A Test Mechanism for Quickly Changing Model Attitude Angle

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.

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 ...

AI Technical Summary

Problems solved by technology

When the mechanism is running, the beam of the π-shaped bracket will swing up and down at high speed around the center of rotation in the wind tunnel, and its motion direction is basically perpendicular to the airflow direction. In the high-speed wind tunnel test, it interferes a lot with the test; high-speed wind During the tunnel test, the air velocity is high, and the load of the mechanism in the wind tunnel flow field is large. Due to the weak stiffness of the π-shaped support, the angle of the model attitude will be distorted during high-speed swing. The influence of aerodynamic force is coupled in the test, and the angle distortion It cannot be corrected, which will cause errors in the experimental data

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