中文摘要：

为实现卫星的高精度高稳定度姿态控制,在控制力矩陀螺群（CMGs）和星体之间加装了隔振平台。首先依据整星动力学简化模型推得了隔振系统传递函数矩阵;然后分析了隔振平台的使用给姿态控制系统带来的影响,并提出了一种既能使CMGs隔振平台满足隔振要求,又能保证姿态控制系统充分稳定性的参数选择方案;最后通过数值仿真的方式验证了所提出的参数选择方案的合理性。

英文摘要：

In order to realize high accuracy and stability requirements for satellite attitude control,a vibration isolation platform（VIP） is employed to interface the cluster of control moment gyros（CMGs） with the satellite bus.First,by employing the reduced satellite dynamics model,the transfer function matrix of VIP is obtained.Then,the influence of the VIP on the attitude control system is discussed.A parameter design scheme for VIP is put forward according to the above analysis.The parameters selected by using this scheme can not only satisfy the requirement for vibration isolation but also guarantee that the closed-loop attitude control system remains sufficiently stable.Finally,the rationality of this parameter selection scheme and the application of the VIP for CMGs are proved by numerical simulation.