一种针对采用冲压发动机的远程空空导弹末段制导算法研究  

Research on Terminal Guidance Algorithm for Ramjet-powered Airborne Missiles

作　　者：段磊[1] 

机构地区：[1]中国空空导弹研究院,洛阳471009

出　　处：《科学技术与工程》2012年第27期7013-7018,共6页Science Technology and Engineering

摘　　要：针对采用冲压发动机的远程BTT空空导弹末段制导算法进行研究。在导弹非线性俯仰-偏航-滚转三通道模型基础上,通过数值解算两点边界值方法,研究非线性模型的弹体加速度控制指令和滚转角速率控制指令的最优算法。采用多时间尺度技术解决了BTT导弹弹体在滚转变化过快时的近优控制指令。系统仿真结果表明,在小噪声干扰情况下,导弹可直接命中目标,制导算法具有一定的应用价值。The terminal guidance design problem for a long-range bank-to-turn（BTT） ramjet missile involves a completely pitch – yaw – roll nonlinear dynamics model.Because of these nonlinear dynamics,an optimal solution for acceleration and roll-rate commands can be found only by numerical methods for solving two-point boundary value problems.Because the roll-rate dynamics of the missiles is much faster than the rest of the system states,a near-optimal solution is obtained to the BTT guidance problem using multiple timescale techniques.Simulation results are presented for a representative terminal guidance using this algorithm.Near-zero miss distances are obtained in a noise-free environment.

关 键 词：BTT导弹 制导算法 两点边界问题 多时间尺度 系统仿真 

分 类 号：V448.233[航空宇航科学与技术—飞行器设计]