To validate the performance of attitude control of the three-axis micro flywheel system, a demo system for three-axis attitude control is made.
为了验证三轴微飞轮的调姿性能，设计了三轴姿态控制实验演示系统。
The three-axis attitude stabilization system of the flexible satellite has been studied, in which three basic vibration modes of the solar array have been considered.
在挠性卫星动力学模型的基础上，建立了只考虑太阳帆板三阶振动模态的挠性卫星三轴姿态控制模型。
As illustration, these models are applied to an attitude control dynamics simulation of a three-axis stability satellite and the corresponding toques were plotted in curves.
为验证模型有效性，将其应用于某三轴稳定对地定向卫星姿态动力学仿真中，得到了相应的太阳光压干扰力矩曲线。
At last, the hardware in the loop simulation system for three-axis stabilized satellite attitude control based on PC, with reaction wheel and gyro in the loop is designed.
最后，该文设计了一个基于PC机的三轴稳定卫星姿态控制硬件在回路仿真系统，将反作用飞轮、陀螺等实物接入仿真系统。
Attitude control problem of a three-axis stabilized, momentum biased, and nadir-pointing satellite is investigated based on yaw observer.
研究了基于偏航观测器的三轴稳定偏置动量对地定向卫星姿态控制问题。
Models of the three-axis stabilized Attitude Control Systems of a rigid satellite and a flexible satellite with a pair of solar arrays are set up.
本论文分别以三轴稳定刚性卫星姿态控制和带太阳帆板的三轴稳定卫星姿态控制为研究对象，建立了控制系统数学模型。
In this paper, the robustness stability analysis of the attitude control system of a three-axis stabilized flexible spacecraft is investigated.
本文应用区间矩阵的理论，研究三轴稳定的挠性空间飞行器姿态控制系统的鲁棒稳定性分析问题。
This paper researches the variation of the Momentum Wheel(MW) rotation rate which is applied to attitude control in three-axis stabilized GEO satellites.
对三轴稳定地球同步卫星中用于姿态控制的偏置动量轮转速变化问题进行研究。
This paper researches the variation of the Momentum Wheel(MW) rotation rate which is applied to attitude control in three-axis stabilized GEO satellites.
对三轴稳定地球同步卫星中用于姿态控制的偏置动量轮转速变化问题进行研究。
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