弹道导弹中段机动突防制导误差修正方法

Guidance error correction method of ballistic missile midcourse maneuvering penetration

针对弹道导弹中段反拦截实时机动突防带来的参数偏差问题,给出了在地球非球形摄动影响下的位置和速度偏差量的计算方法,采用改进的fg级数和预测制导方法获得了机动推力的作用方向及发动机的开启时间,并对再入点误差进行了修正。仿真结果表明,采用该方法可有效地修正因机动突防与地球扁率而引起的再入点参数误差,为末制导系统的工作提供了良好的再入条件。

Aiming to the parameters bias produced by ballistic missiles counter-interception maneuvering penetration,a calculating method of position and velocity bias affected by earth non-sphere perturbation is presented.The maneuvering thrust direction and the unlock time of engine are obtained by adopting improved fg series and prediction guidance.And then,the reentry point error is modified.Simulation results show that the proposed method can effectively modify the parameters error of reentry point because of the maneuvering penetration and earth＇s flattening,and it can also provide favorable reentry condition for terminal guidance systems.