摘要
通过实弹打击试验和数值模拟等方法,研究了飞机遭高速离散杆条打击后形成切槽形损伤的机理,重点讨论了杆条尺寸、速度对飞机结构损伤的影响,建立了相关的计算公式,分析了模拟与打击结果产生误差的原因,可为飞机战伤预测、战伤评估、抢修预案制定及飞机战斗生存力设计提供依据。研究结果表明:只要杆条有足够的撞击速度,且偏航角大于0°,靶板就会形成长条形穿透损伤,即切槽形损伤;由于杆条在侵彻过程中存在着扩孔过程,故靶板上的切槽形损伤宽度大于杆条直径;当靶板不垂直于地面摆放,杆条以垂直于地面且偏航角为90°的姿态水平侵彻靶板时,所形成的切槽形损伤的长度大于杆条长度。在此条件下,适当减小靶板仰角,切槽形损伤长度可增加。
With the methods of real warhead explosion experiment and numeric simulation etc, the mechanism of trough damage in the airplane by discrete rod is discussed. The effect of the rod＇s size, velocity on airplane structure damage is discussed. The correlative computing formula is established to forecast airplane structure battle damage. The reason that causes the error between numeric simulation and real experiment is analyzed. The research result is useful to airplane battle damage forecast, evaluation, establishing ABDR prefab plan and survivability design. The results show that as long as the rod has enough speed and the yaw is bigger than 0？？, the long penetration damage （ trough damage） will be formed on the flat. Because of the damage expanding in the rod penetrating process, the damage width is bigger than the diameter of the rod. When the flat isnt put on the ground vertically, the rod＇s velocity is vertical to the ground and the yaw is 90？, the trough damage size is longer than the length of the rod. In this condition, an appropriate decrease of flat＇s yaw can cause the increase of the trough damage.
出处
《空军工程大学学报（自然科学版）》
CSCD
北大核心
2008年第4期15-19,共5页
Journal of Air Force Engineering University(Natural Science Edition)
基金
国防预研基金资助项目(51327010101)
关键词
切槽形损伤
离散杆
飞机
trough damage
discrete rod
airplane
