Discrete sliding mode control method of piezoelectric drive deformable wing

Abstract

The invention relates to a discrete sliding mode control method of a piezoelectric drive deformation wing. The discrete sliding mode control method comprises the following steps: (a) establishing a coupling kinetic model of piezoelectric suppression wing flutter according to a Lagrange equation; and (b) according to discrete control, sliding mode control and the coupling dynamic model, obtaining adiscrete sliding mode control law of the piezoelectric drive deformation wing, and if the input voltage is carried out according to the control law, converting the wing into a stable state from a flutter state within limited time. Numerical simulation is carried out on discrete sliding mode control. The method has the most important characteristics that a novel piezoelectric actuator is adopted,the driving strain is better, and meanwhile, the wing surface of the wing can be actively controlled, so that the weight of the wing is reduced, and the reliability of the wing is improved. In addition, a discrete sliding mode controller is designed by adopting a discrete sliding mode control method, and wing bending-torsion coupling flutter is effectively inhibited.

Description

technical field [0001] The invention belongs to the technical field of flight control, and relates to a discrete sliding mode control method for a piezoelectrically driven deformed wing, in particular to a discrete sliding mode control method for a piezoelectrically driven deformed wing that is closer to an actual control system and has anti-interference performance method. Background technique [0002] The so-called wing flutter is the phenomenon of self-excited vibration of the wing under the action of the wing and air flow during the flight of the aircraft under the interaction of aerodynamic force, elastic force and inertial force; when the aircraft exceeds a certain critical speed , small disturbances will cause the vibration to diverge, and the amplitude of the wing will increase sharply. The consequences will be very serious, causing damage to the wing or even disintegration of the aircraft, threatening the safety of the aircraft. Wing flutter is one of the main form...

AI Technical Summary

Problems solved by technology

The traditional control method mainly relies on the deflection of the control surface at the trailing edge of the wing to suppress flutter. Although the structure of the device is simple, this control method requires multiple energy conversions (mechanical, hydraulic, electrical, etc.), and a large number of components increase the structural weight. and potential failure rate, high vulnerability of hydraulic piping network, limited frequency bandwidth, limited deflection angle of control surfaces, and thus limited output control force

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