Aircraft airbrakes compensation design using iterative inversion

Abstract

This paper deals with the synthesis of an open-loop control law of a civilian aircraft for the compensation of the pitching moment generated by the extension of airbrakes. The proposed method uses in-flight recorded data and is based on impulse response identification and inverse simulation, whose results are used to design the controller upon qualitative assumptions.Results are then given for both the inversion and the synthesis for different flight cases. The robustness of the method to measurement noise is also assessed.