计及重力补偿的卫星制导炮弹最优制导律设计

Design of Optimal Guidance Law for Satellite Guidance Shell With Compensation of Gravity

针对卫星制导炮弹体积小、弹载计算机计算能力有限的特点,提出并建立了一种简易的计及重力补偿的最优制导律,给出了卫星制导炮弹制导信息获取的数学方法,对比例制导律、弹着角约束最优制导律、计及重力的比例制导律和计及重力弹着角约束最优制导律,进行了六自由度弹道对比仿真分析。仿真结果表明,本文提出的计及重力补偿的制导律具有结构简单、需用法向过载小且突变量较低等特点,易于在弹道调控能力不足的制导炮弹上实现。

Based on the characteristics of the small volume of the satellite guidance shell and limited computational capability of the missile-borne computer, a simple optimal guidance considering the gravity compensation was proposed. The mathematical method of acquiring guidance information was provided. The proportion guidance law, optimal guidance law of 1 impact angle,proportion guidance law considering the gravity and optimal guidance law of 1 impact angle considering the gravity were compared. The 6-DOF trajectory simulation proves the mut inad the law arge arge that proposed guidance law is simple in structure, and Brauch normal overload is small, and the ation value is small. The law can be realized easily in the satellite guidance shell with equate ballistic control ability