基于LQR最优控制规律的巡航导弹控制器设计

Design of cruise missile controller based on LQR optimal control law

摘要:

：为缩短导弹飞行过程中的经历位移，达到精准巡航定位的目的，设计基于LQR最优控制规律的巡航导弹控制器。按照导弹动力电路的供应需求，连接PID控制元件、巡航执行器、纵向导弹弹射器及射程调节器，搭建巡航导弹控制器的主体结构单元。根据控制模块的初始化标准，实现控制系数的模糊化处理，再联合巡航规则库，统计LQR控制系数的实际优化效果，完成基于LQR最优控制规律的巡航建模控制器灵敏度分析，实现巡航导弹控制器的顺利应用。对比实验结果表明，与普通元件控制设备相比，应用课题所设计的新型控制器设备后，导弹飞行位移由93000Km降低至60000Km左右，UDA主导系数也超过1.0，能够解决导弹巡航定位精确性不达标的问题。

Abstract:

In order to shorten the displacement during missile flight and achieve the purpose of accurate cruise positioning, a cruise missile controller based on the optimal control law of LQR is designed. According to the supply demand of the missile power circuit, PID control elements, cruise actuators, longitudinal missile catapults and range regulators are connected to build the main structural unit of the cruise missile controller. According to the initialization standard of the control module, the fuzzy control of the control coefficients is realized, and then the cruise rule base is combined to calculate the actual optimization effect of the LQR control coefficients, complete the cruise model controller sensitivity analysis based on the LQR optimal control law, and realize cruise missile control Smooth application. The comparative experimental results show that compared with ordinary component control equipment, after applying the new controller equipment designed by the subject, the missile flight displacement is reduced from 93000Km to about 60,000Km, and the UDA dominance coefficient also exceeds 1.0, which can solve the missile cruise positioning accuracy not meeting the standards The problem.