The article describes the methodology of a hybrid system for ensuring the fault tolerance of the sensing and actuating subsystems of the flight control system high-speed rotorcraft, capable of solving problems of detection, isolation, identification and compensation of failures in real time under parametric uncertainties. The hybrid approach is based on the joint use of model-based and data-based methods. The main advantage of the methodology described in the article is determined by the use of a single mathematical apparatus in the implementation of both groups of methods. To demonstrate the performance of the methods, a methodical example of a lower-order high-speed rotorcraft dynamics linear model is considered. The results of symbolic and numerical simulation in case of flight control system failure show the operability of the proposed methods. The implementation of the approach being developed will lead to an increase in the levels of reliability and testability of the flight control system, as well as a reduction in its weight and cost due to the rejection, in some cases, of redundant hardware redundancy of the sensing and actuating subsystems, which currently has a 3rd or 4th multiplicity.
High-Speed Rotorcraft Flight Control System Fault Tolerance Under Parametric Uncertainty
13.04.2023
1285569 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
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