基于ESO的运载火箭姿控喷管故障辨识设计及实现  

Design and Implementation of Fault Identification for Attitude Control Nozzle of Launch Vehicle Based on ESO

作　　者：潘豪[1] 王光辉 邵梦晗 胡煜荣 罗宛臻 Pan Hao;Wang Guang-hui;Shao Meng-han;Hu Yu-rong;Luo Wan-zhen(Beijing Aerospace Automatic Control Institute,Beijing,100854)

机构地区：[1]北京航天自动控制研究所,北京100854

出　　处：《导弹与航天运载技术》2021年第1期72-75,共4页Missiles and Space Vehicles

基　　金：国防基础科研计划项目(JCKY2018203B022)。

摘　　要：针对基于喷管开关控制的运载火箭姿控系统故障,提出了一种基于控制效果的喷管故障辨识方法。在对特定喷管配置和轴对称运载火箭模型研究基础上,利用扩张状态观测器实时估计箭体所受的总力矩,进而根据估计结果进行故障判别和极性纠正。仿真结果表明,以ESO为观测器的故障辨识设计方法可有效判别出姿控喷管的极性故障,并能够通过策略设计进行极性纠正,具有较强的工程应用价值。In this paper,an adaptive reconfiguration control method is proposed based on control effect in order to solve the attitude control system fault of a launch vehicle based on nozzle control.On the basis of the study on the specific nozzle configuration and the model of conventional launch vehicle,an extended state observer is designed to estimate vehicle’s total moment.Furthermore,fault discrimination and adaptive reconfigurable design can be achieved as a result of the estimate above-mentioned.The mathematical simulation shows that the polarity fault can be judged effectively applying the above method.The method has strong engineering value as the polarity fault can be eliminated.

关 键 词：运载火箭 喷管控制 故障辨识 

分 类 号：V448.1[航空宇航科学与技术—飞行器设计]