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为预测反作用轮微振动对航天器产生的影响,提出了一种改进的扰动模型.由于共振造成的扰动放大是反作用轮扰动对卫星姿态精度的最重要影响,改进模型通过引入放大系数体现结构固有频率对扰动的影响.鉴于改进模型的非线性特性,应用模拟退火遗传算法对改进模型进行了参数辨识.设计刚性六分量力测试平台对反作用轮扰动进行测试,并利用实测数据对改进模型及参数辨识结果进行验证.验证结果表明:改进模型准确地反映了反作用轮的扰动特点,模拟退火遗传算法可以提高参数辨识的精度.
In order to predict the influence of reaction micro-vibration on the spacecraft, an improved perturbation model is proposed.As the disturbance amplification caused by the resonance is the most important influence of the reaction wheel disturbance on the satellite attitude accuracy, the improved model embodies the inherent structure Frequency on the disturbance.According to the nonlinear characteristics of the improved model, the simulated annealing genetic algorithm is used to identify the parameters of the improved model.Rigid six-component force test platform is designed to test the reaction wheel disturbance, and the measured data is used to improve the model and parameters The verification results show that the improved model accurately reflects the disturbance characteristics of the reaction wheel, and the simulated annealing genetic algorithm can improve the accuracy of parameter identification.