导弹协同作战飞行时间裕度

 基于导弹协同作战任务规划系统进行合理任务分配的需求，研究了导弹可以修正控制飞行时间的裕度。根据导弹-目标在视线坐标系和角动量坐标系下的运动关系，得出了导弹相对于目标的加速度，并基于此给出了导弹剩余飞行时间的估算方法；当前时刻导弹剩余飞行时间的估算值与已经飞行的时间以及任务规划系统指定的期望到达时间构成时间反馈作用，用于修正控制导弹到达目标的最终飞行时间。由于真比例导引律在工程实现和解析运算中具有一定的优势，选择在真比例制导加速度的视线方向施加时间反馈控制作用，进而得出了基于真比例导引律的导弹协同作战飞行时间控制导引律；最后重点研究了在该时间控制导引律的作用下，存在导弹的飞行速度限制以及弹目相对运动约束时，导弹飞行过程中任一时刻对应解析形式的可控飞行时间的裕度。仿真结果表明，本文的设计合理可行，对于多弹协同作战的实现具有重要意义。

Flight Time Margin of Missile Cooperative Engagement

Considering the requirement of rational mission assignment for the missile planning system in cooperative engagement, the investigation on controllable flight time margin of missile is presented. Based on the missile-to-target kinematics and dynamics relations in line of sight and moved inertial coordinate frames, the missile-to-target acceleration is obtained, and then the method of estimating time-to-go is provided. The estimated time-to-go, wasted flight time and scheduled expected arrival time compose the feedback of time control, which can be used to control the final arrival time. Along with the advantage of true proportional guidance law in engineering implement and resolution, the true proportional guidance acceleration along the line of sight is added to the feedback action, and then the missile time-controlled guidance law is obtained. Finally, under the control of the time-controlled guidance law and considering the missile velocity restriction and missile-to-target relative kinematics, the margin of controllable time-to-go with resolved form at any time in the flight progress is analyzed in detail. Simulations demonstrate that the proposed designs are effective, and of much significance for the performance of missile cooperative engagement.