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为实现遥感卫星的高精度指向能力,对遥感卫星星上常用执行机构控制力矩陀螺扰动及性能指标评定进行了研究。首先,充分考虑小型控制力矩陀螺的静动不平衡量以及框架轴的安装误差,根据动量定理和动量矩定理建立了完整的星载小型控制力矩陀螺的动力学模型,并对所建立模型的正确性进行了理论分析和仿真验证;其次,将含有扰动特性的小型控制力矩陀螺应用到星上,建立了整星动力学模型,并选用合适的框架伺服控制系统和转子伺服控制系统,完成整星的姿态稳定控制任务;最后,采用数值仿真的方式分析了陀螺转子静动不平衡因素以及框架角测量误差对星体姿态精度和稳定度带来的影响。结合任务要求,对小型控制力矩陀螺设计提出静动不平衡量等指标要求,以期使其满足星上光学有效载荷的成像要求。
In order to realize the high-precision pointing ability of remote sensing satellites, the disturbance and performance evaluation of control moment gyroscopes commonly used in remote sensing satellite are studied. First of all, considering the static and dynamic unbalance of the small control moment gyroscope and the installation error of the frame axis, a complete dynamic model of the small spacecraft control moment gyroscope is established according to the momentum theorem and the momentum theorem. The correctness of the model The theoretical analysis and simulation verification are carried out.Secondly, the small control moment gyroscope with perturbation characteristics is applied to the star, and the whole-body dynamics model is established, and the appropriate frame servo control system and rotor servo control system are selected to complete the whole star Attitude stability control task. Finally, numerical simulation is used to analyze the influence of gyro-rotor unbalance and frame angle measurement error on the attitude accuracy and stability of the celestial body. Combined with the mission requirements, the small control moment gyroscope design proposed the requirements of static and dynamic unbalance and other indicators, in order to make it meet the optical imaging requirements of the satellite payload.