| 摘要: | 輕型運動類飛機除了可提供個人休閒運動使用之外，並可做為中短距離之交通工具，因此在各國通用
航空位市場均已快速的成長。美國雖已於2004 年通過相關的法規，但對於輕型航空器的適墜性設計卻
未有明確的規範。本研究主要使用有限元素法來探討輕型運動類飛機機身結構在墜落時之速度與角度
對於乘客安全性的影響。本文依據NASA AGATE 、ASTM 與FAR 所定義之掉落速度為參數，以
MIL-STD-1290A 為安全邊界條件。本研究結果顯示，若飛機在不同速度撞擊地面時，以角度30° 可能
產生最大座艙壓縮量。當掉落角度增加時，由於機身前端的引擎固定架與防火牆的結構設計，所以可
承受之垂直掉落速度越大。當機身衝擊角度為80°-90°時，機身結構可吸收衝擊速度之上限約為33
m/s。本文也完成了模擬該類型飛機在不同垂直掉落速度與不同衝擊角度下之安全與可存活的範圍。
In recent years, light sport aircraft which served not only for the purpose of personal recreation but also
means of transportation vehicle for medium and short distance travel has made a rapid growth in the general
aviation industry worldwide. FAA has established the regulations for this new category airplane in 2004.
However, the crashworthiness requirements for this type of airplane have not been clearly specified. This
study used finite element method to investigate the effect of impact angle and speed of the light sport aircraft
(LSA) fuselage structure on passenger safety during a crash event. This work used sink speed defined by
NASA AGATE, ASTM and FAR as parameters. The passenger compartment reducing rate defined by
MIL-STD-1290A is used for a safety boundary condition. The results show the maximum cockpit reducing
rate of the airplane impact angle is 30°. When the impact angle increases, owe to the engine mount and fire
wall's reinforced structure, it can sustain the greater vertical drop speed. When the impact angle is about
80°~90°, the maximum impact speed the fuselage can sustain is 33 mls. This work also completed the
simulation of the safe and unsafe range for light sport aircraft at various impact angle and vertical drop speed
during impact. |
