摘要

Attitude control is a basic task of a spin-stabilized satellite control. There are many kinds of attitude control methods, this paper does research for equiangular precession method. The paper first introduced the basic principle of equiangular precession method, and then gave out a detailed calculation method of attitude control quantity, which included theory executing angular, executing times and time delay, finally attitude maneuver process were simulated. The simulation result shows that the computed result of attitude control quantity is correct, the forecasts for control process are essentially the same as practice. The method has been applied to satellite launch mission.

  • 出版日期2016
  • 单位中国卫星海上测控部