摘要
针对即插即用无线小卫星模块间通信资源约束以及航天器惯量信息难以精确获得下的姿态跟踪控制问题,提出了一种基于事件驱动的航天器姿态自适应跟踪算法。该算法在跟踪控制过程中,通过自适应控制律对转动惯量矩阵进行估计,同时引入事件驱动控制策略,只在驱动条件满足时对控制器进行更新,能有效改善模块间通信频率。然后根据Lyapunov方法证明了闭环控制系统的渐近有界稳定性,并证明了该事件驱动控制无Zeno行为。最后,数值仿真结果验证该控制算法的有效性。
An adaptive control law based on an event-triggered control strategy is proposed to solve the problem of attitude tracking control under the constraints of communication resources between plug-and-play wireless small satellite modules and the difficulty of obtaining the accurate inertia information of spacecraft.In the process of tracking control,the moment of inertia matrix is estimated by adaptive control law in this algorithm,and event driven control strategy is introduced.Under the event-triggered control scheme,the controller is updated only when the triggered conditions are fully set,which can effectively optimize the communication frequency among modules.Then,based on Lyapunov method,the asymptotic boundedness stability of the closed-loop control system is proven that there is a positive lower bound among adjacent triggered instants to ensure that Zeno behavior will not occur.Finally,the numerical simulation results verify the effectiveness of the control algorithm.
作者
林子杰
陆国平
吕旺
吴宝林
Lin Zijie;Lu Guoping;Lv Wang;Wu Baolin(Shanghai Institute of Satellite Engineering,Shanghai 201109,China;Dept.Control Engineering,Harbin Institute of Technology,Harbin 150001,China)
出处
《航天控制》
CSCD
北大核心
2021年第1期32-39,共8页
Aerospace Control
基金
国家自然科学基金(61503093,91438202)。
关键词
航天器姿态控制
事件驱动控制
自适应控制
通讯受限
模型不确定
Spacecraft attitude tracking
Event-triggered control
Adaptive control
Limited communication to actuator
Uncertainty
