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Design parameter control method for transonic flutter wind tunnel model processing

A technology of control method and design parameters, applied in the field of wind tunnel test, to achieve the effect of reducing error and accurate simulation

Active Publication Date: 2021-04-06
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The purpose of this application is to provide a design parameter control method for transonic flutter wind tunnel model processing to solve at least one problem existing in the prior art

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  • Design parameter control method for transonic flutter wind tunnel model processing
  • Design parameter control method for transonic flutter wind tunnel model processing
  • Design parameter control method for transonic flutter wind tunnel model processing

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Embodiment Construction

[0028] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the figures are exemplary, and are intended to explain the present application, and should not be construed as limiting the present application. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of this application. Embodiments of the present application will be described in detail below in conjunction with th...

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Abstract

The invention belongs to the field of wind tunnel tests, and particularly relates to a design parameter control method for transonic flutter wind tunnel model processing. The method comprises the steps that a metal beam frame is adopted for manufacturing an airplane force bearing component, a first flutter wind tunnel model is generated, and a first ground resonance test is conducted on the first flutter wind tunnel model; a balancing weight is adhered to the first flutter wind tunnel model to generate a second flutter wind tunnel model, and a second ground resonance test is performed on the second flutter wind tunnel model; accessories, embedded sensors and pasted foam fillers are mounted on the second flutter wind tunnel model; a composite material skin test piece is obtained, and a material tensile test and a composite material skin test piece resonance test are performed on the composite material skin test piece; a composite material skin is laid in the mold, the second flutter wind tunnel model is put into the composite material skin for medium-temperature curing to generate a third flutter wind tunnel model, and a third ground resonance test is performed on the third flutter wind tunnel model.

Description

technical field [0001] The application belongs to the field of wind tunnel tests, and in particular relates to a design parameter control method for transonic flutter wind tunnel model processing. Background technique [0002] The transonic flutter model test is an effective means to verify the design flutter characteristics and flutter velocity margin of the aircraft in the transonic range. The tests can be used to verify and correct flutter calculation methods used in aircraft flutter calculations and transonic unsteady aerodynamics. The focus of the design of the transonic flutter model is to accurately simulate the dynamic characteristics of the real aircraft structure. Whether the structural dynamics are proportionally similar depends on the mass distribution and the stiffness distribution. Since the transonic model is composed of aluminum alloy metal beam frame, composite material skin and foam filling, it needs to be bonded through multiple medium temperature curing...

Claims

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Application Information

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IPC IPC(8): G01M9/08B64F5/60G06F30/15G06F30/20
CPCG01M9/08B64F5/60G06F30/15G06F30/20G06F2113/26G06F2119/14Y02T90/00
Inventor 胡鑫戴亚光宋恩鹏王标于佳鑫
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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