抄録
This paper presents a design method of reconfigurable flight control systems based on the coprime factorization method. The baseline robust control system is designed using the normalized coprime factorization method. The identification method employed is a closed-loop one, which is also based on coprime factorization; therefore, the method is suitable to the robust control system. The ν-gap metric is chosen as a criterion that indicates the effects of failures on stabilizability of the robust control system. The ν-gap metric can be computed using the identified parameters. To illustrate the effectiveness of the control and identification method, a design example and simulation results for the F-18 HARV are shown.
