Flexible wing flutter model variable in trailing edge

Abstract

The invention relates to a flexible wing flutter model variable in trailing edge and belongs to the technical field of aeroelasticity tests. The flexible wing flutter model comprises a wing beam, a leading edge dimensional-shape frame section, a trailing edge frame section, a trailing edge control connection rod and a steering engine. The leading edge dimensional-shape frame section is fixed to the wing beam and hinged to the trailing edge frame section, the steering engine is arranged on the wing beam, and accordingly the trailing edge frame section can be driven to deflect relative to the leading edge dimensional-shape frame section through the steering engine; and one end of the trailing edge control connection rod is arranged on the leading edge dimensional-shape frame section, and the other end of the trailing edge control connection rod is arranged on the trailing edge frame section so that the deflection directions of multiple frame section bodies of the trailing edge frame section can be controlled. According to the flexible wing flutter model variable in trailing edge, a hinge rod mode is adopted, the wing trailing edge can be deformed through movement of the connection rod, wing unsteady aerodynamic distribution is changed so that a wing can dissipate energy outwards, and accordingly the flutter inhibition purpose is achieved.

Description

technical field [0001] The invention belongs to the technical field of aeroelasticity test, in particular to a flexible wing flutter model with variable trailing edge. Background technique [0002] Compared with the traditional wing structure, the active flexible wing structure can achieve real-time changes in important parameters such as wing shape, thickness, and camber, so on the one hand, it can reduce or even cancel the traditional wing active surface and related control systems. Change the distribution of unsteady aerodynamic forces on the wing, so that the wing can dissipate energy outward, so as to achieve the purpose of increasing the flutter speed and slowing down the gust and maneuvering load. [0003] The trailing edge frame section of the existing wing flutter model is usually designed as a whole, and the driving mechanism fixed on the leading edge of the wing drives the trailing edge frame section to deflect. The deflection is not conducive to the unsteady aer...

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Problems solved by technology

[0003] The trailing edge frame section of the existing wing flutter model is usually designed as a whole, and the driving mechanism fixed on the leading edge of the wing drives the trailing edge frame section to deflect. The deflection is not conducive to the unsteady aerodynamic force distribution of the wing, which in turn makes the energy efficiency of the wing dissipated outward low. If the deflection of the trailing edge frame is to be carried out in stages, it is often necessary to design multiple drive mechanisms. The aerodynamic layout will have a greater impact and bring difficulties to design and processing

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