某空空导弹发动机装药挂飞振动疲劳寿命分析  

Fatigue Life Analysis for a Solid Rocket Motor of Air-to-air Missile under Hanging Flight Vibration

作　　者：李记威 房雷[1] 周建军[1] 职世君[1] 韩波[1] 尹自宾[1] 

机构地区：[1]中国空空导弹研究院,河南洛阳471009

出　　处：《弹箭与制导学报》2016年第1期89-92,共4页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：国家自然科学基金(U1404106);中国空空导弹研究院科技创新基金(201304S04)资助

摘　　要：挂飞振动是空空导弹最重要环境因素之一,研究发动机挂飞疲劳寿命对掌握其环境使用边界具有重要意义。文中利用谐波叠加法模拟发动机所受时域随机振动载荷,结合有限元软件进行了挂飞振动动态模拟,获得了某型发动机应力变化规律。在此基础上,利用雨流计数法统计了该发动机装药危险位置应力循环信息,依据Miner疲劳累积损伤理论预估了该发动机装药挂飞振动疲劳寿命,最后对发动机装药挂飞寿命与推进剂疲劳极限关系进行了分析。One of the most important environmental factors is hanging flight vibration for air-to-air missile,it is significant to study fatigue life of hanging flight vibration for grasping environmental using limits. Harmony superposition method was applied to simulate load of time domain,and time-stress course of dynamic simulation was acquired by using finite element software. On the basis of this simulation,the rain-flow method was applied to the stress circles for statistics,and the fatigue life of SRM was evaluated by applying Miner＇s cumulative damage theory. Finally,the relation between fatigue life of SRM and endurance limit of propellant was analyzed.

关 键 词：空空导弹 固体火箭发动机 挂飞振动 疲劳寿命预估 有限元分析 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]