A lateral flight control design for a flexible aircraft is presented. It is based on a standard two-input-two output problem formalism and H-2 synthesis. The proposed approach consists of two steps. The first step deals with the synthesis of a dynamic output feedback satisfying modal specifications on the rigid modes, stability requirements on the structure, and performance robustness with respect to the various loading cases. The originality in the synthesis setup proposed is that it combines eigenstructure assignment, H-2 frequency domain synthesis, and parametric robustness design. The second step uses a recent theoretical result to transform a given compensator into a linear quadratic Gaussian compensator involving a judiciously selected onboard model, The two-degree-of. freedom compensator thus obtained allows time-domain specifications in response to the pilot's commands to be met satisfactorily. A detailed discussion is provided of the approach together with the aircraft models used and corresponding closed-loop analysis. References: 19
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