提高再入点精度的末助推级制导方法

A Guidance Method of the Last Booster to Improve the Precision at the Reentry Point

本文将需要速度运用于导弹助推级以提高导弹的再入点精度,为再入机动及末制导提供较好的初始条件。文中还考虑到为调整推力方向进行姿态控制的工程可实现性。

This paper applies required velocity to the missile's last booster toimprove its precision at the reentry point, and to provide the better initialconditions for the reentry maneuver and the terminal guidance. The engineeringrealizability of attitude control to adjust thrust direction is also taken intoaccount in it.