Aeroelastic Wing Shaping Control Subject to Actuation Constraints | Zendy

Sean ShanMin Swei | Zendy; Nhan T. Nguyen | Zendy

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Aeroelastic Wing Shaping Control Subject to Actuation Constraints

Author(s) -

Sean ShanMin Swei,

Nhan T. Nguyen

Publication year - 2014

Publication title -

54th aiaa/asme/asce/ahs/asc structures, structural dynamics, and materials conference

Language(s) - English

Resource type - Conference proceedings

DOI - 10.2514/6.2014-1041

Subject(s) - aeroelasticity , wing , subject (documents) , computer science , aerodynamics , control (management) , wing configuration , actuator , aeronautics , aerospace engineering , control engineering , control theory (sociology) , engineering , artificial intelligence , library science

This paper considers the control of coupled aeroelastic aircraft model which is configured with Variable Camber Continuous Trailing Edge Flap (VCCTEF) system. The relative deflection between two adjacent flaps is constrained and this actuation constraint is accounted for when designing an effective control law for suppressing the wing vibration. A simple tuned-mass damper mechanism with two attached masses is used as an example to demonstrate the effectiveness of vibration suppression with confined motion of tuned masses. In this paper, a dynamic inversion based pseudo-control hedging (PCH) and bounded control approach is investigated, and for illustration, it is applied to the NASA Generic Transport Model (GTM) configured with VCCTEF system.

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