Test mechanism for rapidly changing model attitude angle

A model attitude and fast technology, applied in aerodynamic tests, machine/structural component testing, measuring devices, etc., can solve problems such as angle distortion that cannot be corrected, model attitude angle distortion, and weak stiffness of π-shaped brackets, etc., to achieve The effect of convenient amplitude adjustment, small structural damage, and small structural dependence
CN110207935AActive Publication Date: 2019-09-06CHINA ACAD OF AEROSPACE AERODYNAMICS
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Patent Information

Authority / Receiving Office
CN · China
Current Assignee / Owner
CHINA ACAD OF AEROSPACE AERODYNAMICS
Publication Date
2019-09-06

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Abstract

The invention discloses a test mechanism for rapidly changing a model attitude angle. The test mechanism for rapidly changing the model attitude angle comprises a connecting cover plate and a lower connecting seat connected to a wind tunnel test section shell, a bent blade mechanism fixedly connected between the connecting cover plate and the lower connecting seat, an arc guide rail fixedly connected to the side of the bent blade mechanism, a guide rod fixedly connected to the test section shell by a connecting device behind the bent blade mechanism, a sinusoidal generator and a drive motor connected to the connecting cover plate, an upper swing lever connected to the lower side of the connecting cover plate, a push rod mounted on the guide rod, a lower swing lever connected to the arc guide rail, and a strut, a measuring balance and a model connected to the end of the lower swing lever. According to the invention, large pitching oscillation of the aircraft model can be realized by motor driving; the dynamic aerodynamic characteristics of the large pitching oscillation state of the aircraft can be measured by the measuring balance, so as to meet the test requirements of the high-speed wind tunnel; and the test mechanism for rapidly changing the model attitude angle has the characteristics of small snapback characteristics, convenient amplitude adjustment, high positioning accuracy, small support interference and the like.
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Description

technical field

[0001] The invention relates to a test mechanism for changing the attitude angle of a model, which is used for the unsteady wind tunnel test of a large angle of attack of an aerospace vehicle, and belongs to the field of high-speed wind tunnel test technology and aircraft flight mechanics. 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] From the domestic research on dynamic test technology of aircraft in the 1980s, a pitching oscillation test mechanism was established in the low-speed wind tunnel and high-speed wind tunnel.

[0004] Figure 5 It is a pitching oscillation test mechanism of a high-speed wind tunnel. The mechanism is ...

Claims

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