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单框架控制力矩陀螺(SGCMG)在卫星姿态控制中以其具有大力矩输出能力而受到重视并已成功应用于在轨卫星,其应用难点是构形奇异问题,特别是在快速连续机动的过程中,CMG框架角必须迅速脱离奇异状态.使用描述CMG输出力矩和期望控制力矩夹角的奇异度量方法,以便在仿真中观察判别CMG构形的奇异程度.着重改进CMG的奇异鲁棒操纵律,应用高斯函数的方法确定鲁棒系数.仿真实例表明,与传统的梯度型零运动相比,该方法可以在卫星的连续快速机动中使CMG系统更为迅速地摆脱奇异,更为快速地完成机动并减小姿态抖动.
Single-frame control moment gyroscope (SGCMG), which has received great attention in satellite attitude control and has been successfully applied to on-orbit satellites, has its application difficulty in the configuration singularity problem, especially in the process of rapid continuous maneuver , The CMG frame angle must be quickly separated from the singular state.Using the singularity measurement method that describes the angle between the CMG output torque and the desired control moment to observe the singularity of the CMG configuration in the simulation.We focus on improving the CMG’s singular robust manipulative law, Gaussian function to determine the robust coefficient.The simulation results show that this method can make the CMG system get rid of the singularity more quickly than the traditional gradient type zero motion, Reduce gesture jitter.