新型级间分离方案设计与仿真  

Design and simulation of new stage separation scheme

作　　者：李慧通 赵阳[1] 黄意新[1] 王旭刚 

机构地区：[1]哈尔滨工业大学航天学院,哈尔滨150001 [2]北京宇航系统工程研究所,北京100076

出　　处：《固体火箭技术》2016年第4期580-587,共8页Journal of Solid Rocket Technology

摘　　要：设计了某新型导弹级间分离方案,结合级间冷分离和级间热分离的优点,采用固体燃气发生器和反推发动机作为分离能源,提出了合适的分离方式和分离时序。建立了分离过程的运动学和动力学模型,设计了碰撞检测模型,在分离仿真时考虑反推发动机推力偏差和下面级残余推力偏心和偏斜对分离的影响,还采用了蒙特卡洛方法分析了分离体运动范围,得到分离体在偏差干扰下运动情况,同时得到了分离危险时刻中心点相对横移范围,打靶仿真中没有出现碰撞现象,分离体的相对运动在分离要求范围内,说明该分离方案是安全可行的。A new stage separation scheme of missile was designed. The separation process combined the benefits of cool stage separation and thermal stage separation,and solid propellant gas generator and reverse thrust engines were used as separation energy.A proper separation method and separation time sequence were put forward. The dynamic and kinetic model and collision detection model were constructed.The impacts of many factors on separation were considered,including engine thrust deviation,eccentricity and deflection of spent stage residual thrust.The movement range of separation bodies was analyzed with Monte-Carlo method,and the relative lateral movement range of center point at separation danger moment was obtained. During simulation of target practice,no collision occurs and relative movement of separation bodies is in the demanding range,which verifies safety and feasibility of this new separation scheme.

关 键 词：级间分离 分离时序 动力学模型 碰撞检测模型 

分 类 号：V475.3[航空宇航科学与技术—飞行器设计]