Aircraft aerodynamic characteristics measurement test device and test method simulating intake flow

By using the "tail support + lift" support method and orbital transmission in large continuous wind tunnels, the precise simulation of the flow of the aircraft intake channel is achieved, solving the problems of measurement data accuracy and support interference in the prior art, and improving the reliability of aerodynamic characteristics measurement.

CN119269010BActive Publication Date: 2025-03-25INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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Patent Information

Application Number
CN202411826827.8
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2024-12-12
Publication Date
2025-03-25
Estimated Expiration
2044-12-12

AI Technical Summary

Technical Problem

In large continuous wind tunnels, it is difficult for the prior art to accurately simulate intake air flow, which affects the accuracy of the aircraft aerodynamic characteristics measurement data, and the support system has a great interference with the surface flow of the ventilation model.

Method used

The aircraft aerodynamic characteristics measurement test device and method that simulates the intake airflow, including a support device, a variable side sliding angle device and a measuring device, is adopted. Through the "tail support + lift" support method, combined with orbital transmission and telescopic sleeve, the side sliding angle of the ventilation model is continuously adjustable and the flexible compensation of the airflow pipeline.

Benefits of technology

It realizes accurate simulation of the intake duct flow of the aircraft, reduces the interference of the downstream flow of the intake duct to the upstream flow, improves the reliability of measurement data, and supports the measurement of aerodynamic characteristics of large aircraft.

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Abstract

The present invention belongs to the technical field of wind tunnel tests, and discloses an aircraft aerodynamic characteristic measurement test device and a test method for simulating intake flow. The ventilation model of the test device is installed on the upper part of the tail support bracket through a balance bellows and a ventilation strut. A variable sideslip angle device is installed between the rear section of the tail support bracket and the mounting platform. Measuring devices such as a flow meter and an ejector are fixed on the mounting platform. The rear end of the mounting platform is fixedly connected to the scimitar mechanism of the wind tunnel; the variable sideslip angle device changes the sideslip angle of the ventilation model. The test method includes wind tunnel test preparation; conducting wind tunnel tests; and test data processing. The present invention adopts a "tail support + lifting" support method to achieve a perfect combination of the test system and the support system; a hollow telescopic sleeve with ball joints at both ends is used to achieve compensation for changes in the length and angle of the airflow pipeline caused by the sideslip angle deflection, providing a solution for accurate simulation of intake flow in large-scale continuous high-speed wind tunnels, and has engineering practical value.
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