Optimal scaling modeling method of aeroelasticity wind-tunnel model of composite material wing

A technology of aeroelasticity and modeling method, which is applied in the field of structure and test of aeronautical vehicles, and can solve problems such as difficulty in establishing scale models under similar conditions

Inactive Publication Date: 2014-03-26
BEIHANG UNIV +1
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Problems solved by technology

Strict similarity conditions and differences from the origina

Method used

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  • Optimal scaling modeling method of aeroelasticity wind-tunnel model of composite material wing
  • Optimal scaling modeling method of aeroelasticity wind-tunnel model of composite material wing
  • Optimal scaling modeling method of aeroelasticity wind-tunnel model of composite material wing

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Embodiment Construction

[0016] The wind tunnel test is carried out according to the principle of relativity and similarity.

[0017] The basis of the aeroelastic model test is the similarity law of aeroelastic scaling. For different aeroelastic phenomena, the corresponding similarity law can be obtained through the similarity transformation of the motion equation. The speed and dither frequency can then be determined. There are many similar proportions k between the model and the real object. For the aeroelastic model, the low-speed test takes k l ,k V ,k ρ For the basic similarity ratio, take k for the high-speed test l ,k q ,k ρ are basically similar proportions, where l, V, q, ρ represent length, velocity, velocity pressure and density respectively.

[0018] The aeroelastic scaling modeling is to reconstruct the aeroelastic characteristics of the original structure on the scaling model based on the similarity criterion. Since the aerodynamic shape remains similar, the problem is viewed as...

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Abstract

The invention provides a scaling modeling method based on aeroelasticity constraints. The method includes the steps that (A) an aerodynamic force analytical model and a structure finite element model are established according to a standard wing model; (B) a structure flutter analytical model is established according to the aerodynamic force analytical model and the structure finite element model; (C) the flutter characteristic of the model is solved according to a boundary condition; (D) whether the flutter characteristic meets a predetermined requirement or not is judged according to a predetermined constraint condition. The scaling modeling method has the advantages that in the wind-tunnel scaling modeling method of a composite material wing, the dynamics constraint, the pitch line constraint and the flutter constraint are comprehensively considered, the flutter model is optimally obtained, and thus the dynamics and flutter characteristic of a true structure can be better simulated; by optimal modeling of a low speed and high subsonic speed flutter model, flutter scaling modeling procedures based on an optimization method are respectively established, the modeling efficiency can be improved, the model can be made to well reflect the aeroelasticity characteristic of an entity, and the method is applicable to aeroelasticity wind-tunnel modeling of civil aircraft composite material wings.

Description

technical field [0001] The invention relates to a scaling modeling method of an aeroelastic wind tunnel model of a composite material wing of a civil aircraft, and belongs to the field of structures and tests of aviation vehicles. Background technique [0002] The development of each aircraft model must go through theoretical calculations and wind tunnel tests to obtain the flutter data of the model. Due to the limitations of wind tunnel scale and cost technology, it is impossible to conduct full-scale model tests. Therefore, the original model must be scaled down and manufactured with suitable materials, and then the blowing test must be carried out. Therefore, the establishment and manufacture of the scaled model is the key to solving the problem. The flutter wind tunnel model is generally made of metal materials. Since metal is an isotropic material, its mechanical properties are relatively simple and its processing accuracy is high. Therefore, it is relatively mature to...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCY02T90/00
Inventor 杨超王斌团刘超丁未龙孙晓红万志强
Owner BEIHANG UNIV
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