为分析并修正发射点垂线偏差对导弹惯性制导精度的影响,建立了完整的惯性制导误差传递模型,通过基于标准弹道参数的误差仿真,得出不同射程、射向条件下垂线偏差引起的惯性制导误差特性,其中,视加速度投影误差是产生制导误差的主要因素,引力加速度计算误差和自瞄准误差的影响也不可忽略。利用该误差传递模型对垂线偏差影响进行计算和修正,可有效提高导弹惯性制导精度。

To analyze and correct the influence of launch point vertical deflection on missile inertial guidance precision, a complete errortransfer model of missile inertia guidance was established. Inertia guidance error characteristic of different range and direction was analyzed by error simulation based on standard trajectory parameter. Projection error of apparent acceleration is the main factor of guidance error, while the calculation error of gravitational acceleration and self-aiming error cannot be neglected either. Based on this error-transfer model, vertical deflection influence can be calculated and corrected, which has contributed to improve missile inertial guidance precision.