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分析了小卫星捕获阶段的客观条件要求 ,重力梯度杆的指向要求 ,捕获阶段视为大角度机动问题 ,采用欧拉动力学和四元数方法描述 ,建立小卫星捕获阶段的动力学模型。控制器采用大角度机动拟 PD控制 ,拟PD控制器参数采用了简化分析和经验调试设计 ,同时分析设计了磁力矩器的磁偶极子 ,最后给出某小卫星姿态捕获仿真结果 ,经过几个轨道周期后可以实现一定精度的对地捕获 ,验证了本文的设计方法的可行性。
The objective requirements of the small satellite acquisition phase, the pointing requirements of the gravity gradient rod are analyzed. The capture phase is considered as a large-angle maneuver problem. Euler dynamics and quaternion methods are used to describe the dynamic model of the small satellite acquisition phase. The controller uses a large-angle motorized pseudo-PD control, and the parameters of the pseudo-PD controller adopt simplified analysis and experience debugging design. At the same time, the magnetic dipole of the magnetic torque device is analyzed and analyzed. Finally, the simulation results of a small satellite attitude acquisition are given. After a period of orbit can achieve a certain accuracy of the ground to capture, verify the feasibility of this design method.