论文部分内容阅读
针对反作用飞轮中存在的力矩波动和力矩跳动这2种非理想电磁力矩,分析其产生机理,建立了轮控微小卫星姿态稳定控制系统的仿真模型.分析了力矩波动系数和力矩波动频率、力矩跳动幅值和跳动持续时间对卫星姿态的影响,最后给出抑制非理想电磁力矩的措施.分析和仿真表明:当卫星姿态控制精度要求较高时,非理想电磁力矩的影响不容忽视.力矩波动使卫星姿态发生同频率波动,在飞轮转速过零时力矩波动的影响最大,力矩跳动使卫星姿态发生偏差.避免反作用飞轮转速过零、提高力矩波动频率、降低力矩波动系数、减小力矩跳动幅值和跳动持续时间均可有效降低非理想电磁力矩对卫星姿态的影响.
According to the two kinds of non-ideal electromagnetic moments existing in reaction flywheel, such as torque ripple and torque runout, the generation mechanism is analyzed, and the simulation model of wheelset micro-satellite attitude stability control system is established. The torque fluctuation coefficient and torque fluctuation frequency, Amplitude and duration of beating on the attitude of the satellite are discussed.At last, measures to suppress the non-ideal electromagnetic torque are given.Analysis and simulation show that the impact of non-ideal electromagnetic torque can not be ignored when the satellite attitude control accuracy is high, Satellite attitude occurs with the same frequency fluctuations in the flywheel zero crossing torque moment when the impact of the largest torque beats the attitude of the satellite deviation to avoid reaction flywheel zero speed, increase torque ripple frequency, reduce the torque fluctuation coefficient, reduce the torque jump amplitude And beating duration can effectively reduce the impact of non-ideal electromagnetic torque on satellite attitude.