Elastic gust response wind tunnel test device

A wind tunnel test and gust technology, applied in the direction of measuring devices, aerodynamic tests, machine/structural component testing, etc., can solve problems such as unsatisfactory gust response tests, inability to simulate elastic conditions, and single model support methods

Active Publication Date: 2020-03-17
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

[0004] In order to solve the above technical problems, the embodiment of the present invention provides an elastic gust response wind tunnel test device to solve the existing rigid model form of the gust re

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  • Elastic gust response wind tunnel test device

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Embodiment Construction

[0026] In order to make the purpose, technical solution and advantages of the present invention more clear, the embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings. It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined arbitrarily with each other.

[0027] The following specific embodiments provided by the present invention can be combined with each other, and the same or similar concepts or processes may not be repeated in some embodiments.

[0028] figure 1 It is a schematic structural diagram of an elastic gust response wind tunnel test device provided by an embodiment of the present invention. The elastic gust response wind tunnel test device provided in this embodiment may include: a wing 1 , an adapter 2 , a wing connection 3 and a test support 4 .

[0029] Such as figure 2 As shown, it is a schematic structura...

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Abstract

The embodiment of the invention discloses an elastic gust response wind tunnel test device, which comprises wings, an adapter piece, a wing connecting piece and a test supporting piece, and is characterized in that the test supporting piece comprises a guide rail, supporting bases arranged at the two ends of the guide rail respectively, and a sliding assembly nested on the guide rail. The wings comprise a left wing and a right wing which are symmetrically arranged; the adapter piece comprises a left wing adapting piece and a right wing adapting piece; the left wing is arranged at one side of the wing connecting piece through the left wing adapting piece, and the right wing is arranged at the other side of the wing connecting piece through the right wing adapting piece, the wing connectingpieces and the adapting pieces are connected to the outer portion of the sliding assembly in a sleeving mode; and the wings are driven to move through sliding of the sliding assembly in the axial direction of the guide rail. According to the embodiment of the invention, the problems that an existing gust response model in a rigid model form cannot simulate the elasticity condition in a gust response test, the model support mode is single, and gust response tests under various boundary conditions cannot be met are solved.

Description

technical field [0001] The present application relates to but is not limited to the technical field of aeroelasticity test, especially an elastic gust response wind tunnel test device. Background technique [0002] During the flight (especially for large aircraft), when encountering gusts of wind during the flight, the aircraft will produce a large response, which will bring safety hazards to the aircraft structure and passengers. Significance. [0003] Since the current gust response model is mainly a rigid model, and the elastic deformation of large aircraft is large during flight, the above rigid model does not consider the elastic effect; and the support method of the model is single, which cannot meet the gust response test under various boundary conditions. Contents of the invention [0004] In order to solve the above technical problems, the embodiment of the present invention provides an elastic gust response wind tunnel test device to solve the existing rigid mod...

Claims

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Application Information

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IPC IPC(8): G01M9/00G01M9/04
CPCG01M9/00G01M9/04
Inventor 张庚庚霍应元蒲利东罗务揆曾宪昂魏巍
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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