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Longitudinal freedom degree simulation full aircraft flutter wind tunnel model support system

A support system and flutter model technology, applied in the testing of machines/structural components, measuring devices, instruments, etc., can solve problems such as difficult to meet the support frequency, inapplicable flutter active control, load mitigation, etc., to ensure safety Effect

Active Publication Date: 2016-08-10
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

In the prior art, the model support system usually adopts a spring suspension system and a double-cable suspension system, but when the first-order natural frequency of the model is very low, it is difficult to meet the requirements of the support frequency, and it is not suitable for active control of flutter and load mitigation Wait for the test

Method used

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  • Longitudinal freedom degree simulation full aircraft flutter wind tunnel model support system
  • Longitudinal freedom degree simulation full aircraft flutter wind tunnel model support system
  • Longitudinal freedom degree simulation full aircraft flutter wind tunnel model support system

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Embodiment Construction

[0036] 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. 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 invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...

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Abstract

The invention relates to a longitudinal freedom degree simulation full aircraft flutter wind tunnel model support system and belongs to the technical field of aeroelasticity tests. The longitudinal freedom degree simulation full aircraft flutter wind tunnel model support system comprises a support beam rack and a model suspension device, wherein the model suspension device is arranged on the support beam rack and is used for suspending a flutter model, a model suspension device can be arranged on a main beam rack in a sliding manner, and displacement of the model suspension device along an axis of the main beam rack can be restricted via an ups and downs brake block arranged on a lateral part of the model suspension device; the model suspension device also comprises a pitching brake block and a model suspension shaft, the model suspension shaft is used for suspending the flutter model so as to make the flutter model rotate around the model suspension shaft, the pitching brake block can press tightly on or get away from the flutter model, and therefore pitching angle displacement of the model suspension device can be restricted. According to the longitudinal freedom degree simulation full aircraft flutter wind tunnel model support system, freedom of a full aircraft flutter in an up and down direction and a pitching direction in a wind tunnel can be realized via the ups and downs brake block and the pitching brake block, and therefore a real flight state of an aircraft can be simulated.

Description

technical field [0001] The invention belongs to the technical field of aeroelasticity test, and in particular relates to a whole machine flutter wind tunnel model support system for simulating longitudinal degrees of freedom. Background technique [0002] When the flight reaches a certain speed, due to the interaction of aerodynamic and structural elastic vibrations, the aircraft will undergo a self-excited vibration called flutter, most of which will cause disastrous consequences. For example, the wings and tail of an airplane break down in seconds. This prompted the aeronautical engineering community to first carry out theoretical and experimental research on flutter, and this work was listed as an important link in the aircraft design work. [0003] The wind tunnel test of the full-aircraft flutter model generally adopts the support of multi-degree-of-freedom direction movement. In addition to supporting the aircraft model, this support should also ensure that the aircra...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/04G01M9/08
CPCG01M9/04G01M9/08
Inventor 陈海党云卿黄国宁李俊杰胡志勇
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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