State-space theory is employed here to model a new active wing flutter suppression control. In this paper, the design of a flutter suppression control law, for the NASA Benchmark Active Control Technology wing, is proposed through a single input-single output controller and unsteady aerodynamics is modelled using the Theodorsen''s theory. Wing dynamic model is obtained by combining the aeroelastic equations of motion with the actuator model presented. Open-loop dynamic behaviour is examined for a single feedback variable that combines pitch and plunge accelerations. Here, a new formulation of control law, based on classical control techniques and featuring two feedback closed-loops, is successfully employed to reach superior stability robustness with respect to other control laws designed with classical flutter suppression schemes having only one feedback closed-loop. The process allows the stability of the aeroelastic system for flight speeds that exceed the open-loop flutter velocity.
|Numero di pagine||12|
|Rivista||PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS. PART G, JOURNAL OF AEROSPACE ENGINEERING|
|Stato di pubblicazione||Published - 2007|
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