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匹配顺轨和逆轨拦截模式的估计方法是精确计算剩余飞行时间(TGO)的必要条件,适用于逆轨拦截模式的TGO估计方法并不适于顺轨拦截模式。为此,针对顺轨拦截模式,分别提出了拦截机动/非机动目标的TGO估计方法。通过对线性制导方程的变形求解出了拦截弹的飞行弧长,并根据预测的碰撞点位置求得了TGO估计的解析式。该求解方法通用性强,适用于弹道成型制导律的TGO估计。以负比例(RPN)和扩展RPN(ARPN)为制导框架,与经典方法进行对比,所提出的TGO估计方法精确度高,能够有效提高导弹的制导性能。
The method of estimating the matched and the orbital tracking modes is a necessary condition for accurately calculating the remaining flight time (TGO). The TGO estimation method applied to the orbital tracking mode is not suitable for the interceptor mode. Therefore, for the intercept mode, the TGO estimation methods for intercepting maneuvering / non-maneuvering targets are respectively proposed. The flight arc length of the interceptor was solved by the deformation of the linear guidance equation and the analytic formula of the TGO was obtained according to the predicted collision location. The solving method is versatile and suitable for TGO estimation of ballistic guidance law. Compared with the classical method, the RPO and the extended RPN (ARPN) are the guidance framework, the proposed TGO estimation method has high accuracy and can effectively improve the guidance performance of the missile.