As a key technology for orbital applications, researches on spacecraft formation flying(SFF) attract more attention. However, most of existing researches about dynamics and control of SFF focus on rigid spacecrafts wi...As a key technology for orbital applications, researches on spacecraft formation flying(SFF) attract more attention. However, most of existing researches about dynamics and control of SFF focus on rigid spacecrafts without considering the effect of flexible attachments(such as flexible panels). In this paper, relative attitude dynamics and active control of SFF for a flexible spacecraft(follower spacecraft) and a rigid spacecraft(target spacecraft) are investigated. Firstly, a dynamic model of the flexible spacecraft is established by the principle of angular momentum. Then, the equation of relative attitude dynamics between the flexible spacecraft and the rigid spacecraft is derived by the quaternion to represent the attitude relation of the two spacecrafts. Finally,an attitude feedback controller is designed for the SFF system, and its stability is proved by the Lyapunov stability theory. Simulation results indicate that the panel flexibility has an obvious influence on the dynamic behaviour of the system, the designed controller can effectively control the attitude of the two spacecrafts to achieve synchronization, and the elastic vibration of the panels may be suppressed simultaneously.展开更多
基金the National Natural Science Foundation of China(Nos.11772187 and 11802174)the China Postdoctoral Science Foundation(No.2018M632104)the Research Project of Shanghai Institute of Technical Physics of the Chinese Academy of Science(No.CASIR201702)
文摘As a key technology for orbital applications, researches on spacecraft formation flying(SFF) attract more attention. However, most of existing researches about dynamics and control of SFF focus on rigid spacecrafts without considering the effect of flexible attachments(such as flexible panels). In this paper, relative attitude dynamics and active control of SFF for a flexible spacecraft(follower spacecraft) and a rigid spacecraft(target spacecraft) are investigated. Firstly, a dynamic model of the flexible spacecraft is established by the principle of angular momentum. Then, the equation of relative attitude dynamics between the flexible spacecraft and the rigid spacecraft is derived by the quaternion to represent the attitude relation of the two spacecrafts. Finally,an attitude feedback controller is designed for the SFF system, and its stability is proved by the Lyapunov stability theory. Simulation results indicate that the panel flexibility has an obvious influence on the dynamic behaviour of the system, the designed controller can effectively control the attitude of the two spacecrafts to achieve synchronization, and the elastic vibration of the panels may be suppressed simultaneously.
