亚轨道高动态飞行器拦截弹道模式研究  

Research on Interceptor Trajectory for High Dynamic Suborbital Vehicle

作　　者：余卓阳 谢放 许伟 田博 郭昊 Yu Zhuo-yang;Xie Fang;Xu Wei;Tian Bo;Guo Hao(Science and Technology on Space Physics Laboratory,Beijing,100076)

机构地区：[1]空间物理重点实验室

出　　处：《导弹与航天运载技术》2019年第5期12-16,22,共6页Missiles and Space Vehicles

摘　　要：由于亚轨道高动态飞行器一般在大气层边缘作高速飞行,现有的防空导弹难以对其进行拦截,因此针对亚轨道高动态飞行器拦截弹道模式进行研究。建立了拦截弹运动学和动力学模型,在此基础上利用参数优化方法和最优控制理论分别对传统视距拦截作战模式和超视距拦截作战模式下的拦截弹道进行了优化设计,得到了两种作战模式下拦截弹最优弹道。研究结果表明:超视距拦截作战模式能够充分发挥拦截弹能量优势,扩展拦截弹的射程。High dynamic suborbital vehicle flight at the edge of the atmosphere in high speed, and the air defense missile is difficult to intercept it, so the interceptor trajectory for high dynamic suborbital vehicle is studied in this issue. First, the kinematics and dynamics model of interceptor is established, then the optimal trajectory for traditional in the horizon combat mode and over the horizon combat mode is designed by the method of parameter optimization and optimal control. Simulation results illustrate over the horizon combat mode can maximum the advantage of the energy of interceptor. The over the horizon combat mode can also extend the range of interceptor and improve the effect of interceptor.

关 键 词：亚轨道飞行器 弹道模式 超视距拦截 参数优化 最优控制 

分 类 号：V412.1[航空宇航科学与技术—航空宇航推进理论与工程]