Spacecraft attitude fault tolerant control based on multi-objective optimization
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Aerospace Research Institute, Ministry of Science, Research and Technology, Tehran, Iran
Sharif University of Technology, Department of Aerospace Engineering, Tehran, Iran
Submission date: 2019-09-08
Final revision date: 2020-01-26
Acceptance date: 2020-03-25
Online publication date: 2020-10-15
Publication date: 2020-10-15
Corresponding author
Alireza Alikhani   

Dynamics and control, Aerospace research institute, Iran
Journal of Theoretical and Applied Mechanics 2020;58(4):983-996
An active fault tolerant controller is designed for the attitude control of a faulty spacecraft. Feedback linearization and Lyapunov’s direct method are used to solve angular velocity equations and to ensure convergence of the system outputs to reference inputs, respectively. In order to ensure finite time convergence, final time constraints are proposed. Three con- structive objective functions are considered as performance measures and optimized using multi-objective optimization. The results show that the outputs converge to the reference attitudes, even for severe actuator faults/failures.
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