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本文引入卫星动力学等效概念,把单自旋卫星的动力学分析、制控的概念和方法推广应用到双自旋卫星。提出了双自旋卫星的双脉冲闭路控制的设计方案。分析了由于结构误差引起的摆动,给出了摆动角的计算公式和卫星姿态的稳定判据。论证了管一球武章动阻尼器也适用于双自旋卫星。证明了章动阻尼器不能消除摆动,甚至对卫星姿态误差产生不可忽视的影响;最大姿态误差角等于章动角和摆动角之和。最后,用仿真试验验证了分析结果。
This paper introduces the equivalent concept of satellite dynamics and extends the application of the concepts and methods of dynamic analysis and control of single-spin satellites to double-spin satellites. The design scheme of double-pulse closed-loop control of double-spin satellite is proposed. The swing caused by the structural error is analyzed. The formulas for calculating the swing angle and the stability criterion of the satellite attitude are given. It is proved that the tube-ball martial motion damper is also suitable for double-spin satellites. It is proved that the nutation damper can not eliminate the wobble and even has an irreversible effect on the satellite attitude error. The maximum attitude error angle is equal to the sum of the nutation angle and the wobble angle. Finally, the simulation results verify the analysis results.