Journal of Astronautics ›› 2015, Vol. 36 ›› Issue (1): 68-75.doi: 10.3873/j.issn.1000-1328.2015.01.009

Previous Articles     Next Articles

L1 Adaptive Control of Flexible Satellite with Thermally Induced Disturbance

LI Li jun,YUAN Jun   

  1. 1. Beijing Institute of Control Engineering, Beijing 100190,China;
     2. Science and Technology on Space Intelligent Control Laboratory, Beijing 100190,China
  • Received:2013-12-11 Revised:2014-02-20 Online:2015-01-15 Published:2015-01-25


To find out the principle of thermally induced motion of solar panel and its effect on satellite attitude maneuver, the dynamics model of the rigid body with a flexible beam suffered to sudden heat flux is established by using Lagrange method and the thermally induced motion of the panel is also analyzed. Given that system parameters are not known, L1 adaptive controller is designed by using only attitude angle and attitude rate as the feedback signals and the thermally induced distortion and vibration as the unmodeled dynamics. The satellite attitude angle maneuver under the thermally induced disturbance can be performed. Numerical simulation results show that solar panel’s motion contains quasi-static distortion and vibration and the attitude error including constant steady state error and attitude vibration, under the condition of sudden surrounding temperature change. The attitude maneuver can be accomplished rapidly by using the designed L1 adaptive controller in the presence of thermally induced disturbance. And flexible modes of the panel are stable and system parameters converge to a stable state.

Key words: Attitude maneuver, L1 adaptive control;Thermally induced vibration;Flexible solar panel;Dynamics modeling

CLC Number: