大着地角卫星制导炸弹最优制导律研究

Optimal Guidance Law of Satellite Guided Bombs with Large Landing Angle

为满足卫星制导炸弹大着地角的弹道要求,进行了最优制导律研究。根据卫星制导炸弹的特点,建立了弹目运动状态方程。分别基于极小值原理和通过求解黎卡提方程得到最优制导律,结果一致。对该最优制导律简化后获得了次最优制导律,适用于工程和仿真计算。利用次最优制导律进行了卫星制导炸弹六自由度全弹道仿真,与使用比例导引律的计算结果相比,着地角增加了60%。该制导律可以显著提高着地角和打击精度,能够满足卫星制导炸弹的弹道要求。

An optimal guidance law is researched to meet the trajectory requirements of large landing angle for satellite guided bombs.Based on the characteristics of satellite guided bombs,the missile-target motion state equations are established.The optimal guidance law is designed by using minimum principle and solving Riccati equation respectively and the results are accordant.The optimal guidance law is simplified and the suboptimal guidance law is given to adapt to engineering and simulation.Whole ballistic simulations of six degree-of-freedom are made by using the suboptimal guidance law and compared with the simulation results of general proportional navigation guidance law.The landing angle of the proposed method increases 60 percent.This guidance law can improve landing angle and hit precision significantly and meet the trajectory requirements of satellite guided bombs.