A Discrete Sliding Mode Control Method for Piezoelectric Driven Deformed Wings
A piezoelectric drive and control method technology, applied in the field of flight control, can solve the problems of increased structural weight failure rate of components, limited control surface deflection angle, limited output control force, etc., to reduce the weight and complexity of the wing, maintain Structural integrity, lift-enhancing effect
Active Publication Date: 2022-05-31
SHANGHAI UNIV OF ENG SCI
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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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[0098] The present invention will be further described below in conjunction with specific embodiments. It should be understood that these examples are only used to illustrate the present invention and not to limit the scope of the present invention. In addition, it should be understood that after reading the content taught by the present invention, those skilled in the art can make various changes or modifications to the present invention, and these equivalent forms also fall within the scope defined by the appended claims of the present application.
[0099] A discrete sliding mode control method for a piezoelectrically driven deformable wing of the present invention includes: (a) establishing a coupled dynamics model for piezoelectrically suppressing wing flutter; (b) applying the coupled dynamics model to discrete control and sliding-mode control, the discrete sliding-mode control control law of the piezoelectrically driven deformable wing is obtained; figure 1 It is a flo...
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The invention relates to a discrete sliding mode control method for a piezoelectrically driven deformed wing, comprising: (a) establishing a coupled dynamics model for piezoelectrically suppressing wing flutter according to the Lagrangian equation; Sliding mode control and the coupling dynamics model, the discrete sliding mode control control law of piezoelectrically driven deformed wing is obtained, and the input voltage is carried out according to this control law, and the wing can turn from a flutter state to a stable state within a limited time . The invention also performs numerical simulation on the discrete sliding mode control. The most important feature of the present invention is the use of a new type of piezoelectric actuator, which has better driving strain, and at the same time, the wing surface can be actively controlled, thereby reducing the weight of the wing and improving the reliability of the wing; in addition, the discrete sliding mode control method is adopted A discrete sliding mode controller is designed to effectively suppress the wing bending-torsional coupling flutter.
Description
technical field [0001] The invention belongs to the technical field of flight control, and relates to a discrete sliding mode control method for piezoelectrically driven deformable wings, in particular to a discrete sliding mode control method for piezoelectrically driven deformable wings 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 interaction of aerodynamic force, elastic force and inertial force under the action of the wing and the air flow during the flight of the aircraft; when it exceeds a certain critical speed , the slight disturbance will cause the vibration to diverge, and the amplitude of the wing will increase sharply. Wing flutter is one of the main forms of aircraft failure, and the flutter problem is also the main aerodynamic problem faced by high-speed aircraft. The wing flutter suppression m...
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IPC IPC(8): G05B13/04
CPCG05B13/042Y02T90/00
Inventor 袁家信李达杨慧胡志贤
Owner SHANGHAI UNIV OF ENG SCI