摘要
惯性系统误差系数修正是提高弹道导弹制导精度的有效方法。通过分析惯导误差系数修正方法,提出惯性制导系统的自由段实时补偿技术,通过公式推导,建立了误差系数补偿的理论模型。运用弹道仿真计算,分析误差造成的落点偏差,验证了修正模型对导弹落点偏差的补偿作用,证明该补偿方法不需要硬件改动,仅对弹上制导软件进行小量改动就能够显著提高导弹命中精度。
It is a valid method for improving the guidance precision of ballistic missile to correct the inertial system error. By analyzing the correction method of the used inertial guidance error coefficient, the free-field segment compensation technique of the inertial system is put forward and the compensation model is built. The point-falling deviation of ballistic missile is analyzed by simulation calculation and it is proved that the hitting precision of ballistic missile is higher by using the method.
出处
《导弹与航天运载技术》
北大核心
2009年第6期8-10,共3页
Missiles and Space Vehicles
关键词
惯性系统
误差模型
误差补偿
弹道仿真
IMU error equation
Error model
Error compensation
Ballistic simulation
