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Variable structure flutter control of a prototypical wing section with unsteady aerodynamics

Chemplavil S. C., Singh S. N., Wells W. R.

Systems Science

2004

Vol. 30, no 2

109-118

This paper presents a variable structure control system for the realization of an aeroelastic system with unsteady aerodynamics. The aeroelastic model describes the plunge and pitch motion of a wing. Based on the sliding mode design technique, a control law for the trajectory control of the pitch angle is derived. For the synthesis of the controller, only the plunge displacement, pitch angle, control surface deflection and their derivatives are measured, and the states associated with Theodorsen's function are treated as unknown signals. In the closed-loop system, the state vector asymptotically convergers to the origin.

Stability of a circular ring in postcritical equilibrium states with two deformation-dependent loads and geometrical imperfections

Kozak I., Szabo T.

Computer Assisted Mechanics and Engineering Sciences

2002

Vol. 9, No. 2

291-308

The circular ring is linearly elastic and its cross-section is rectangular. Two deformation dependent distributed loads, that is follower loads, are applied simultaneously on the outer surface of the ring. The first load is a uniform pressure on the whole outer surface. The second load is uniform normal traction exerted on two surface parts situated in axially symmetric positions. Both loads are selfequilibrated independently from each other. A nonlinear FE program with 3D elements is used for the numerical analysis of a geometrically perfect and two imperfect rings. Displacement control is used in the equilibrium iterations. Equilibrium surfaces are determined in the space of three parameters such as one characteristic displacement coordinate, and two load factors. The stability analysis is performed in the knowledge of the equilibrium surfaces.