摘要
针对大气层内拦截弹直接力/气动力复合控制系统设计问题,首先根据直接力机构特性建立了复合控制系统动力学模型;其次,给出了一种控制器结构,并应用LQR最优控制理论求解出导弹自动驾驶仪的增益矩阵,按ITAE准则用遗传算法对其进行计算寻优;最后,在Matlab环境下进行仿真;仿真结果表明,与传统的LQR结果对比,该方法设计的自动驾驶仪跟踪具有速度快、稳态误差小并有一定的鲁棒性等优点,验证了该控制器的有效性。
As for the endo--atmospheric interceptor which uses dual aero/propulsive control, the dynamic model is established. And al- so, a controller is proposed and the autopilot gain matrix values are obtained according to optimal control, the parameters are selected by opti- mizing a cost/unction using genetic algorithm. Simulation is done in Matlab and the results show that the proposed scheme can track the ma- neuver command with high precision and fast response speed compared with the traditional one. It is applicable to design the autopilot for dual aero/propulsive missile.
出处
《计算机测量与控制》
北大核心
2014年第4期1157-1159,1162,共4页
Computer Measurement &Control
基金
航空科学基金项目(20120112001)
