自旋小卫星姿态动力学建模与控制研究

Research on Attitude Dynamics Modeling and Control for Spin-Stabilized Micro-Satellite

研究探测近地空间自旋稳定小卫星姿态动力学建模与姿态控制问题,探测任务对该卫星姿态控制有着特殊要求。建模中特别考虑了自旋小卫星双侧伸杆扰动对其姿态运动的影响。利用自旋卫星的章动特性,设计了姿态-章动联合控制器,根据星体横向角速度相位和喷气力矩在惯性空间的方位来确定喷气时刻,采取先章动粗控与进动控制,后章动精控的策略。当卫星受空间扰动力矩长期作用产生较大章动角而需调姿进行轨道机动时,可以应用本控制器方便地调整自旋轴的指向。

Research involved attitude dynamics modeling in this paper focuses on and control of a spinstabilized micro-satellite for near-earth space exploration. There are some special requirements for attitude control due to the scientific mission. During modeling, the effect of double-side booms-extended disturbance on the satellite attitude has been considered in detail. Using the nutation characteristics of the spin-stabilized satellite, a controller of attitude control combined with nutation control has been designed. The firing time is determined based on the phase of satellite transverse angular velocity and the orientation of jet torque in the inertial space. Following control strategy has been applied： firstly coarse nutation control and precession control, then fine nutation control. When the satellite nutation angle is large due to the long term action of disturbance torques and orbit maneuver is needed, this controller can be used to adjust the orientation of spin axis conveniently.