Abstract

In this paper a new design and analysis method for aeroelastic control of composite lifting surfaces is presented. The novel feature of the method is the integration of the active control design to the structural design through aeroelastic tailoring. The design is posed as an optimization problem to determine fiber orientations of the individual laminae of the composite structure, together with an optimum quadratic control cost to maximize the critical (flutter or divergence) speed of the system. The method is illustrated for the design of a symmetric cantilevered composite plate, of a given geometry, with structural and control constraints.

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