Implicit model following technique for aircraft configuration with multiple control surfaces

The implicit model following technique, based on linear quadratic theory, was applied to design the flight control augmentation system (FCAS) of an aircraft with multiple control surfaces. The selection philosophy for the ideal model was investigated, which is based on the flight dynamics and the flying qualities requirements. The closed-loop design schemes were evaluated according to command following accuracy and ability to subdue effects of the atmospheric turbulences and other disturbances, where the structured singular value analysis method was adopted to evaluate robust stability and robust performance of the FCAS. The results show that the designed FCAS can subdue the turbulence and has good robust stability and adequate robust performance.