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Elastic supports for flutter wind tunnel models

An elastic support, wind tunnel technology, applied in the testing of machine/structural components, instruments, measuring devices, etc., can solve the problems of difficult design requirements of the control surface, low rotation frequency, small moment of inertia, etc., and reduce the rotation frequency of the control surface. , the effect of reducing difficulty and simple structure

Active Publication Date: 2019-09-27
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, its rigidity is relatively high, and in a limited design space, it is difficult to meet the design requirements for control surfaces with light weight, small moment of inertia and low rotation frequency.

Method used

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  • Elastic supports for flutter wind tunnel models
  • Elastic supports for flutter wind tunnel models
  • Elastic supports for flutter wind tunnel models

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Embodiment Construction

[0022] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention.

[0023] The present invention designs an elastic supporting part, which is used for the connection between the flutter model control surface and the stabilizer surface, so that it can provide support stiffness with lower rotation frequency for the control surface with light weight and small moment of inertia.

[0024] refer to figure 1 The shown elastic support for the flutter wind tunnel model of the present invention includes a first mount 1, a second mount 2 and a flexible part 3, the flexible part 3 is an annular structure with an opening, and the first mount 1 The first mounting seat 1, the second mounting seat 2 and the flexible part 3 are designed in one piece, and the first mount...

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Abstract

The invention relates to an elastic supporter for a flutter wind tunnel model and belongs to the airplane flutter test technology field. The supporter comprises a first mounting seat, a second mounting seat and a flexible portion, wherein the flexible portion is an annular structure with openings, the first mounting seat and the second mounting seat are arranged at the two openings, the first mounting seat, the second mounting seat and the flexible portion are in an integrated design mode, and the first mounting seat and the second mounting seat are respectively fixed on a stabilization surface and a control surface of the flutter wind tunnel model. The supporter is advantaged in that a control surface supporter with relatively low supporting rigidity can be designed in the limited space,good structural strength is realized, the control surface rotation frequency can be substantially reduced, rotation frequency design and test requirements of the control surface can be satisfied, andmodel design difficulty is reduced.

Description

technical field [0001] The invention belongs to the technical field of aircraft structure tests, and in particular relates to a design method for a split cabin door. Background technique [0002] Flutter is an aeroelastic instability phenomenon caused by the coupling of the natural vibration mode and aerodynamic force of the wing surface during flight. It is necessary to determine whether the flutter boundary meets the requirements of the flight envelope through simulation calculations and wind tunnel tests. . For airfoils with control surfaces (such as rudder, flaps, ailerons, etc.), usually the mode of the control surface will also participate in the flutter, even the critical flutter mode. Therefore, in the flutter It is necessary to accurately simulate the rotational frequency of the control surface during the wind tunnel test. [0003] In the design of the flutter model, springs or springs are used to provide the support stiffness of the control surface, and the rotat...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/00
Inventor 脱朝智胡鑫胡家亮于佳鑫柏楠赵飞宇
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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