Добірка наукової літератури з теми "Aircraft crashworthiness"
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Статті в журналах з теми "Aircraft crashworthiness"
Peng, Liang, Xiao Peng Wan, and Mei Ying Zhao. "Improved Fuselage Design for Crashworthiness." Applied Mechanics and Materials 246-247 (December 2012): 777–81. http://dx.doi.org/10.4028/www.scientific.net/amm.246-247.777.
Повний текст джерелаRen, Y., and J. Xiang. "Energy absorption structures design of civil aircraft to improve crashworthiness." Aeronautical Journal 118, no. 1202 (April 2014): 383–98. http://dx.doi.org/10.1017/s0001924000009180.
Повний текст джерелаYu, Ze Liang, and Pu Xue. "Crashworthiness Study of Composite Fuselage Section." Key Engineering Materials 725 (December 2016): 94–98. http://dx.doi.org/10.4028/www.scientific.net/kem.725.94.
Повний текст джерелаSchwinn, Dominik B. "Integration of Crashworthiness Aspects into Preliminary Aircraft Design." Applied Mechanics and Materials 598 (July 2014): 146–50. http://dx.doi.org/10.4028/www.scientific.net/amm.598.146.
Повний текст джерелаJusuf, Annisa, Afdhal Afdhal, and Minda Mora. "Kajian Desain Kelaiktabrakan Pesawat Terbang." WARTA ARDHIA 42, no. 3 (September 22, 2017): 117. http://dx.doi.org/10.25104/wa.v42i3.241.117-122.
Повний текст джерелаWang, Yu Fei, Ban Wang, Jin Yuan Wang, and Dong Qi Meng. "Optimization of Biomechanical Systems For the Fighter Plane Ejection Seats." Advanced Materials Research 815 (October 2013): 880–85. http://dx.doi.org/10.4028/www.scientific.net/amr.815.880.
Повний текст джерелаChen, Pu-Woei, and Yung-Yun Chen. "Optimization Analysis on the Crashworthiness of Light Aircrafts." International Journal of Manufacturing, Materials, and Mechanical Engineering 5, no. 3 (July 2015): 1–23. http://dx.doi.org/10.4018/ijmmme.2015070101.
Повний текст джерелаXue, P., L. Ding, F. Qiao, and X. Yu. "Crashworthiness study of a civil aircraft fuselage section." Latin American Journal of Solids and Structures 11, no. 9 (2014): 1615–27. http://dx.doi.org/10.1590/s1679-78252014000900007.
Повний текст джерелаRen, Yiru, and Jinwu Xiang. "Improvement of aircraft crashworthy performance using inversion failure strut system." Aircraft Engineering and Aerospace Technology 89, no. 2 (March 6, 2017): 330–37. http://dx.doi.org/10.1108/aeat-09-2015-0205.
Повний текст джерелаChen, Pu Woei, Shu Han Chang, Yu Yang Hsieh, and Tai Sing Sun. "Crashworthiness Simulation Analysis of Light Sport Aircraft Fuselage Structure." Advanced Materials Research 199-200 (February 2011): 48–53. http://dx.doi.org/10.4028/www.scientific.net/amr.199-200.48.
Повний текст джерелаДисертації з теми "Aircraft crashworthiness"
Stephens, V. M. "Crashworthiness of composite seats for civil aircraft." Thesis, Cranfield University, 1992. http://hdl.handle.net/1826/1771.
Повний текст джерелаCarvalho, Roberta Godinho de. "Aircraft crashworthiness: proposal of accident investigation checklist." Instituto Tecnológico de Aeronáutica, 2003. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=549.
Повний текст джерелаSatterwhite, Matthew Ryan. "Development and Validation of Fluid-Structure Interaction in Aircraft Crashworthiness Studies." Thesis, Virginia Tech, 2013. http://hdl.handle.net/10919/51559.
Повний текст джерелаMaster of Science
Abdullah, Ahmad Sufian. "Crash simulation of fibre metal laminate fuselage." Thesis, University of Manchester, 2014. https://www.research.manchester.ac.uk/portal/en/theses/crash-simulation-of-fibre-metal-laminate-fuselage(fd254489-243f-4071-8dea-ca9e2dd9d3bc).html.
Повний текст джерелаHuang, Yu-Jen, and 黃毓仁. "Crashworthiness Analysis of Light Aircraft Seat." Thesis, 2011. http://ndltd.ncl.edu.tw/handle/94068401244168315527.
Повний текст джерела淡江大學
航空太空工程學系碩士班
99
As for the pursuit of flight speed and efficient time, the flight safety remains a concern. During the flight, the passenger restraint system comes from two parts: 1. seat belts; 2. seat. Structural strength of the seats is the main system to protect all the passengers and the crew. In order to improve the survival rate of the crew and passengers when the plane crash, the seats must withstand a certain degree of impact. Therefore, FAA developed a standard of the flight seat to ensure the passengers’ safety. The main purpose of this paper is to discuss the use of the finite element software to create an aviation simulation platform for crashworthiness of the seats of light aircraft. As the seat of light aircraft is not clearly defined, static and dynamic analyses are in accordance with the safety regulations of FAR 23. 3D seating model was established by using the Pro / ENGINEER. Also, by using finite element software ABAQUS grid, setting the boundary and load conditions, and conducting the operations and analysis to obtain components of air seats to be set, strain distribution and the amount of deformation. According to the static simulation results, the 3003-H16 aluminum alloy air seats meet regulation of FAR 23.561 as below: forward 9G, lateral 1.5G, 3G up and down the norms 6G test. As for the dynamic simulation, after the two tests from FAR 23.562 which states: 1. Pitch angle of 30 degrees under speed 31fps down fall. 2. Deflection angle of 10 degrees under speed 42fps forward impacts will have damage. Under the yield stress, the maximum speed to withstand destruction is downward 7.3fps, forward 6.7fps.
Lin, Ya-Yun, and 林亜昀. "The Crashworthiness Analysis of Composite Light Aircraft." Thesis, 2015. http://ndltd.ncl.edu.tw/handle/30818692011388836709.
Повний текст джерела淡江大學
航空太空工程學系碩士班
103
People pay more attention to aircraft because of the growth of aviation industry. In the past few years, metal materials be replaced by composite materials because of the advantages of composite materials. The flight accidents cannot be avoided, so it is an important issue to discuss the crashworthiness of composite aircraft. In this study we use finite element software, such as Abaqus to discuss the crashworthiness and the safety crash zone of the cockpit by using metal and composite materials. We used Pro/ENGINEER to build STOL CH 701 model and the materials used is aluminum, carbon fiber composite material, glass fiber composites and polymer fiber composites. The boundary conditions are 1.3 followed by ASTM, and 30o impact angle defined by AGATE. The result of dynamic simulation must conform 15% cockpit reducing rate which is define by MIL-STD-1290A. In this study the safety crash zone of the cockpit by CFRP and GFRP are higher than 38.56% and 32.12% that of aluminum alloy. The safety crash zone of KFRP is slightly lower than 4.74% that of aluminum alloy. The safety crash zone of the cockpit either change the angle or change the speed, A inclined beams are the key structural. In four different kinds of materials, the deformation of CFRP impact only the Y direction slightly higher than the deformation of aluminum alloy, and the X direction and A direction are lower than the deformation of any other materials. Also the whole safety crash zone of the cockpit by CFRP is better than the whole safety crash zone of the cockpit by other materials.
Hsieh, Yu-Yang, and 謝育揚. "Crashworthiness Analysis of Light Sport Aircraft Structure." Thesis, 2010. http://ndltd.ncl.edu.tw/handle/23497003636126114477.
Повний текст джерела淡江大學
航空太空工程學系碩士班
98
Science and technology are processing with era. The controllability performance on the aircraft is much better than before, but it still hard to avoid human error or mechanical breakdown, etc. This research of crashworthiness is one of an important issue of how can we approve the percentage of survival in the accident. This research takes the aviation accidents in Taiwan as an example of light-sport aircraft; explain the importance of crashworthiness of aircraft. Recently, most research of crashworthiness are mainly discuss about large civil aircraft, barley discuss about small civil aircraft. Because of the market demand on the small civil aircraft increase in the future, the demand of security must improve. This research regards STOL CH701 structural of airframes as samples, using software of finite element─HyperMesh and LS-DYNA to simulate and analysis the structure on dynamic test, to build the relationship between flying speed, impact angle and structural strength. This research is proving that reliability of the simulate dynamic test based on the AGATE report data that shows the possibility velocity and angle that passenger may survive in the accident, and the stalling speed which follows ASTM standard then analyzing, respectively. Further more, we use different angle to run the simulation test, and built the relationship between velocity, angle and the cockpit reducing rate of the light sport aircraft. Besides we set up the cockpit reducing rate as 15%, to find out the safety zone between the velocity and angle.
Chen, Kuan-Jung, and 陳冠融. "The Crashworthiness Analysis of Composite and Metal Light Aircraft." Thesis, 2012. http://ndltd.ncl.edu.tw/handle/35372375595305159037.
Повний текст джерела淡江大學
航空太空工程學系碩士班
100
In recent years, the advantages of composite materials make that the composite materials take the place of the metal materials for aerospace industry. Because the flight accidents cannot be avoided completely, so it’s an important issue to investigate crashworthiness of composite aircraft structure under the tendency of composite aircraft. In recent years, the mostly researching objects of composite aircraft crashworthiness are the large aircrafts. To face of the composite light aircraft market will increased, that also means that crashworthiness of the composite light aircraft also emphasize its importance. In this study we use Pro/ENGINEER to establish STOL CH 701 model, the metal material is Al 6061-T6, and composite material is Std CF Fabric Composite. The boundary conditions are 1.3 landing velocity followed by ASTM F2245-07 4.4.4.1, and 30degree impact angle defined by AGATE. The result of dynamic simulation must be under the 15% cockpit reducing rate defined by MIL-STD-1290A. The process of dynamic simulation is meshing model by finite element software Hypermesh, then output the simulation data by LS-DYNA. The result of this study was informed that the safety impact speed of metal material cockpit is 9.59 m/s while crashed for 30 degree impact angle, but composite cockpit can afford the speed greater than defined by ASTM. The safety impact angle of metal cockpit is 16.56 degree, composite cockpit is 84.9 degree. By the relation of impact speed and impact angle to cockpit reducing rate, the safety crash zone of composite cockpit is 160% higher than metal cockpit. Above these results, light aircraft has the batter crashworthiness to replace metal material by composite material.
Chen, Yung-Yun, and 程永耘. "Crashworthiness Analysis of Light Sport Aircraft Structure by Topology Optimization." Thesis, 2014. http://ndltd.ncl.edu.tw/handle/90301046566146226701.
Повний текст джерела淡江大學
航空太空工程學系碩士班
102
In recent years, the general aviation develop to flourish, and also get more attention on security of general aviation. The general aviation which use single piston engine such as light aircraft and light sport aircraft, its high fatal rate also point out the structure needed to be improve. Improving security dependant on the crashworthiness of the aircraft, and the way to improve is strengthen structure and change material. This study use Abaqus, the finite element software and topology optimization to achieve the goals of enhance structure strength. Boundary conditions of dynamic simulation are impact angle defined by AGATE and landing speed followed by ASTM. Build safety zone base on 15% safe reducing rate by MIL-STD-1290A. The result of this study is that optimum model compare with original model, the safety zone of cant beam increase 12%, the safety zone along x direction increase 13%, and the total safety zone increase 10%. The above results show that the crashworthiness of optimum model is better than original model.
Hsi-WenLai and 賴璽文. "Dynamic Impact Damage Response and Crashworthiness Analysis of Ultra-Light Aircraft Structures." Thesis, 2010. http://ndltd.ncl.edu.tw/handle/62061529879194854988.
Повний текст джерела國立成功大學
航空太空工程學系碩博士班
98
The purpose of this study is based on analyzing dynamic impact response and crashworthiness of ultra-light aircraft which is composed of hollow thin-walled tube subjected to impact. The design of structure crashworthiness concept usually appears in several of vehicle structure such as car, bumper, train, and aircraft. Besides, most and previous theses also focus on vehicle structure that possesses the resisted ability and absorb sufficient energy during the impact process. When the thin-walled tube is subjected to axial impact, the transformation mode could be predicted by studying dynamic impact response, force, energy absorption and stroke of the tube. On theoretical analysis view, use analytic solution to obtain mean force, stroke, duration time, energy and the collapse number. The good agreement is presented and reported for the experimental data and simulated result in our study. In addition, the explicit commercial code – LS-DYNA is utilized to solve and simulate the dynamic impact response of the hollow circular tube and the ultra-light aircraft accident. The comparison is examined for experimental result of tube and suffers injury of the accident case. By changing the impact velocity and the tube thicknesses, energy adsorptions, maximum acceleration of pilot and passenger for the Ultra-light aircraft full-scale model with deferent thicknesses of tube are represented in our simulations. The Human Tolerance Limits is adopted to describe the significant damage objective between thin-walled tube thicknesses and crush spinal damage for human.
Книги з теми "Aircraft crashworthiness"
Segal, Antony M. Aircraft (full-size glider) crashworthiness impact test. [S.l.]: [S.n.], 1989.
Знайти повний текст джерелаPoon, C. A review of crashworthiness of composite aircraft structures. Ottawa: National Aeronautical Establishment, 1990.
Знайти повний текст джерелаFinn, Ed. Cushion the impact: Canadian research leads to advances in understanding aircraft crashworthiness. [S.l.]: [s.n.], 1988.
Знайти повний текст джерелаNorth Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Energy absroption of aircraft structures as an aspect of crashworthiness. Neuilly sur Seine, France: AGARD, 1988.
Знайти повний текст джерелаGeneral Aviation Aircraft Meeting and Exposition (1987 Wichita, Kan.). General aviation aircraft crash dynamics. Warrendale, PA: Society of Automotive Engineers, 1987.
Знайти повний текст джерелаHuculak, P. A review of research and development in crashworthiness of general aviation aircraft: seats, restraints and floor structures. Ottawa: National Aeronautical Establishment, 1990.
Знайти повний текст джерелаNorth Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Energy absorption of aircraft structures as an aspect of crashworthiness. Neuilly sur Seine, France: AGARD, 1989.
Знайти повний текст джерелаCarden, Huey D. Effect of crash pulse shape on seat stroke requirements for limiting loads on occupants of aircraft. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.
Знайти повний текст джерелаGeneral Aviation Aircraft Meeting and Exposition (1985 Wichita, Kan.). Crash dynamics of general aviation aircraft. Warrendale, PA: Society of Automotive Engineers, 1985.
Знайти повний текст джерелаUnited States. National Transportation Safety Board. Safety study: Crashworthiness of large poststandard schoolbuses. Washington, D.C: The Board, 1987.
Знайти повний текст джерелаЧастини книг з теми "Aircraft crashworthiness"
Kindervater, C. M. "Aircraft and Helicopter Crashworthiness: Design and Simulation." In Crashworthiness of Transportation Systems: Structural Impact and Occupant Protection, 525–77. Dordrecht: Springer Netherlands, 1997. http://dx.doi.org/10.1007/978-94-011-5796-4_20.
Повний текст джерелаLankarani, H. M. "Current Issues Regarding Aircraft Crash Injury Protection." In Crashworthiness of Transportation Systems: Structural Impact and Occupant Protection, 579–612. Dordrecht: Springer Netherlands, 1997. http://dx.doi.org/10.1007/978-94-011-5796-4_21.
Повний текст джерелаBaghel, Puneet, Sanjay Kumar Tak, Rajshree Swami, Zenab Kagzi, and Manisha Prajapat. "The Crashworthiness Performance of Thin-Walled Energy Absorbing Devices: An Overview." In SCRS Proceedings of International Conference of Undergraduate Students, 263–70. 2023rd ed. Soft Computing Research Society, 2023. http://dx.doi.org/10.52458/978-81-95502-01-1-29.
Повний текст джерелаТези доповідей конференцій з теми "Aircraft crashworthiness"
Madayag, A. F., and John W. Olcott. "Criteria for General Aviation Fuel Systems Crashworthiness." In General Aviation Aircraft Meeting and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1989. http://dx.doi.org/10.4271/891016.
Повний текст джерелаMarcus, Jeffrey H. "Dummy and Injury Criteria for Aircraft Crashworthiness." In General, Corporate & Regional Aviation Meeting & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1995. http://dx.doi.org/10.4271/951167.
Повний текст джерелаArnaudeau, F., M. Mahe´, E. Deletombe, and F. Le Page. "Crashworthiness of Aircraft Composites Structures (Invited Talk)." In ASME 2002 International Mechanical Engineering Congress and Exposition. ASMEDC, 2002. http://dx.doi.org/10.1115/imece2002-32917.
Повний текст джерелаDing, Menglong, Anhuan Xie, Shiqiang Zhu, Wei Song, Jiandong Cai, Xufei Yan, Pengyu Zhao, Jason Gu, and Yanyan Zhang. "Crashworthiness Design Optimization for an eVTOL Aircraft." In 2022 IEEE International Conference on Robotics and Biomimetics (ROBIO). IEEE, 2022. http://dx.doi.org/10.1109/robio55434.2022.10011735.
Повний текст джерелаWang, Xing-Yu, Shu-Hua Zhu, and Xu-Long Xi. "Research on crashworthiness of a civil transport aircraft." In 2022 8th International Conference on Mechanical Engineering and Automation Science (ICMEAS). IEEE, 2022. http://dx.doi.org/10.1109/icmeas57305.2022.00060.
Повний текст джерелаZhao, H., W. Lu, D. Wang, P. Ke, Z. Qu, and Y. Hou. "Civil helicopter crashworthiness safety and CRFS application." In CSAA/IET International Conference on Aircraft Utility Systems (AUS 2022). Institution of Engineering and Technology, 2022. http://dx.doi.org/10.1049/icp.2022.1576.
Повний текст джерелаMaia, Leandro Guimarães, and Paulo Henriques Iscold Andrade De Oliveira. "A Review of Finite Element Simulation of Aircraft Crashworthiness." In SAE Brasil 2005 Congress and Exhibit. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2005. http://dx.doi.org/10.4271/2005-01-4012.
Повний текст джерелаClark, John C. "Summary Report on the National Transportation Safety Board's General Aviation Crashworthiness Project Findings." In General Aviation Aircraft Meeting and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1987. http://dx.doi.org/10.4271/871006.
Повний текст джерелаBeheshti, Hamid Kh, Hamid M. Lankarani, and Sivaraman Gopalan. "A Hybrid Multibody Model for Aircraft Occupant/Seat Cushion Crashworthiness Investigation." In ASME 2005 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2005. http://dx.doi.org/10.1115/detc2005-84041.
Повний текст джерелаPaz Mendez, Javier, Jacobo Díaz García, and Luis Romera Rodríguez. "Crashworthiness Analysis and Enhancement of Aircraft Structures under Vertical Impact Scenarios." In AIAA Scitech 2019 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-0778.
Повний текст джерелаЗвіти організацій з теми "Aircraft crashworthiness"
Schoenbeck, Ann, and Michael Schultz. Emerging Technologies in Aircraft Crashworthiness. Fort Belvoir, VA: Defense Technical Information Center, May 1999. http://dx.doi.org/10.21236/ada375738.
Повний текст джерелаShannon, Samuel G., and Dennis F. Shanahan. Estimating the Impact of Crashworthiness Standards on Mortality and Morbidity Events in the U.S. Army Rotary-Wing Aircraft Mishaps. Fort Belvoir, VA: Defense Technical Information Center, September 1993. http://dx.doi.org/10.21236/ada277121.
Повний текст джерела