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本文介绍一种关于导弹弹道中段和末段的混合制导规律,以提高导弹的射程及其优良的拦截特性。文中导出了中段和末段三维飞行的闭环非线性最优制导规律的解析解。这种混合制导规律在中制导段目标方向发生变化时能迅速修正导弹的弹道。在从中段转到末段时,航向误差可以达到零。这种制导的算法取反馈形式,既可用于惯性坐标系,又可用于寻的坐标系。此算法在弹上实现起来相当简单,已经成功地用于在线工作。
This article introduces a hybrid guidance law for the middle and last stages of the missile trajectory to improve the missile’s range and its excellent interception characteristics. In this paper, the analytical solutions of the closed-loop nonlinear optimal guidance law in the middle and last three-dimensional flight are derived. This hybrid guidance law can quickly correct the ballistic trajectory of a missile when the target direction of the guided section changes. When going from the middle section to the final section, the heading error can reach zero. This guidance algorithm takes the form of feedback, which can be used both for inertial and for finding the coordinate system. This algorithm is fairly simple to implement on the fly and has been used successfully for online work.