{"title":"Applied Actuator Fault Accommodation in Flight Control Systems Using Fault Reconstruction Based FDD and SMC Reconfiguration","authors":"A. Ghodbane, M. Saad, J.-F. Boland, C. Thibeault","country":null,"institution":"","volume":91,"journal":"International Journal of Mechanical and Mechatronics Engineering","pagesStart":1141,"pagesEnd":1147,"ISSN":"1307-6892","URL":"https:\/\/publications.waset.org\/pdf\/9998722","abstract":"

Historically, actuators’ redundancy was used to deal
\r\nwith faults occurring suddenly in flight systems. This technique was
\r\ngenerally expensive, time consuming and involves increased weight
\r\nand space in the system. Therefore, nowadays, the on-line fault
\r\ndiagnosis of actuators and accommodation plays a major role in the
\r\ndesign of avionic systems. These approaches, known as Fault
\r\nTolerant Flight Control systems (FTFCs) are able to adapt to such
\r\nsudden faults while keeping avionics systems lighter and less
\r\nexpensive. In this paper, a (FTFC) system based on the Geometric
\r\nApproach and a Reconfigurable Flight Control (RFC) are presented.
\r\nThe Geometric approach is used for cosmic ray fault reconstruction,
\r\nwhile Sliding Mode Control (SMC) based on Lyapunov stability
\r\ntheory is designed for the reconfiguration of the controller in order to
\r\ncompensate the fault effect. Matlab®\/Simulink® simulations are
\r\nperformed to illustrate the effectiveness and robustness of the
\r\nproposed flight control system against actuators’ faulty signal caused
\r\nby cosmic rays. The results demonstrate the successful real-time
\r\nimplementation of the proposed FTFC system on a non-linear 6 DOF