基于扩张状态观测器的小型固体火箭控制系统设计与验证  

Extended state observer based small solid rocket control system design and validation

作　　者：李彤[1] 张士峰[1] 杨华波[1] 张银辉[1] 

机构地区：[1]国防科技大学航天科学与工程学院,长沙410073

出　　处：《固体火箭技术》2014年第6期749-755,共7页Journal of Solid Rocket Technology

基　　金：国防科学技术大学研究生创新资助项目(S140104)

摘　　要：以自研小型固体火箭为对象,基于扩张状态观测器,对三通道姿态控制器进行了设计及验证。建立了以攻角、侧滑角和滚转角为控制目标的积分链状态空间模型;结合扩张状态观测器,应用极点配置法对三通道姿态控制器进行了鲁棒设计;通过数值仿真和半实物仿真,结合拉偏分析,对控制器设计进行校核,证明了设计的有效性和鲁棒性;通过飞行试验验证了控制器性能,跟踪结果符合仿真分析,基本无延时、无静差,证明了该方法的可行性和工程应用价值。The design and validation for the three-channel attitude controller of a self-developed small solid rocket based on the extended state observer approach were presented.The integral-chain state space model was established for the control design of the angle of attack,angle of sideslip and roll angle;Combined with the extended state observer,the pole placement was applied to the ro-bust design of the three-channel attitude controller;Through numerical and hardware-in-the-loop simulation with uncertainties con-sidered,the effectiveness and robustness of the controller were illustrated and verified.The performance of the controller was valida-ted by flight-test with results of nearly no time delay or state error conforming to the simulation,which illustrates the feasibility and the engineering application value.

关 键 词：小型固体火箭 姿态控制器 扩张状态观测器 半实物仿真 飞行试验 

分 类 号：V448[航空宇航科学与技术—飞行器设计]