Dynamic modeling and control of large flexiblespacecraft combination

Zhou, Zijian; Wang, Xinglong; Guang-ji, QU

doi:10.1360/sspma2018-00104

Cited by 2 publications

(1 citation statement)

References 2 publications

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“…6 The periodic attitude disturbances of the satellite body emerged after the launch of FY-3A due to the coupling vibration of the solar panels. 7 Moreover, the motion forms of the space structure are also complex and diverse when they are in large scales, such as large maneuvering, [8][9][10] space movement of large manipulator, [11][12][13] rendezvous and docking, [14][15][16] and large-scale appendage deployment and locking. [17][18][19] For example, the flexible vibration of the solar panels poses a strong coupling effect on the attitude of the spacecraft body and the joint motion of the robotic arm for large or substantially large spacecraft platforms with enormous flexible solar panels, such as GEO communication satellites.…”

Section: Introductionmentioning

confidence: 99%

Recursive dynamic modeling for attitude control of fully flexible spacecraft with central body and appendages

Wang,

Wang

2024

Advances in Mechanical Engineering

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A spacecraft composed of a central body and flexible appendages is a typical rigid-flexible coupling system. Current modeling methods generally regard the central body as rigid. As the central body becomes larger and more flexible, the elastic deformation of the central body may not be ignored. In this study, considering the flexibility effect of the central body and based on the recursive kinematics, a complete coupled dynamic model of the orbit, attitude, and elastic deformation of a fully flexible spacecraft is established. Compared with traditional methods, the model has smaller generalized coordinate dimension and can more clearly reveal the kinematic relationship between the appendages and the central body. By comparing the simulation results of typical working conditions with the ADAMS software, the correctness of the built model is verified. The PD controller for the attitude of the spacecraft is used, and three models of different rigid/flexible settings are compared in detail. The dynamic response of the system in uncontrolled and controlled states are discussed. Numerical simulation results show that the flexibility of the central body poses a certain influence on the attitude response of the spacecraft, the flexible vibration of the appendages, and the attitude control accuracy.

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