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A Test Mechanism for Changing the Model's Average Angle of Attack in Real Time

An average and angle-of-attack technology, applied in the high-speed wind tunnel test technology and the field of aircraft flight mechanics, can solve the problems of damaged model balances, damaged support mechanisms, etc., and achieve the effects of small structural damage, reduced startup times, and improved utilization.

Active Publication Date: 2021-03-26
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

When the model has a preset angle of attack, the situation will be more severe. In severe cases, it will damage the balance of the model, or even damage the entire support mechanism

Method used

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  • A Test Mechanism for Changing the Model's Average Angle of Attack in Real Time
  • A Test Mechanism for Changing the Model's Average Angle of Attack in Real Time
  • A Test Mechanism for Changing the Model's Average Angle of Attack in Real Time

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Embodiment Construction

[0024] Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided for more thorough understanding of the present disclosure and to fully convey the scope of the present disclosure to those skilled in the art. It should be noted that, in the case of no conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0025] figure 1 It is a schematic diagram of the test mechanism for changing the average angle of attack of the model in real time provided by the embodiment...

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Abstract

The invention discloses a test mechanism capable of changing the average incidence angle of a model in real time. The mechanism comprises a pitch oscillation mechanism, an upper seat plate, a supportcross beam, a linear guide rail, a linear guide rail sliding block, a guide rail seat, a straight rack, an average incidence angle drive motor, a gear, a sinusoidal generator base, an arc rack, an arcguide rail, and an arc guide rail sliding block. The linear guide rail sliding block and the bottom of the support cross beam are fixedly connected. The linear guide rail is arranged at the linear guide rail sliding block in a communication manner; the guide rail set and the linear guide rail are connected; the straight rack is connected to the bottom of the guide rail seat; one end of the straight rack is engaged with the gear connected with the average incidence angle drive motor; the arc guide rail sliding block is arranged on the inner side wall of the sinusoidal generator base; the arc guide rail is arranged at the arc guide rail sliding block in a communication manner; the arc rack is arranged on the outer side wall of the sinusoidal generator base and is engaged with the other endof the straight rack; and the arc guide rail and the upper seat plate are connected. Therefore, the measurement of dynamic aerodynamic characteristics in a pitch oscillation state in which the averageincidence angle of the aircraft changes in real time is realized.

Description

technical field [0001] The invention belongs to the technical fields of high-speed wind tunnel test technology and aircraft flight mechanics, and in particular relates to a test mechanism for changing the average angle of attack of a model in real time. Background technique [0002] With the development of aerospace technology, modern fighter jets require high maneuverability, so the unsteady aerodynamic characteristics of the aircraft at high angles of attack are crucial. Current theoretical calculations can't solve this kind of problems well, and its research methods mainly rely on wind tunnel experiment simulation. [0003] In existing high-speed wind tunnels, the pitching oscillation test mechanism for unsteady aerodynamic research at high angles of attack of aircraft has an average angle of attack preset before the test, and the model already has an angle of attack before the wind tunnel is started. However, the airflow in the temporary super wind tunnel is extremely u...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/06
CPCG01M9/06
Inventor 魏忠武张晨凯金佳林杨辉董金刚谢峰李广良
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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