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。
In this paper, the robustness stability analysis of the attitude control system of a three-axis stabilized flexible spacecraft is investigated.
文中给出了系统稳定的充分条件和该方法的实现方式，通过对三轴仿真转台的实验验证了该方法的有效性。
The sufficient condition of the system stability and the realization are given. The effectiveness of the method is illustrated by simulation in a three axis flight simulator.
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。
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.
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。
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.
通过建立三轴稳定质量矩拦截器的数学模型，得到一个非线性动力系统。
According to the constructed model of the mass moment interceptor with three-axial stabilization, a nonlinear dynamic system was acquired.
通过建立三轴稳定质量矩拦截器的数学模型，得到一个非线性动力系统。
According to the constructed model of the mass moment interceptor with three-axial stabilization, a nonlinear dynamic system was acquired.
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