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Wind tunnel experiment system for free flight model

A technology for wind tunnel experiments and models, applied in the field of aircraft wind tunnel experiments, can solve the problems of limited versatility, difficult to achieve quantitative analysis, and high cost

Inactive Publication Date: 2012-01-04
BEIHANG UNIV
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  • Abstract
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  • Application Information

AI Technical Summary

Problems solved by technology

In the wind tunnel experiments of some flutter models, the "free-free" state of the model is realized by elastic suspension, but because the attitude of the model cannot be controlled, and it is not suitable to arrange measurement equipment, etc., only qualitative analysis of the flutter mechanism can be done, which is very difficult. Difficult to meet the requirements of quantitative analysis
The flight test can complete the verification and exploration of various technologies in the "free-free" state of the aircraft, but its versatility is limited due to its high cost

Method used

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  • Wind tunnel experiment system for free flight model
  • Wind tunnel experiment system for free flight model
  • Wind tunnel experiment system for free flight model

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Embodiment Construction

[0019] The specific implementation manners of the present invention will be described below in conjunction with the accompanying drawings.

[0020] figure 1 Shown is a schematic diagram of a free-flying model wind tunnel experiment system according to an embodiment of the present invention, which includes an aircraft wind tunnel experiment model (10), a stability control system (11) and a support system (5).

[0021] Such as figure 2 As shown, the support system (5) includes a linear slide rail (18), a platform (23) and a bearing (17). Among them, the linear slide rail (18) realizes the moving pair (25) for simulating the ups and downs of the wind tunnel test model (10); the bearing (17) realizes the rotating pair for simulating the pitching movement of the wind tunnel test model (10) The platform (23) is connected with the linear slide rail (18) and the bearing (17), in order to simulate the true state of the wind tunnel experiment model (10) vertically free to fly.

[00...

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Abstract

The invention provides a wind tunnel experiment system for an aircraft, which is used for wind tunnel experiments of free flight models and can simulate a real state of an airplane lengthways and freely flying. The system comprises a wind tunnel experiment model for the aircraft, a stability control system and a support system, wherein the stability control system is connected with the wind tunnel experiment model through a signal line, and is used for receiving built-in sensor signals of the model and outputting control surface deflection signals through corresponding control operation. Therefore, various wind tunnel experiment researches on the aircrafts (such as wind tunnel experiment researches on flutter models, wind tunnel experiment researches on full aircraft flight mechanics, wind tunnel experiment researches on full aircraft gust alleviation, wind tunnel experiment researches on full aircraft control augmentation stability systems and the like) can be realized.

Description

technical field [0001] The patent of the present invention relates to a free-flying model wind tunnel experiment system, which can realize wind tunnel experiments under the "free-free" constraint conditions of individual component models and full-machine models, and belongs to the field of aircraft wind tunnel experiments, especially large-scale aircraft model wind tunnels Free flight experiment. Background technique [0002] The design and manufacture of aircraft must rely on various professional technologies, which belongs to the high-tech field. For the verification and exploration of technology, it must rely on various experiments to complete, and wind tunnel experiments are an indispensable part of it. Through wind tunnel experiments, the verification of aircraft control technology, the selection of design solutions, and the exploration of new aerodynamic layouts can be completed. Most of the traditional aircraft wind tunnel experiments are full-aircraft force and pre...

Claims

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Application Information

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IPC IPC(8): G01M9/02G01M9/04
Inventor 吴志刚王立波沈龙陈磊杨超
Owner BEIHANG UNIV
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