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 reconfigurability metric standard of control moment gyro of satellite actuator was studied,and a reconfigurability metric standard under energy consumption constraint was proposed.Based on the satellite attitude control dynamics equation and kinematic equation,a linear dynamics equation was established in the form of state space.Failure fault factor vector was introduced into the linear dynamic equation.The reconfigurability metric standard was established based on Gram matrix.Finally,simulation was made for control moment gyro group with pyramid configuration,and the result show that this method is correct and effective.