摘要
高超声速飞行器再入段需要反作用控制系统(RCS)维持姿态稳定。设计一种固定推力器开启数的再分配伪逆控制分配方法,并应用在了高超声速飞行器再入段姿态控制中。首先,建立高超声速飞行器再入段RCS姿态模型,采用有限时间终端滑模算法设计姿态跟踪控制器。针对给定8推力器配置的RCS,设计固定3推力器开启的再分配伪逆法对RCS进行控制分配,能提高系统实时性并且降低燃料消耗。最后将设计的控制分配系统应用于高超声速飞行器再入姿态仿真,仿真结果表明设计的方法具有很好的控制效果,在保证控制性能和实时性的同时能够降低燃料消耗。
The attitude control system of the hypersonic vehicle(HV)reentry phase required the compound control of the pneumatic rudders and reaction control system(RCS).An improved redistribution pseudo-inverse control allocation method with a constant opening number of thrusters was designed and applied to the attitude control of hypersonic vehicle reentry stage.Firstly,the hypersonic vehicle RCS attitude model of the reentry section was established.The finite-time terminal sliding mode control method was employed for HV attitude tracking control of the reentry phase.For the given RCS configuration with 8 thrusters,an improved redistribution pseudo-inverse method with 3 thrusters turned on was proposed,which could significantly improve the real-time performance and reduce fuel consumption.Finally,the designed control allocation system was applied to the hypersonic vehicle reentry attitude simulation.The simulation results indicated that the proposed control allocation method had satisfactory performance.
作者
宋佳
张严雪
SONG Jia;ZHANG Yanxue(School of Astronautics, Beihang University, Beijing 100191, China)
出处
《郑州大学学报（理学版）》
CAS
北大核心
2021年第2期19-25,共7页
Journal of Zhengzhou University:Natural Science Edition
基金
国家自然科学基金项目(61473015,91646108)
国家H863项目(11100002017115004,111GFTQ2018115005,111GFTQ2019115006)。
关键词
高超声速飞行器
反作用控制系统
终端滑模控制
改进的再分配伪逆法
控制分配
hypersonic vehicle
reaction control system(RCS)
terminal sliding mode control
improved redistribution pseudo-inverse method
control allocation
