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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2017, Vol. 38 ›› Issue (6): 320778-320778.doi: 10.7527/S1000-6893.2016.0306

• Electronics and Electrical Engineering and Control • Previous Articles     Next Articles

Design of moving-mass attitude control system for nanosatellites in orbital transfer stage

LU Zhengliang, ZHANG Xiang, YU Yongjun, MO Qiankun, LIAO Wenhe   

  1. College of Mechanical Engineering, Nanjing University of Science and Technology, Nanjing 210094, China
  • Received:2016-09-12 Revised:2016-11-21 Online:2017-06-15 Published:2016-11-27
  • Supported by:

    The Scientific Research Project of NJUST (30916011101)

Abstract:

A moving-mass control technology is proposed to stabilize the attitude of nanosatellites in orbital transfer stage. After the configuration of actuator masses is obtained, 8 DOF dynamic equations are derived based on momentum and moment of momentum theorem. According to the results of dynamic analysis, a simplified control model is developed. On this basis, a robust controller characterized by a global sliding mode is given to stabilize the yaw and pitch angle and to track the actuator position. The validation of this control system is simulated with the condition of parametric uncertainty. Results indicate that the two-dimensional mass moment control system could rapidly adjust the attitude and have a good robustness against disturbance. It is concluded that this system can be applied for attitude control in orbital transfer.

Key words: orbital transfer, nanosatellite, moving-mass, attitude control, sliding mode control

CLC Number: