Integrated structure/control/aerodynamic synthesis of actively controlled composite wings

A new multidisciplinary optimization capability for integrated synthesis of actively controlled composite wings is reviewed. It is shown that the nonlinear programming/approximation concepts approach to design optimization, combined with appropriate simplified analysis techniques for the different disciplines, make multidisciplinary wing synthesis both feasible and practical for the conceptual and preliminary design stages. The composite wing of a remotely piloted vehicle is used for numerical experimentation. Synthesis studies with design variables and constraints that span the disciplines of structures, control, and aerodynamics are presented. These studies provide new insight into the complex nature of multidisciplinary interactions in wing design. [A], { [AD} D/(APPRX) {P} {P} {qc} {qc} Nomenclature aeroservoelastic system state space matrix and input vector in standard form aerodynamic matrix used for the calculation of induced drag control system design variables (coefficients in the transfer function of a control law) induced drag induced drag approximation number of terms in the thickness polynomial for t(x, y) number of terms in the Ritz polynomial series for elastic deformation w(x, y) number of terms in the polynomial series for jig shape structural generalized stiffness matrix aeroelastic (structural and aerodynamic) generalized stiffness matrix generalized static loads generalized loads in maneuver (including inertial, jig shape, and control surface contributions) static generalized displacements generalized displacements in maneuver (including control surface rotation needed) approximate generalized displacements in maneuver