大气层内动能拦截弹脉冲矢量发动机点火控制算法研究

基于脉冲矢量发动机的工作特点，提出了在飞行末端分段设计跟踪过程控制力的方法，其中过渡段利用最优控制以使所消耗的发动机数量最小，并引入神经网络以保证工作的实时性。在飞行初段，提出用直接力来对弹道进行调姿以减小中制导段需用过载的方案，并利用最优控制的方法设计了直接力作用方案。点火控制算法基于极坐标的形式，该法可充分利用脉冲矢量发动机，且可灵活控制直接力的指向。仿真表明，所提方法可以最小的代价跟踪上外界输入，具有较高的工程应用价值。

Investigation of Ignition Control Algorithm of the Pulse Vector Motors of the Endoatmospheric Kinetic Interceptor

Based on the working characteristic of the pulse vector motors, the design methods of control force of the different phase of the tracking process during the end guidance phase are proposed, whose transition phase use optimal control to minimize the motors, and introduce the neural net to assure the real-time. During the initial flight phase, the method which regulates the ballistic trajectory to reduce the overload requirement of the flight middle phase using the direct force is presented. Ignition control algorithm is based on the polar coordinates, which can take full advantage of the motors, and regulate the direction of the direct force. The last simulation shows that the methods which presented in the paper make the attitude control system track the input, and have high engineering application values.