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为了实现卫星在飞轮电池储放能过程中保持姿态不变或按要求实现姿态机动,采用理论分析与实验测试相结合的方法,建立了应用于卫星的集成化单轴储能与姿态控制模拟实验系统的数学模型,并对集成化单轴储能及姿态控制模拟实验系统进行了实验研究。系统储能过程中,针对上、下飞轮电机单元系统模型参数变化较大,通过串联校正的方法进行了补偿,提出了积分离式分段PID复合控制算法;而系统放能与姿态调整过程中,两飞轮模型基本一致,采用了可控恒流源与PD控制相结合的方法。初步实验表明,采用该方法有效抑制了超调,实现了系统在高转速、宽范围内的稳定控制。储能过程中,系统姿态控制精度达到1.0°;放能过程中,系统姿态控制精度达到0.5°,折算到百公斤级卫星的姿态角控制波动量分别为1.2’和0.6’。
In order to maintain the attitude of the satellite during the process of storing and releasing the flywheel battery or to realize the attitude maneuver as required, a simulation experiment of integrated uniaxial energy storage and attitude control applied to the satellite was established by a combination of theoretical analysis and experimental testing The mathematical model of the system and the experimental research on the integrated simulation system of uniaxial energy storage and attitude control are carried out. In the process of energy storage, the model parameters of the upper and lower flywheel motor units vary greatly and are compensated by the method of series correction. The integrated fractional segmented PID compound control algorithm is proposed. In the energy release and attitude adjustment process , The two flywheel model is basically the same, using a combination of controllable constant current source and PD control method. Preliminary experiments show that this method can effectively suppress the overshoot and realize the stable control of the system at high speed and wide range. During the process of energy storage, the attitude control accuracy of the system reaches 1.0 °. During the energy release, the attitude control precision of the system reaches 0.5 °. The fluctuation of attitude angle control converted to 100 kg satellites is 1.2 ’and 0.6’ respectively.