Chinese Journal of Theoretical and Applied Mechanics ›› 2019, Vol. 51 ›› Issue (1): 1-13.DOI: 10.6052/0459-1879-18-054

• Research Review •     Next Articles


Cao Dengqing2,)*(), Bai Kunchao, Ding Hu**, Zhou Xubin††, Pan Zhongwen***, Chen Liqun†††, Zhan Shige   

  1. *School of Astronautics, Harbin Institute of Technology, Harbin 150001, China
    Department of Mathematics and Physics, National Natural Science Foundation of China, Beijing 100085, China
    **Shanghai Institute of Applied Mathematics and Mechanics, Shanghai University, Shanghai 200072, China
    ††Shanghai Institute of Satellite Engineering, Shanghai 201109, China
    ***Beijing Institute of Space System Engineering, Beijing 100076, China
    †††School of Science, Harbin Institute of Technology, Shenzhen 518055, Guangdong, China
  • Online:2019-01-18 Published:2019-03-01
  • Contact: Dengqing Cao,Kunchao Bai,Hu Ding,Xubin Zhou,Zhongwen Pan,Liqun Chen,Shige Zhan


With the gradual implementation of the major projects in aerospace engineering, the spacecraft design is heading towards the direction of ultra-high speed, large scale and multi-function, and its launching and operating environment is likely to worsen. The problems on vibration and active and/or passive control in spacecraft launching process, dynamic modeling and response analysis of large flexible spacecraft in orbit, and the hybrid control of structural vibration and attitude maneuver of the spacecraft are getting more and more complicated and difficult to deal with. The enlarged scale and increased flexibility of the spacecraft structure (suchas the large aperture antenna and solar panels) present a challenge to the ground test and semi-physical simulation. The dynamics and control problems involved in the large-scale flexible spacecraft such as the whole-spacecraft vibration isolation in the spacecraft lunching process, the dynamic modeling and vibration response analysis of large-scale flexible structures, and the coupling dynamics and hybrid control of structural vibration and attitude and or orbital maneuver of the large-scale flexible spacecraft are presented. The key scientific issues seriously in the fields of spacecraft dynamics and control could then be extracted as follows: the dynamic modeling and order reduction of multi-rigid flexible body systems (including the dynamic modeling of the flexible structure with large deformation, the collaborate simulations with multi-solvers, model reductions, the analytical approach for the dynamic modeling of composite structures, etc.), the construction of state space model of complicated structures and its controllability investigation (including the theoretical and experiment methods of the state space model formulation, the observability and controllability of the control system for complex structures, etc.), and the design of hybrid control law of structural vibration and attitude maneuver for the large-scale flexible spacecraft (concerning the robust hybrid control of attitude maneuver and structural vibration, the collaborative control of actuating mechanism and piezoelectric actuator, etc.

Key words: large-scale flexible spacecraft|space structures|nonlinear dynamics|vibration control|attitude and orbital maneuvering|multi-body system dynamics

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