摘要
针对升力式再入飞行器再入过程中执行机构发生故障的情况,基于反步法思想,设计了一种无需飞行器转动惯量信息的姿态容错控制律,同时,该控制律能有效地抑制外界干扰。控制律的设计除了给出稳定性证明外,还给出了误差上界与控制参数的关系。以临近空间飞行器X-33为模型进行了数学仿真,结果表明了该控制律的有效性。
An inertia-free fault-tolerant attitude tracking law is proposed for a lifting reentry vehicle with the actuator faults. The proposed control law is based on the backstepping control. The effect on attitude control performance by the external disturbance is also suppressed by the proposed control law. The stability of the control law is ensured.Furthermore,the relationship between the upper bound of the tracking error and the design parameter is also given in this paper. To demonstrate the efficiency of the method,the simulation of X-33 vehicle in reentry mode is carried out.
作者
刘伟星
耿云海
吴宝林
LIU Wei-xing;GENG Yun-hai;WU Bao-lin(Research Center of Satellite Technology,Harbin Institute of Technology,Harbin 150080,China)
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2018年第6期683-689,共7页
Journal of Astronautics
基金
国家自然科学基金(61503093
91438202)
哈尔滨工业大学资助项目(AUGA5710053114)
微小型航天器技术国防重点学科实验室开放基金(HIT.KLOF.MST.201502)
关键词
再入飞行器
姿态跟踪
容错控制
反步法
Reentry vehicle
Attitude tracking
Fault-tolerant control
Baekstepping control
