This article addresses the issues of model reduction and actuator/sensor placement for flexible spacecraft with plant, actuator, and sensor faults. First, the sensitivity of controllability and observability with respect to faults is analyzed; Second, instead of a complete redesign of balanced truncation, a fault tolerant truncation method is proposed by estimating the bounds of Hankel singular value of faulty spacecraft and is fully based on the original balanced truncation structure; Third, a reconfiguration scheme of actuator/sensor placement is developed based on the reduced-order faulty flexible spacecraft.
Fault Tolerant Model Reduction and Actuator/Sensor Placement for Flexible Spacecraft
IEEE Transactions on Aerospace and Electronic Systems ; 57 , 2 ; 1334-1344
2021-04-01
751207 byte
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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