基于大气预估的再入飞行器机动减速制导方法  

Maneuvering-Deceleration Guidance Algorithm Based on Atmosphere Estimation for Reentry Vehicle

作　　者：李强[1] 夏群利[1] 何镜[2] 温求遒[1] 

机构地区：[1]北京理工大学宇航学院,北京100081 [2]中国兵器科学研究院,北京100089

出　　处：《兵工学报》2013年第9期1091-1096,共6页Acta Armamentarii

摘　　要：针对高超声速再入飞行器精确制导与减速控制一体化的需求,提出一种基于大气预估的再入飞行器机动减速制导方法。基于终端位置及落角约束推导得到制导指令闭合解,在此基础上针对终端速度约束,提出在制导上附加机动减速指令的机动减速制导形式。机动减速制导指令由制导指令和机动减速指令叠加生成,制导指令由包含终端位置及角度约束的最优制导律计算确定;机动减速采用对位置影响最小的正弦指令形式,通过数值预测终端速度偏差确定指令参数大小,并引入参数辨识技术实现预测模型大气偏差修正,提高终端速度预测精度。通过仿真验证了该方法能够在偏差条件下,保证制导精度并有效控制终端飞行速度,实现精确制导与减速控制的一体化设计。A new maneuvering-deceleration guidance algorithm based on atmosphere estimation is presen- ted for the precise guidance and velocity control of hypersonic reentry vehicle. The maneuvering-decelera- tion guidance command is composed of optimal guidance command and deceleration command. The opti- mal guidance command is obtained by guidance law with position and impact angle constraints. Sinusoid maneuvering-deceleration command is used to minimize the position disturbance caused by deceleration. And the parameters of maneuvering command are produced from mismatch between terminal predicted ve- locity and nominal-velocity by numerical integration method. The atmosphere parameter identification technology is also used to improve the prediction precision. The simulation results show that the maneuve- ring-deceleration guidance algorithm has strong robustness against uncertain conditions; it can accomplish the integrated design of precise guidance and deceleration control efficiently.

关 键 词：飞行器控制 导航技术 再入飞行器 机动目标 精确制导 减速控制 大气预估 

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]