Design method of static aeroelasticity test model

Abstract

The invention provides a design method of a static aeroelasticity test model. The design method comprises the following steps: firstly, through a similarity relationship, calculating the section rigidity of the model, and utilizing relevant three-dimensional modeling software to carry out model section design, wherein the designed model section comprises the leading edge, the trailing edge and a windward side of a wing so as to realize a purpose on improving leading and trailing edge model rigidity; using rigid form to fill a metal girder so as to guarantee the aerodynamic configuration of the model; and painting the surface of the model to guarantee the surface flatness of the model. Through an integrative structural model, the deformation of the surface of the model in a wind tunnel test can be effectively reduced, and influence on wing aerodynamic force due to the deformation of the surface of the model is eliminated. In addition, since the leading edge and the trailing edge of the model are made of metal materials, the strength of the model is greatly improved.

Description

technical field [0001] The invention relates to wind tunnel test technology, in particular to static aeroelastic test technology, and belongs to the field of aerospace engineering. Background technique [0002] In order to measure the aeroelastic performance of the aircraft, the method of static air bomb test is usually used, and the static air bomb test technology is widely used in the field of aerospace engineering. [0003] like figure 1 As shown, the existing static aeroelastic test model includes: metal main girder 1, metal wing rib 2, outrigger beam, and lightweight filling material 3. The model usually uses a straight or nearly straight metal shaft as the main beam 1 of the model. The cross-sectional shape of the main beam 1 is usually a rectangular solid cross-section, and the section stiffness of the main beam will be equal to the section stiffness required by the model. In order to maintain the shape of the wing, corresponding outrigger beams 2 are added to the m...

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Problems solved by technology

[0005] (1) Using balsa wood as a filling material, the additional rigidity is large, and the model design is not accurate

[0006] (2) Use hard foam as the filling material. The foam at the front and rear edges of the wing is easily damaged in the wind tunnel. The deformation of the foam on the windward side is inevitable, which will affect the aerodynamic force of the model in the wind tunnel

[0007] (3) Using silica gel as a filling material requires high mold requirements and high design costs

[0008] (4) The overhanging beam has a certain influence on the stiffness of the section, which reduces the accuracy of the model design

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