Aeroservoelastic Design with Distributed Smart Actuation System for High Performance Aircraft.
Technical rept. Jul 97-Dec 98,
CSA ENGINEERING INC PALO ALTO CA
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This report describes the work done by the author to study the feasibility of shaping lifting surfaces via distributed smart actuation systems to achieve high performance flight configurations. In this report, the focus is on first obtaining and identifying optimal distributed-parameter-control equivalent actuation profiles for desired flight maneuvers by a modal synthesis approach. Subsequently, this distributed-parameter equivalent aeroservoelastic solution is to be implemented via a multitude of spatially-discrete actuators distributed throughout the domain of the lifting surface. The selection of the number and distribution of discrete actuators is to be based on optimal approximation solutions which use the optimal distributed-parameter-control equivalent solution as a guiding design. The insight to solutions are sought by considering the aeroservoelastic interactions among aerodynamics, structural flexibility and control actuators from the perspective of work-energy, control power, and control loading requirements. The aeroelastic modal formulation is presented in terms of real modal matrices and modal-state variables. Real bi-orthonormality relationships for aeroelastic modes are given with respect to structural matrices. The solution for distributed-parameter-control of an aeroelastic system is developed by modal synthesis from modal-state-space control inputs. In particular, the globally power optimal Independent Modal-Space Control IMSC technique is used for maneuver set-point control of an aeroelastic system by a modal-performance-output synthesis approach. Control power functionals for an aeroelastic system are defined for any actuation profile and control design.