基于临近空间防空导弹的气动力控制系统仿真

对基于临近空间防空导弹的气动力控制系统进行了研究和设计。给出了导弹的气动力控制系统数学模型的推导、建立过程,并利用状态反馈配置极点的方法,对导弹的控制系统进行了设计。在MATLAB/Simulink平台上,对具体实例进行了仿真计算,给出了导弹与目标的飞行仿真轨迹,以及导弹俯仰和偏航两个通道的过载变化图。通过对仿真结果的分析,指出了所设计的气动力控制系统在飞行于临近空间、气动舵输出过载大小有限的情况下,也能够使得导弹准确拦截目标。

Simulation of Pneumatic Control System Based on Air Defense Missile of Near Space

The core contents and procedures of the simulation of pneumatic control system base on one air defense missile of near space are presented.Firstly,it shows that the procedures of the derivation and foundation of the mathematic model of the pneumatic control system of a missile.The 6 DOF mathematic model is presented in section 1.In section 2,the control system of the missile is designed by using the method of state feedback in pole placement.And the feedback matrix k can be solved via the state equation that is presented.The simulation results are given in Figs.2,3,4,5 and 6 in section 3.The analysis shows that missile can hit the air target precisely via the pneumatic control system designed in this article,though the missile is flying in the area of near space and the overload output of the pneumatic rudders is limited.