Visualisation of data analysis...

  15. Low frequency noise reduction using stiff light composite panels

    Institute of Scientific and Technical Information of China (English)

    DENG Yongchang; LIN Weizheng

    2003-01-01

    The experiment presented in this paper is to investigate and analyze the noise reduction at low frequency using stiff light composite panels. Since these composite panels are made of lightweight and stiff materials, this actuation strategy will enable the creation of composite panels for duct noise control without using traditional heavy structural mass. The results suggest that the mass-spring resonance absorption in the case of a comparatively stiff thick panel with a thin flexible plate is more efficient with minimum weight, when subjected to low-frequency (<500 Hz). The efficiency of the panel absorber depends on the mass of the thin flexible plate and the stiffness of the panel.

  16. Influence of plywood grain direction on sandwich panel bending properties

    OpenAIRE

    Jaroslav Kljak; Mladen Brezović; Alan Antonović

    2009-01-01

    This paper investigates the influence of plywood grain direction on bending properties of a sandwich panel, as well as on stress distribution in each layer. Experimental sandwich panels (tnom= 29 mm) were made of two three-ply plywood panels and a rigid PVC core between them. Grain directions of plywood panels were between 0° and 90°, continuously raised by 15°. Seven models of sandwich panels were made. Bending properties of a sandwich panel was determined by three point bending method and s...

  17. A multifunctional heat pipe sandwich panel structure

    Energy Technology Data Exchange (ETDEWEB)

    Queheillalt, Douglas T.; Wadley, Haydn N.G. [University of Virginia, Department of Materials Science and Engineering, 140 Chemistry Way, P.O. Box 400745, Charlottesville, VA 22904 (United States); Carbajal, Gerardo [University of Turabo, School of Engineering, P.O. Box 3030, Gurabo 00778 (Puerto Rico); Peterson, G.P. [University of Colorado at Boulder, 914 Broadway, Boulder, CO 80309 (United States)

    2008-01-15

    A multifunctional sandwich panel combining efficient structural load support and thermal management characteristics has been designed and experimentally assessed. The concept is based upon a truncated, square honeycomb sandwich structure. In closed cell honeycomb structures, the transport of heat from one face to the other occurs by a combination of conduction through the webs and convection/radiation within the cells. Here, much more effective heat transport is achieved by multifunctionally utilizing the core as a heat pipe sandwich panel. Its interior consists of a 6061 aluminum truncated-square honeycomb core covered with a stochastic open-cell nickel foam wick. An electroless nickel plating barrier layer inhibited the chemical reaction between the deionized water working fluid and the aluminum structure, retarding the generation of non-condensable hydrogen gas. A thermodynamic model was used to guide the design of the heat pipe sandwich panel. We describe the results of a series of experiments that validate the operational principle of the multifunctional heat pipe sandwich panel and characterize its transient response to an intense localized heat source. The systems measured thermal response to a localized heat source agrees well with that predicted by a finite difference method model used to predict the thermal response. (author)

  18. 77 FR 4583 - Meetings of Humanities Panel

    Science.gov (United States)

    2012-01-30

    ... 20540. Program: This meeting will review applications for American History and Foreign Relations...) 606-8282. SUPPLEMENTARY INFORMATION: The proposed meetings are for the purpose of panel review... have determined that these meetings will be closed to the public pursuant to subsections (c) (4), and...

  19. Identification of Macroeconomic Factors in Large Panels

    DEFF Research Database (Denmark)

    Bork, Lasse; Dewachter, Hans; Houssa, Romain

    standard practices in the SVAR literature. Estimators based on the EM algorithm are developped. We apply this framework to a large panel of US monthly macroeconomic series. In particular, we identify nine macroeconomic factors and discuss the economic impact of monetary policy stocks. The results...

  20. Vertical reflector for bifacial PV-panels

    DEFF Research Database (Denmark)

    Jakobsen, Michael Linde; Thorsteinsson, Sune; Poulsen, Peter Behrensdorff;

    2016-01-01

    Bifacial solar modules offer an interesting price/performance ratio, and much work has been focused on directing the ground albedo to the back of the solar cells. In this work we design and develop a reflector for a vertical bifacial panel, with the objective to optimize the energy harvest...

  1. Limited dependent variable models for panel data

    NARCIS (Netherlands)

    Charlier, E.

    1997-01-01

    Many economic phenomena require limited variable models for an appropriate treatment. In addition, panel data models allow the inclusion of unobserved individual-specific effects. These models are combined in this thesis. Distributional assumptions in the limited dependent variable models are

  2. Nearly Unbiased Estimationin Dynamic Panel Data Models

    NARCIS (Netherlands)

    M.A. Carree (Martin)

    2002-01-01

    textabstractThis paper introduces two easy to calculate estimators with desirable properties for the autoregressive parameter in dynamic panel data models. The estimators are (nearly) unbiased and perform satisfactorily even for small samples in either the time-series or cross-section dimension.

  3. 77 FR 71873 - Disciplinary Appeals Board Panel

    Science.gov (United States)

    2012-12-04

    ... AFFAIRS Disciplinary Appeals Board Panel AGENCY: Department of Veterans Affairs. ACTION: Notice with... Relations and Performance Management Service (051), Office of Human Resources Management, Department of... of 1991 (Pub. L. 102-40), dated May 7, 1991, revised the disciplinary grievance and appeal procedures...

  4. 76 FR 77327 - Disciplinary Appeals Board Panel

    Science.gov (United States)

    2011-12-12

    ... AFFAIRS Disciplinary Appeals Board Panel AGENCY: Department of Veterans Affairs. ACTION: Notice with..., Employee Relations and Performance Management Service, Office of Human Resources Management, Department of... of 1991 (Pub. L. 102-40), dated May 7, 1991, revised the disciplinary grievance and appeal procedures...

  5. 76 FR 8848 - Disciplinary Appeals Board Panel

    Science.gov (United States)

    2011-02-15

    ... AFFAIRS Disciplinary Appeals Board Panel AGENCY: Department of Veterans Affairs. ACTION: Notice with..., Employee Relations and ] Performance Management Service, Office of Human Resources Management, Department... of 1991 (Pub. L. 102-40), dated May 7, 1991, revised the disciplinary grievance and appeal procedures...

  6. Panel Analysis of Approaches to Family Therapy.

    Science.gov (United States)

    Palisi, Anthony T.; Ruzicka, Mary F.

    1981-01-01

    Describes Cattell's model as inclusive of the work of family therapists of all orientations. The model defines groups as having interrelated aspects, and all variables related to group phenomena as fitting into three panels: population traits, characteristics of internal structure, and syntality traits. Suggests model gives uniformity to field.…

  7. Compressive Strength of Longitudinally Stiffened GRP Panels

    DEFF Research Database (Denmark)

    Böhme, J.; Noury, P.; Riber, Hans Jørgen

    1996-01-01

    A structural analysis of a cross stiffened orthotropic GRP panel subjected to uniaxial compressive loads is carried out. Analytical solutions to the buckling of such structures are proposed and validated by a finite element analysis. Both analytical and finite element approaches confirm an identi...

  8. Robust control investigations for equipment loaded panels

    DEFF Research Database (Denmark)

    Aglietti, G.S.; Langley, R.S.; Rogers, E.

    1998-01-01

    This paper develops a modelling technique for equipment load panels which directly produces (adequate) models of the underlying dynamics on which to base robust controller design/evaluations. This technique is based on the use of the Lagrange's equations of motion and the resulting models...

  9. X-joints in composite sandwich panels

    NARCIS (Netherlands)

    Vredeveldt, A.W.; Janssen, G.Th.M.

    1998-01-01

    The small structural weight of fast large ships such as fast mono hulls or catamaran type of ships is of extreme importance to their success. One possible light weight structural solution is the sandwich panel with fibre reinforced laminates and a balsa, honeycomb or foam core. A severe obstacle for

  10. Rethinking critical criminology - A panel discussion

    NARCIS (Netherlands)

    R. van Swaaningen (René); I. Taylor (Ian)

    1994-01-01

    textabstractThis paper takes the form of a report on the panel discussion held at the conclusion of the 1992 meetings of the European Group for the Study of Deviance and Social Control in Padua in September 1992. In the light of a perceived crisis of relevance for earlier, 1970s notions of critique

  11. 75 FR 27825 - Arts Advisory Panel

    Science.gov (United States)

    2010-05-18

    ...: 2010-11812] NATIONAL FOUNDATION ON THE ARTS AND THE HUMANITIES National Endowment for the Arts Arts... amended, notice is hereby given that one meeting of the Arts Advisory Panel to the National Council on the Arts will be held at the Nancy Hanks Center, 1100 Pennsylvania Avenue, NW., Washington, DC 20506...

  12. 77 FR 13154 - Arts Advisory Panel Meeting

    Science.gov (United States)

    2012-03-05

    ... ARTS AND THE HUMANITIES Arts Advisory Panel Meeting AGENCY: National Endowment for the Arts, National Foundation on the Arts and Humanities. ACTION: Notice--meeting. Pursuant to Section 10(a)(2) of the Federal Advisory Committee Act (Pub. L. 92-463), as amended, notice is hereby given that a meeting of the...

  13. 77 FR 2766 - Arts Advisory Panel Meeting

    Science.gov (United States)

    2012-01-19

    ... ARTS AND THE HUMANITIES Arts Advisory Panel Meeting AGENCY: National Endowment for the Arts, National Foundation on the Arts and Humanities. ACTION: Notice; correction. SUMMARY: Pursuant to Section 10(a)(2) of... Arts (state folk arts projects review) meeting, scheduled for January 19-20, 2012 in Room 714....

  14. Vertical reflector for bifacial PV-panels

    DEFF Research Database (Denmark)

    Jakobsen, Michael Linde; Thorsteinsson, Sune; Poulsen, Peter Behrensdorff

    2016-01-01

    Bifacial solar modules offer an interesting price/performance ratio, and much work has been focused on directing the ground albedo to the back of the solar cells. In this work we design and develop a reflector for a vertical bifacial panel, with the objective to optimize the energy harvest...

  15. Developing a solar panel testing system

    Directory of Open Access Journals (Sweden)

    Árpád Rácz

    2009-10-01

    Full Text Available Solar energy is increasingly used togenerate electricity for individual households. There isa wide variety of solar panel technologies, whichshould be tested at an individual level during theirlifetime. In this paper, the development of a testingstation at the University of Debrecen is presented. Thetesting system can be used for research andeducational purposes and for in field applicationsequally well.

  16. Advances in micro-perforated panel absorbers

    Institute of Scientific and Technical Information of China (English)

    LIU Ke; TIAN Jing; JIAO Fenglei; L(U) Yadong

    2006-01-01

    Theoretical and experimental investigations on the performance of micro-perforated-panel absorbers are reviewed in this paper. By reviewing recent research work, this paper reveals a relationship between the maximum absorption coefficient and the limit of the absorption frequency bandwidth. It has been demonstrated that the absorption frequency bandwidth can be extended up to 3 or 4 octaves as the diameters of the micro-holes decrease. This has become possible with the development of the technologies for manufacturing micro-perforated panels,such as laser drilling, powder metallurgy, welded meshing and electro-etching to form micrometer order holes. In this paper, absorption characteristics of such absorbers in random fields and in high sound intensity are discussed both theoretically and experimentally. A new absorbing structure based on micro-perforated-panel absorbers demonstrate experimentally high sound absorption capability. This review shows that the micro-perforated-panel absorber has potentials to be one of ideal absorbing materials in the 21st century.

  17. Airborne Sense and Avoid Radar Panel

    Science.gov (United States)

    2014-10-01

    land and crop surveys, aerial photography , and critical infrastructure protection—their widespread usage within the National Airspace System is...RFIC) developed for the ABSAA panel enable state-of-the- art performance by providing two indepen- dent channels for the amplification, the phase

  18. 77 FR 56875 - Meetings of Humanities Panel

    Science.gov (United States)

    2012-09-14

    ... program on the subject of Art History, submitted to the Division of Preservation and Access. 9. Date... of Art History, submitted to the Division of Public Programs. 14. Date: October 30, 2012. Time: 8:30... ARTS AND THE HUMANITIES Meetings of Humanities Panel AGENCY: National Endowment for the...

  19. X-joints in composite sandwich panels

    NARCIS (Netherlands)

    Vredeveldt, A.W.; Janssen, G.Th.M.

    1998-01-01

    The small structural weight of fast large ships such as fast mono hulls or catamaran type of ships is of extreme importance to their success. One possible light weight structural solution is the sandwich panel with fibre reinforced laminates and a balsa, honeycomb or foam core. A severe obstacle for

  20. Compressive Strength of Longitudinally Stiffened GRP Panels

    DEFF Research Database (Denmark)

    Böhme, J.; Noury, P.; Riber, Hans Jørgen

    1996-01-01

    A structural analysis of a cross stiffened orthotropic GRP panel subjected to uniaxial compressive loads is carried out. Analytical solutions to the buckling of such structures are proposed and validated by a finite element analysis. Both analytical and finite element approaches confirm an identi...

  1. Recent Discoveries on Antwerp Panel Makers' Marks

    DEFF Research Database (Denmark)

    Wadum, Jørgen

    1993-01-01

    more can be added to our comprehension of the way the panel makers worked in Antwerp. In the following paper I shall give a brief summary of the present state of research, as well as outline the complicated task of interpreting these marks and their use as a dating tool. The ready-made supports...

  2. Panel data specifications in nonparametric kernel regression

    DEFF Research Database (Denmark)

    Czekaj, Tomasz Gerard; Henningsen, Arne

    parametric panel data estimators to analyse the production technology of Polish crop farms. The results of our nonparametric kernel regressions generally differ from the estimates of the parametric models but they only slightly depend on the choice of the kernel functions. Based on economic reasoning, we...

  3. Design scenarios for flat panel photobioreactors

    NARCIS (Netherlands)

    Slegers, P.M.; Wijffels, R.H.; Straten, van G.; Boxtel, van A.J.B.

    2011-01-01

    Evaluation of the potential of algae production for biofuel and other products at various locations throughout the world requires assessment of algae productivity under varying light conditions and different reactor layouts. A model was developed to predict algae biomass production in flat panel

  4. Absorptive coating for aluminum solar panels

    Science.gov (United States)

    Desmet, D.; Jason, A.; Parr, A.

    1979-01-01

    Method for coating forming coating of copper oxide from copper component of sheet aluminum/copper alloy provides strong durable solar heat collector panels. Copper oxide coating has solar absorption characteristics similar to black chrome and is much simpler and less costly to produce.

  5. 78 FR 16711 - Meetings of Humanities Panel

    Science.gov (United States)

    2013-03-18

    ... April, 2013 as follows. The purpose of the meetings is for panel review, discussion, evaluation, and... discuss applications for the Seminars and Institutes for College and University Teachers grant program...: 315. This meeting will discuss applications for the Seminars and Institutes for School Teachers...

  6. 78 FR 22345 - Meetings of Humanities Panel

    Science.gov (United States)

    2013-04-15

    ... for panel review, discussion, evaluation, and recommendation of applications for financial assistance... for the Institutes for College and University Teachers grant program, submitted to the Division of... applications for the Institutes for School Teachers grant program, submitted to the Division of...

  7. Applicability valuation for evaluation of surface deflection in automotive outer panels

    Directory of Open Access Journals (Sweden)

    D.H. Park

    2008-12-01

    Full Text Available Purpose: Upon unloading in a forming process there is elastic recovery, which is the release of the elasticstrains and the redistribution of the residual stresses through the thickness direction, thus producing surfacedeflection. It causes changes in shape and dimensions that can create major problem in the external appearanceof outer panels. Thus surface deflection prediction is an important issue in sheet metal forming industry. Manyfactors could affect surface deflection in the process, such as material variations in mechanical properties, sheetthickness, tool geometry, processing parameters and lubricant condition.Design/methodology/approach: Numerical simulation of process was performed by the use of finite elementmethod, paying attention particularly to the thickness distribution and surface deflection of the drawn outerpanel and the outline flange during forming. Simulation procedures of automotive outer panel as large size shapeare as follows; 1 Acquisition of drawing parts 2 Laser scanning for generating CAD model 3 CAD modelgeneration 4 Simulation model operation 5 Simulation execution and analyses of simulation results.Findings: The development of automation in stamping and assembly processes of automobile manufacture willrequire an excellent surface quality of formed panels and also their accurate dimensions.Practical implications: The use of high strength steel sheets in the manufacturing of automobile outer panels hasincreased in the automotive industry over the years because of its lightweight and fuel-efficient improvement.But one of the major concerns of stamping is surface deflection in the formed outer panels. Hence, to be costeffective, accurate prediction must be made of its formability. The automotive industry places rigid constraintson final shape and dimensional tolerances as well as external appearance quality of outer panels. The numericalsimulation makes it possible to design and optimize the total process to a level

  8. An automatic gore panel mapping system

    Science.gov (United States)

    Shiver, John D.; Phelps, Norman N.

    1990-01-01

    The Automatic Gore Mapping System is being developed to reduce the time and labor costs associated with manufacturing the External Tank. The present chem-milling processes and procedures are discussed. The down loading of the simulation of the system has to be performed to verify that the simulation package will translate the simulation code into robot code. Also a simulation of this system has to be programmed for a gantry robot instead of the articulating robot that is presently in the system. It was discovered using the simulation package that the articulation robot cannot reach all the point on some of the panels, therefore when the system is ready for production, a gantry robot will be used. Also a hydrosensor system is being developed to replace the point-to-point contact probe. The hydrosensor will allow the robot to perform a non-contact continuous scan of the panel. It will also provide a faster scan of the panel because it will eliminate the in-and-out movement required for the present end effector. The system software is currently being modified so that the hydrosensor will work with the system. The hydrosensor consists of a Krautkramer-Branson transducer encased in a plexiglass nozzle. The water stream pumped through the nozzle is the couplant for the probe. Also, software is being written so that the robot will have the ability to draw the contour lines on the panel displaying the out-of-tolerance regions. Presently the contour lines can only be displayed on the computer screens. Research is also being performed on improving and automating the method of scribing the panels. Presently the panels are manually scribed with a sharp knife. The use of a low power laser or water jet is being studied as a method of scribing the panels. The contour drawing pen will be replaced with scribing tool and the robot will then move along the contour lines. With these developments the Automatic Gore Mapping Systems will provide a reduction in time and labor costs

  9. Sound radiation and transmission characteristics of finite composite panels

    Science.gov (United States)

    Patil, Avinash R.

    2000-10-01

    Laminated composite and sandwich composite panels are used widely in aircraft and space structures. Corrugated panels or bead-stiffened panels are used in building structures and automobiles. In these applications, the sound transmission through such panels is an important factor in their design. Their sound radiation characteristics are also important. These panels have been analyzed earlier mostly by assuming them to be of infinite size. But in real applications, only finite panels were used. The finite size of a panel affects its sound radiation below the critical frequency and consequently it also affects the resonant sound transmission through the panel. In the present work, such panels are analyzed considering their finite size. The analysis presented in this thesis is restricted to laminated composite panels, which have no coupling between bending and twisting. Corrugated panels with corrugations in only one direction were analyzed in this work. Sandwich composite panels, which have a symmetric configuration, were analyzed as well. Statistical Energy Analysis (SEA) was used for this purpose. The dispersion relations for laminated composite, sandwich composite and corrugated panels were studied. The phenomenon known as 'critical frequency band' was explained. Wavenumber diagrams were plotted for various frequencies. The mode count was obtained for the panels. A frequency averaged radiation efficiency was obtained from first principles. These results were used to calculate various SEA parameters. The transmission loss of the panels was predicted by using SEA and it is compared with the experimental results obtained by other researchers. The parametric analysis and optimization of a sandwich composite panel was carried out here. The analysis in this thesis is useful in the design of panels used for various engineering applications.

  10. A general panel sizing computer code and its application to composite structural panels

    Science.gov (United States)

    Anderson, M. S.; Stroud, W. J.

    1978-01-01

    A computer code for obtaining the dimensions of optimum (least mass) stiffened composite structural panels is described. The procedure, which is based on nonlinear mathematical programming and a rigorous buckling analysis, is applicable to general cross sections under general loading conditions causing buckling. A simplified method of accounting for bow-type imperfections is also included. Design studies in the form of structural efficiency charts for axial compression loading are made with the code for blade and hat stiffened panels. The effects on panel mass of imperfections, material strength limitations, and panel stiffness requirements are also examined. Comparisons with previously published experimental data show that accounting for imperfections improves correlation between theory and experiment.

  11. PMARC - PANEL METHOD AMES RESEARCH CENTER

    Science.gov (United States)

    Ashby, D. L.

    1994-01-01

    Panel methods are moderate cost tools for solving a wide range of engineering problems. PMARC (Panel Method Ames Research Center) is a potential flow panel code that numerically predicts flow fields around complex three-dimensional geometries. PMARC's predecessor was a panel code named VSAERO which was developed for NASA by Analytical Methods, Inc. PMARC is a new program with many additional subroutines and a well-documented code suitable for powered-lift aerodynamic predictions. The program's open architecture facilitates modifications or additions of new features. Another improvement is the adjustable size code which allows for an optimum match between the computer hardware available to the user and the size of the problem being solved. PMARC can be resized (the maximum number of panels can be changed) in a matter of minutes. Several other state-of-the-art PMARC features include internal flow modeling for ducts and wind tunnel test sections, simple jet plume modeling essential for the analysis and design of powered-lift aircraft, and a time-stepping wake model which allows the study of both steady and unsteady motions. PMARC is a low-order panel method, which means the singularities are distributed with constant strength over each panel. In many cases low-order methods can provide nearly the same accuracy as higher order methods (where the singularities are allowed to vary linearly or quadratically over each panel). Low-order methods have the advantage of a shorter computation time and do not require exact matching between panels. The flow problem is solved by assuming that the body is at rest in a moving flow field. The body is modeled as a closed surface which divides space into two regions -- one region contains the flow field of interest and the other contains a fictitious flow. External flow problems, such as a wing in a uniform stream, have the external region as the flow field of interest and the internal flow as the fictitious flow. This arrangement is

  12. El Salvador - Rural Electrification Sub-Activity: Solar Panel Component

    Data.gov (United States)

    Millennium Challenge Corporation — This is a summative qualitative performance evaluation (PE) of the solar panel component of the solar panel component of the RE Sub-Activity. The final report will...

  13. Strengthening masonry infill panels using engineered cementitious composites

    DEFF Research Database (Denmark)

    Dehghani, Ayoub; Fischer, Gregor; Nateghi Alahi, Fariborz

    2015-01-01

    This comprehensive experimental study aims at investigating the behavior of masonry infill panels strengthened by fiber reinforced engineered cementitious composites (ECC). The experimental program included testing of materials, masonry elements and panels. Material tests were carried out first f...

  14. Multipurpose Panel Display Device Investigation. [technology assessment and product development

    Science.gov (United States)

    Sliwa, R.

    1977-01-01

    A multipurpose panel was developed to provide a flexible control and a LED display panel with easily changeable nomenclature for use in applications where panel space is limited, but where a number of similar subsystems must be controlled, or where basic panel nomenclature and functions must be changed rapidly, as in the case of between mission changes of space shuttle payloads. In the first application, panel area limitations are overcome by time sharing a central control panel among several subsystems. In the latter case, entire control panel changes are effected by simply replacing a memory module, thereby reducing the extent of installation and checkout procedures between missions. Several types of control technologies (other than LED's) which show potential in meeting criteria for overcoming limitations of the panel are assessed.

  15. 75 FR 57102 - Occupational Information Development Advisory Panel Meeting; Correction

    Science.gov (United States)

    2010-09-17

    ... ADMINISTRATION Occupational Information Development Advisory Panel Meeting; Correction AGENCY: Social Security Administration. ACTION: Notice; correction. SUMMARY: The Social Security Administration published a document in...: Occupational Information Development Advisory Panel, Social Security Administration, 6401 Security...

  16. 76 FR 70804 - Occupational Information Development Advisory Panel Meeting

    Science.gov (United States)

    2011-11-15

    ... From the Federal Register Online via the Government Publishing Office SOCIAL SECURITY ADMINISTRATION Occupational Information Development Advisory Panel Meeting AGENCY: Social Security Administration... Advisory Panel, Social Security Administration, 6401 Security Boulevard, Robert M. Ball Federal Building,...

  17. Electrohydraulic Forming of Near-Net Shape Automotive Panels

    Energy Technology Data Exchange (ETDEWEB)

    Golovaschenko, Sergey F.

    2013-09-26

    The objective of this project was to develop the electrohydraulic forming (EHF) process as a near-net shape automotive panel manufacturing technology that simultaneously reduces the energy embedded in vehicles and the energy consumed while producing automotive structures. Pulsed pressure is created via a shockwave generated by the discharge of high voltage capacitors through a pair of electrodes in a liquid-filled chamber. The shockwave in the liquid initiated by the expansion of the plasma channel formed between two electrodes propagates towards the blank and causes the blank to be deformed into a one-sided die cavity. The numerical model of the EHF process was validated experimentally and was successfully applied to the design of the electrode system and to a multi-electrode EHF chamber for full scale validation of the process. The numerical model was able to predict stresses in the dies during pulsed forming and was validated by the experimental study of the die insert failure mode for corner filling operations. The electrohydraulic forming process and its major subsystems, including durable electrodes, an EHF chamber, a water/air management system, a pulse generator and integrated process controls, were validated to be capable to operate in a fully automated, computer controlled mode for forming of a portion of a full-scale sheet metal component in laboratory conditions. Additionally, the novel processes of electrohydraulic trimming and electrohydraulic calibration were demonstrated at a reduced-scale component level. Furthermore, a hybrid process combining conventional stamping with EHF was demonstrated as a laboratory process for a full-scale automotive panel formed out of AHSS material. The economic feasibility of the developed EHF processes was defined by developing a cost model of the EHF process in comparison to the conventional stamping process.

  18. [Present state and future of flat panel detector in Japan].

    Science.gov (United States)

    Higashida, Yoshiharu

    2002-01-01

    In our country, the introduction of flat panel detector is carried out in the diagnosis region since before several years. In flat panel detector with the high image characteristic, large expectation is being placed. In this paper, image characteristic of flat panel detector and effectiveness of clinical application were reviewed. It is anticipated that flat panel detector with the excellent image characteristic gives large effect in the radiological diagnosis.

  19. Streamlining CubeSat Solar Panel Fabrication Processes

    OpenAIRE

    Sandberg, Ariel; Smith, Timothy

    2016-01-01

    A critical facet of CubeSat fabrication is solar panel characterization and assembly. Though capable of producing flight quality solar subsystems, traditional methods of solar panel fabrication contain intrinsic inefficiencies and inconsistencies that compromise the subsystem’s overall reliability. Taking Michigan Exploration Laboratory’s (MXL) heritage solar panel procedures as a case study, this investigation sought to streamline the solar panel fabrication process to increase its yield, co...

  20. 78 FR 4878 - Arts and Artifacts Indemnity Panel Advisory Committee

    Science.gov (United States)

    2013-01-23

    ... From the Federal Register Online via the Government Publishing Office NATIONAL FOUNDATION ON THE ARTS AND THE HUMANITIES Arts and Artifacts Indemnity Panel Advisory Committee AGENCY: Federal Council... Artifacts Domestic Indemnity Panel. The purpose of the meeting is for panel review, discussion,...

  1. Sound transmission performance on cavity ferrocement panels with ties

    Institute of Scientific and Technical Information of China (English)

    Kandaswamy S; Ramachandraiah A

    2003-01-01

    Ferrocement panels have been used in low cost housing construction in developingcountries. This study focuses on the sound transmission performance of cavity ferrocement pan-els with ties. In this study, panels have been cast and tested in transmission loss suite speciallydesigned and constructed for testing their sound transmission performance experimentally. Themeasured results agree well with the theoretical model.

  2. 77 FR 58413 - Aerospace Safety Advisory Panel; Meeting

    Science.gov (United States)

    2012-09-20

    ... SPACE ADMINISTRATION Aerospace Safety Advisory Panel; Meeting AGENCY: National Aeronautics and Space... meeting of the Aerospace Safety Advisory Panel. DATES: Friday, October 12, 2012, 12:00 p.m. to 1:00 p.m.... FOR FURTHER INFORMATION CONTACT: Ms. Harmony Myers, Aerospace Safety Advisory Panel Executive...

  3. 76 FR 2923 - Aerospace Safety Advisory Panel; Meeting

    Science.gov (United States)

    2011-01-18

    ... SPACE ADMINISTRATION Aerospace Safety Advisory Panel; Meeting AGENCY: National Aeronautics and Space... meeting of the Aerospace Safety Advisory Panel. DATES: Friday, February 4, 2011, 11:30 a.m. to 1:30 p.m... CONTACT: Ms. Kathy Dakon, Aerospace Safety Advisory Panel Executive Director, National Aeronautics...

  4. 76 FR 36937 - Aerospace Safety Advisory Panel; Meeting

    Science.gov (United States)

    2011-06-23

    ... SPACE ADMINISTRATION Aerospace Safety Advisory Panel; Meeting AGENCY: National Aeronautics and Space... meeting of the Aerospace Safety Advisory Panel. DATES: Friday, July 15, 2011, 10 a.m. to 12 p.m. ADDRESSES... INFORMATION CONTACT: Ms. Kathy Dakon, Aerospace Safety Advisory Panel Executive Director, National...

  5. 75 FR 61219 - Aerospace Safety Advisory Panel; Meeting

    Science.gov (United States)

    2010-10-04

    ... SPACE ADMINISTRATION Aerospace Safety Advisory Panel; Meeting AGENCY: National Aeronautics and Space... meeting of the Aerospace Safety Advisory Panel. DATES: Friday, October 22, 2010, 12:30 p.m. to 2 p.m... 77058. FOR FURTHER INFORMATION CONTACT: Ms. Kathy Dakon, Aerospace Safety Advisory Panel...

  6. 78 FR 56941 - Aerospace Safety Advisory Panel; Meeting

    Science.gov (United States)

    2013-09-16

    ... SPACE ADMINISTRATION Aerospace Safety Advisory Panel; Meeting AGENCY: National Aeronautics and Space... meeting of the Aerospace Safety Advisory Panel. DATES: Friday, October 11, 2013, 10:00 a.m. to 11:00 a.m.... FOR FURTHER INFORMATION CONTACT: Ms. Harmony Myers, Aerospace Safety Advisory Panel Executive...

  7. 75 FR 36697 - Aerospace Safety Advisory Panel; Meeting

    Science.gov (United States)

    2010-06-28

    ... SPACE ADMINISTRATION Aerospace Safety Advisory Panel; Meeting AGENCY: National Aeronautics and Space... meeting of the Aerospace Safety Advisory Panel. DATES: Friday, July 16, 2010, 1 p.m. to 3 p.m. ADDRESSES... CONTACT: Ms. Kathy Dakon, Aerospace Safety Advisory Panel Executive Director, National Aeronautics...

  8. 78 FR 36793 - Aerospace Safety Advisory Panel; Meeting

    Science.gov (United States)

    2013-06-19

    ... SPACE ADMINISTRATION Aerospace Safety Advisory Panel; Meeting AGENCY: National Aeronautics and Space... meeting of the Aerospace Safety Advisory Panel (ASAP). DATES: Friday, July 12, 2013, 09:00-10:00 a.m.... Harmony Myers, Aerospace Safety Advisory Panel Executive Director, National Aeronautics and...

  9. 76 FR 19147 - Aerospace Safety Advisory Panel; Meeting.

    Science.gov (United States)

    2011-04-06

    ... SPACE ADMINISTRATION Aerospace Safety Advisory Panel; Meeting. AGENCY: National Aeronautics and Space... meeting of the Aerospace Safety Advisory Panel. DATES: Friday, April 29, 2011, from 11 p.m. to 1 p.m..., FL 32899. FOR FURTHER INFORMATION CONTACT: Ms. Kathy Dakon, Aerospace Safety Advisory Panel...

  10. 78 FR 1265 - Aerospace Safety Advisory Panel; Meeting

    Science.gov (United States)

    2013-01-08

    ... SPACE ADMINISTRATION Aerospace Safety Advisory Panel; Meeting AGENCY: National Aeronautics and Space... meeting of the Aerospace Safety Advisory Panel. ] DATES: Friday, January 25, 2013, 10:00 a.m. to 11:00 a.m... CONTACT: Ms. Harmony Myers, Aerospace Safety Advisory Panel Executive Director, National Aeronautics...

  11. 77 FR 38090 - Aerospace Safety Advisory Panel; Meeting.

    Science.gov (United States)

    2012-06-26

    ... SPACE ADMINISTRATION Aerospace Safety Advisory Panel; Meeting. AGENCY: National Aeronautics and Space... meeting of the Aerospace Safety Advisory Panel. DATES: Friday, July 20, 2012, 11:30 a.m. to 12:30 p.m. EDT... FURTHER INFORMATION CONTACT: Ms. Harmony Myers, Aerospace Safety Advisory Panel Executive...

  12. 76 FR 65750 - Aerospace Safety Advisory Panel; Charter Renewal

    Science.gov (United States)

    2011-10-24

    ... SPACE ADMINISTRATION Aerospace Safety Advisory Panel; Charter Renewal AGENCY: National Aeronautics and... Aerospace Safety Advisory Panel. SUMMARY: Pursuant to sections 14(b)(1) and 9(c) of the Federal Advisory... of the NASA Aerospace Safety Advisory Panel is in the public interest in connection with...

  13. 32 CFR 724.104 - NDRB Traveling Panel.

    Science.gov (United States)

    2010-07-01

    ... 32 National Defense 5 2010-07-01 2010-07-01 false NDRB Traveling Panel. 724.104 Section 724.104 National Defense Department of Defense (Continued) DEPARTMENT OF THE NAVY PERSONNEL NAVAL DISCHARGE REVIEW BOARD Definitions § 724.104 NDRB Traveling Panel. An NDRB Panel that travels for the purpose...

  14. 76 FR 41075 - Copyright Arbitration Royalty Panel Rules and Procedures

    Science.gov (United States)

    2011-07-13

    ... Copyright Office 37 CFR Part 251 Copyright Arbitration Royalty Panel Rules and Procedures AGENCY: Copyright... making an amendment to its regulations by removing Part 251 Copyright Arbitration Royalty Panel Rules of Procedure. In 2004, Congress replaced the Copyright Arbitration Royalty Panels with three Copyright...

  15. 76 FR 69799 - Open meeting of the Taxpayer Advocacy Panel

    Science.gov (United States)

    2011-11-09

    ... Internal Revenue Service Open meeting of the Taxpayer Advocacy Panel AGENCY: Internal Revenue Service (IRS) Treasury. ACTION: Notice of meeting. SUMMARY: An open meeting of the Taxpayer Advocacy Panel will be conducted. The Taxpayer Advocacy Panel is soliciting public comments, ideas, and suggestions on...

  16. 76 FR 12418 - Recruitment Notice for the Taxpayer Advocacy Panel

    Science.gov (United States)

    2011-03-07

    ... Internal Revenue Service Recruitment Notice for the Taxpayer Advocacy Panel AGENCY: Internal Revenue... Advocacy Panel (TAP) Members. DATES: March 14, 2011 through April 29, 2011. FOR FURTHER INFORMATION CONTACT... nation's tax agency by applying to be members of the Taxpayer Advocacy Panel (TAP). The mission of...

  17. 77 FR 16895 - Taxpayer Advocacy Panel Meeting Cancellation

    Science.gov (United States)

    2012-03-22

    ... Internal Revenue Service Taxpayer Advocacy Panel Meeting Cancellation AGENCY: Internal Revenue Service (IRS... the open meeting of the Taxpayer Advocacy Panel Taxpayer Burden Reduction Project Committee scheduled... cancelled pending renewal of the Taxpayer Advocacy Panel Charter. FOR FURTHER INFORMATION CONTACT: Audrey...

  18. 75 FR 68403 - Open meeting of the Taxpayer Advocacy Panel

    Science.gov (United States)

    2010-11-05

    ... Internal Revenue Service Open meeting of the Taxpayer Advocacy Panel AGENCY: Internal Revenue Service (IRS) Treasury. ACTION: Notice of meeting. SUMMARY: An open meeting of the Taxpayer Advocacy Panel will be conducted. The Taxpayer Advocacy Panel is soliciting public comment, ideas, and suggestions on...

  19. 76 FR 75951 - Taxpayer Advocacy Panel Meeting Cancellation

    Science.gov (United States)

    2011-12-05

    ... Internal Revenue Service Taxpayer Advocacy Panel Meeting Cancellation AGENCY: Internal Revenue Service (IRS... the open meeting of the Taxpayer Advocacy Panel scheduled for Tuesday, December 6, 2011, and Wednesday.... ] Dated: November 30, 2011. Shawn Collins, Director, Taxpayer Advocacy Panel. BILLING CODE 4830-01-P...

  20. 32 CFR 724.122 - Recorder, NDRB Panel.

    Science.gov (United States)

    2010-07-01

    ... 32 National Defense 5 2010-07-01 2010-07-01 false Recorder, NDRB Panel. 724.122 Section 724.122 National Defense Department of Defense (Continued) DEPARTMENT OF THE NAVY PERSONNEL NAVAL DISCHARGE REVIEW BOARD Definitions § 724.122 Recorder, NDRB Panel. A panel member responsible for briefing an...