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A robust integrated controller/diagnosis aircraft application

In this paper, an application of the robust integrated control/diagnosis approach using ℋ︁∞‐optimization techniques to the nonlinear longitudinal dynamics of a Boeing 747‐100/200 aircraft is presented. The integrated approach allows to address directly the trade‐off between the conflicting controller and fault diagnosis objectives. The integrated design formulation (interconnection and weight selection) is defined using five LTI plants obtained through out the Up‐and‐Away flight envelope. Linear and nonlinear closed‐loop time simulations are carried out under a realistic turbulence and noise environment. A comparison drawn with the non‐integrated design of a controller and a diagnosis filter with the same objectives shows that the integrated case results in similar diagnosis characteristics but improved fault tolerant performance and ease of design. Copyright © 2005 John Wiley & Sons, Ltd.