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In the event of a control surface failure, the purpose of a reconfigurable flight control system is to redistribute and coordinate the control effort among the aircraft's remaining effective surfaces such that satisfactory flight performance is retained. In this paper, a model following reconfigurable flight control system designed for the AFTI/F-16 is discussed. The system utilizes an adaptive proportional plus integral controller with gain adjustment based on errors between desired performance and actual performance. Stability analysis and simulation results are presented.
Morse et al. (Thu,) studied this question.