The Crashworthiness Analysis of Composite Light Aircraft

• Main Authors: Ya-Yun Lin, 林亜昀
• Other Authors: Pu-Woei Chen
• Format: Others
• Language: zh-TW
• Published: 2015
• Online Access: http://ndltd.ncl.edu.tw/handle/30818692011388836709

碩士 === 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.