Flutter analysis and suppression of an aircraft wing with a flexibly mounted external store using a magneto-rheological damper are investigated. The wing performs as a cantilever beam and the structural model, which incorporates bending-torsion flexibility, is used. A modified Bouc–Wen model is utilized in order to model the elastic connection between the store and the wing. The modified Peter’s finite-state loading is also considered to simulate the aerodynamic force and moment. The governing equations are obtained via Hamilton’s principle and assumed modes method is subsequently applied to transform the resulting partial differential equations into a set of ordinary differential equations. Numerical simulations are validated against several previously published papers by using a clean Goland wing. In order to control the vertical and rotational vibrations of the store and the wing, a state feedback controller and a compensator with full-order observer are designed. The performance of these controllers is compared together in several situations. Eventually, the performances are treated when disturbance is applied to the system. The results show that magneto-rheological damper’s performance is suitable for controlling the limit cycle oscillations of the wing and external store, in flutter condition.
Transonic Wing Flutter Analysis Using a Parallel Euler Solver
