Journal of Astronautics ›› 2011, Vol. 32 ›› Issue (9): 1911-1917.doi: 10.3873/j.issn.1000-1328.2011.09.007

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Study on Attitude Decoupling Control for Advanced Upper Stage
during Orbital Maneuver

CUI Nai   

  1. (School of Astronautics, Harbin Institute of Technology, Harbin 430072, China)
  • Received:2010-02-01 Revised:2010-05-01 Online:2011-09-15 Published:2011-09-28

Abstract: For the issues of attitude strong coupling and large disturbances of advanced upper stage with multi\|satellite deploying when the main engine is working, a feedback linearization\|based attitude decoupling control algorithm is presented. By definitions of coordinates and the attitude angle during multi\|satellite deploying, the attitude dynamics and kinematics equations described by Euler angles are built. A control method combining thrust vector control of the main engine and attitude control thrusters is proposed. The configuration of these actuators is described. The formulas of swing angles of the main engine are derived. A feedback linearization\|based attitude PD control law is designed. An example of mathematical simulation is completed. And the errors of attitude angular velocity and attitude angle can quickly tend to
1°/s and 0.5°respectively. Simulation results show that the decoupling control algorithm has good stability and feasibility.

Key words: Upper stage, Attitude control, Decoupling control, Thrust vector control, Feedback linearization

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