主动段扰动引力对闭路制导的影响分析

Effects of gravity anomaly in boost phase on closed loop guidance

针对主动段扰动引力对采取惯性制导方式的远程火箭命中精度的影响问题,提出了主动段扰动引力对闭路制导的影响分析方法。结合闭路制导中的导航计算与关机方程,剖析主动段扰动引力造成落点偏差的机理,分析了扰动引力对待增速度的影响,提出了将关机点处待增速度偏差分为两个组成部分分别研究的分析方法。对出现推力、质量等偏差时的状态进行了仿真分析,得到关机点处待增速度偏差主要受关机点时间影响的结论。所得结论对提高远程火箭制导精度有借鉴意义。

For the problem of the hit precession of long-range rocket based on inertial guidance is influenced by the gravity anomaly in boost phase, a series of analytical methods are proposed to explain this process. Based on the navigation calculation and shutdown equation in closed loop guidance, the mecha- nism of the impact point deviation caused by the gravity anomaly is studied. The influence of the gravity anomaly on the required velocity increase is analyzed. And a method of dividing the required velocity in- crease at the shutdown point into two components is put forward. The simulation analysis of the state of thrust and mass deviation is made, and the conclusion is obtained that the required velocity increase at the shutdown time is mainly affected by the shutdown time. The conclusion can be used as a reference for improving the precision of long rocket guidance.