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分别针对顺轨与逆轨拦截飞行轨迹的特点,设计了相应的剩余飞行时间(TGO)估计方法。该方法通过对弹目碰撞点的预测,降低了发射条件差异对TGO估计精度的影响。首先对线性比例导引运动方程进行变形,得到拦截弹飞行轨迹关于弹目距离的一阶微分方程,基于预测碰撞点,对不同初始发射角造成的积分结果误差进行修正,得出了2种拦截模式下的TGO解析表达式。通过与3种现有估计方法对比分析,验证了提出方法的实时性和估计精度,且能够优化制导性能。
The corresponding residual flight time (TGO) estimation methods are designed respectively for the characteristics of the orbital and interceptor trajectories. The method predicts the collision point of projectiles to reduce the influence of different emission conditions on the accuracy of TGO estimation. Firstly, the linear proportional governing equations are transformed to obtain the first-order differential equation of the trajectory of the interceptor in relation to the projectile distance. Based on the predicted collision point, the error of the integral result caused by different initial launch angles is corrected, and two interceptions are obtained TGO parsing expression in mode. By comparing with the three existing estimation methods, the real-time performance and the estimation accuracy of the proposed method are verified, and the guidance performance can be optimized.