一类质心突变飞行器的重构容错控制(英文)

Reconfigurable Fault Tolerant Control for Spacecraft with Abrupt Changes of Centroid

提出了一类质心突变飞行器的一种故障诊断与控制律重构设计方法。采用以unscented卡尔曼滤波为基本估计单元且用闭环系统性能为指标的交互式多模型算法对飞行器故障情况进行检测与诊断;设计了飞行器比例导数加前馈补偿的姿态跟踪控制律;当诊断出故障时,重构控制律的结构,采用滑模变结构容错控制律对系统进行补偿控制。最后,用飞行器一次分离体释放前后的姿态跟踪过程进行了数值仿真,验证了方法的有效性。

This paper proposes an integrated fault detection, diagnosis, and reconfigurable control method for a spacecraft with abrupt changes of centroid. A novel interacting multiplemodel algorithm, based on the unscented Kalman filter and an index related to the closed-loop system performance, is presented to detect and diagnose the faults. To achieve steady attitude tracking, the controller which shares the structure of a proportional-derivative feedback plus feedforward compensation is designed. When a fault is detected and isolated, the controller structure is reconfigured and the variable structure fault tolerant controller with sliding mode is adopted to compensate the faulty system to maintain the system performance. A simulation example evaluating the attitude tracking process before and after load release is employed, which demonstrates the efficiency of the proposed approach.