一类质心突变飞行器的姿态控制律重构设计

Attitude Controller Reconfiguration for Spacecrafts with Abrupt Change of Centroid

研究了一类质心突变飞行器姿态控制系统在发生故障时的一种控制律重构方法。采用以Unscented卡尔曼滤波为基本估计单元且用输出残差为故障诊断指标的交互式多模型算法实时地对飞行器故障情况进行检测与诊断。当诊断出故障时,重构控制律的参数对系统进行补偿控制,使得故障下飞行器的姿态跟踪精度得以维持。通过数值仿真验证了该方法的有效性。

This paper proposes a fault-tolerant reconfigurable controller for attitude control system of spacecrafts with abrupt changes of centroid. A novel interactive multiple model algorithm, based on the Unscented Kalman filter and a performance index using output residuals, is presented to diagnose the faults. Once a fault is detected and isolated, controller parameters can be reconfigured to compensate the loss of performance and to keep the good attitude tracking accuracy of the spacecraft. Numerical simulations validate the effectiveness of the proposed method.