本文就是在这种背景下,从理论和应用两个方面对应单框架控制力矩陀螺(SGCMG)作为执行机构的卫星大角度姿态快速机动决策以及控制进行了深入的研究,提出了同时解决若干问题的方案。
基于43个网页-相关网页
·2,447,543篇论文数据,部分数据来源于NoteExpress
根据实际情况限定了大型航天器单框架控制力矩陀螺(SGCMG)构型分析研究的对象;
The single gimbal control moment gyro (SGCMG) configuration of a large spacecraft is studied. First, the research object of analyzing configuration is restricted.
提出了一种用于双框架控制力矩陀螺的梯度型伪逆控制律,介绍了控制律的原理与计算方法。
The design of a gradient singularity avoidance pseudo-inverse control law used for double gimbal control moment gyro (DGCMG), its principle and calculation were introduced.
研究了以变速控制力矩陀螺(VSCMG)作为执行机构的卫星多目标快速机动的控制问题。
The multi-target rapid maneuver control problem is studied for agile satellites with Variable Speed Control Moment Gyro(VSCMG) as actuator.
应用推荐