基于预测脱靶量的远程拦截速度增益导引  

Velocity-to-be-gained Guidance Based on Predicted Miss Distance for Long-range Intercept

作　　者：陈峰[1] 王育林[2] 肖业伦[1] 陈万春[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191 [2]中国飞行试验研究院,陕西西安710089

出　　处：《航空学报》2008年第6期1665-1672,共8页Acta Aeronautica et Astronautica Sinica

摘　　要：针对拦截器使用耗尽关机固体燃料发动机的情况,设计了大气层外目标拦截的速度增益导引方法。导引律中根据Lambert导引确定指令推力方向初值,利用剩余速度增量信息,计算惯性速度增益下的预测脱靶量,使用Kepler轨道摄动方程计算消除脱靶量所需的速度增益修正,根据惯性速度增益和速度增益修正之和确定指令推力方向。给出了一种计及J2项引力摄动影响的滑行段弹道预测半解析方法,减少导引律运算量,降低导引方法误差;导引律中引入了剩余速度增量测量环节,增强了导引精度对推进系统参数的鲁棒性。与传统的通用能量管理(GEM)导引相比,采用该导引律拦截远程目标时指令推力方向平稳、变化范围小,脱靶量降低了两个数量级。A velocity-to-be-gained guidance law for exoatmospheric targets is proposed for an interceptor with a fuel-exhaustion-shutoff solid rocket motor. First,the assumption is made that the interceptor has attained the inertial velocity-to-be-gained,and the predicted miss distance is obtained by using the parameter of remaining velocity increment. Then the correction of the velocity-to-be-gained is attained by using the perturbation matrix of the Kepler orbit,and the predicted miss distance could be eliminated by it. Finally,the command thrust orientation is determined by the sum of the inertial velocity-to-be-gained and its correction. The initial command thrust orientation is determined by Lambert guidance. A semi-analytical trajectory-predicting method which takes into consideration the impact of J2 item perturbation is presented to decrease the amount of calculation and reduce errors. A measurement method for the remaining velocity increment is proposed to improve the robustness of guidance against motor parameter uncertainties. Simulation results demonstrate that when using the proposed guidance law,the command thrust orientation varies more evenly in a narrower range,and the miss distance is about two orders of magnitude lower as compared with conventional general energy management （GEM） guidance.

关 键 词：预测脱靶量 Lambert拦截 速度增益导引 剩余速度增量 惯性速度增益 J2项摄动 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]