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对卫星执行机构控制力矩陀螺的可重构性度量标准进行了研究,提出了一种基于能耗约束下的控制力矩陀螺可重构性度量标准。结合卫星姿态控制动力学与运动学方程,建立状态空间形式表达的线性姿态动力学方程,将故障失效因子向量引入到线性空间方程;建立了基于格兰姆矩阵的可重构性度量标准。最后对金字塔构型的控制力矩陀螺群进行仿真分析,仿真结果符合实际情况,验证了该度量标准的正确性与有效性。
The reconfigurable metric of the control moment gyro of satellite actuator is studied, and a metric of reconfigurable control moment gyroscope based on the constraint of energy consumption is proposed. Combining satellite attitude control dynamics and kinematic equations, a linear attitude dynamics equation in the form of state space is established, and the failure failure factor vector is introduced into the linear space equation. A reconfigurable metric based on the Gram matrix is established. Finally, the control moment gyroscopic group of the pyramid configuration is simulated and the simulation results are in accordance with the actual situation, which verifies the correctness and validity of the metric.