摘要
考虑拦截器使用固体推进系统的情况,设计了基于零控脱靶量(ZEM)的大气层外超远程拦截制导方法。首先设计了考虑摄动影响的适用于超远程拦截的零控脱靶量计算方法;其次使用变分法结合Kepler轨道摄动方程推导了线性的ZEM动力学方程;最后考虑固体推进拦截器的可控性约束条件设计了ZEM控制律并结合动力学方程确定指令推力方向。本文给出的制导方法设计过程中没有对拦截器和目标的引力差进行简化,考虑了摄动因素对滑行段弹道的影响,制导精度对推进系统参数偏差的鲁棒性好。仿真结果表明使用本文制导方法拦截大气层外超远程目标,脱靶量可达公里量级,推进系统参数偏差对制导精度的影响很小。
A guidance law based on zero effort miss （ZEM） for super-range exoatmospheric intercept is proposed for the case when the interceptor uses a solid rocket motor. A ZEM calculating approach for super-range intercept under the influence of perturbation is presented first, and then the linear dynamic equation of ZEM is obtained using the variational method and the perturbation equation of Kepler orbit. Finally, taking into consideration the trust controllability condition of the interceptor with a solid motor, the control law of ZEM is designed to determine the command trust orientation. The gravity difference during the coast phase between the target and the interceptor is not simplified, and the perturbation is also considered in the presented guidance law, making it robust to motor parameter uncertainties. Simulation results demonstrate that when using the presented guidance law for super-range exoatmospheric intercept the order of ZEM magnitude is kilometer, and the guidance precision is robust to motor parameter uncertainties
出处
《航空学报》
EI
CAS
CSCD
北大核心
2009年第9期1583-1589,共7页
Acta Aeronautica et Astronautica Sinica
关键词
超远程拦截
零控脱靶量
固体推进系统
鲁棒性
Kepler轨道摄动方程
弹道预测
super-range intercept
zero effort miss
solid propellant system
robustness
perturbation equation of Kepler orbit
trajectory prediction
