为消除卫星制导高度误差的影响,从而提高命中精度,卫星制导炸弹最优制导律必须满足大弹着角约束条件。文中在分析航空制导炸弹信息获取的基础上,提出并建立了卫星制导虚拟导引头数学模型;基于该虚拟导引头,研究了带有弹着角约束的最优制导律,并进行了六自由度全弹道仿真。仿真结果证明,该制导律响应速度快,弹着角性能提高约60%,具有较好的制导精度,同时制导参数设置简单,易于工程实现。

To minimize the influence of altitude error caused by satellites guidance for improving hit precision, the optimal guidance law of satellites guidance bomb must meet the constraint conditions for impact angle. In this paper, based on the analysis of information acquisition for guide air bomb, the mathematic model of vitual seeker was proposed and built. Based on this virtual seeker, the optimal guidance law constrained with impact angle was studied. The 6-DOF trajectory simulation proved that the guidance law responds quickly, improves 60% capability for the impact angle, and provides preferable guidance precision. What is more, it features easy guidance parameter setting engineering realication.