Wing tip support device for wind tunnel test

A technology of wind tunnel test and support device, which is applied in the direction of measuring device, aerodynamic test, machine/structural component test, etc. It can solve the interference of air flow, affect the reliability of test results, and cannot realize the model angle of attack and sideslip Angle changes and other issues, to improve reliability and facilitate research
CN102288381BActive Publication Date: 2013-04-17NORTHWESTERN POLYTECHNICAL UNIV
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
NORTHWESTERN POLYTECHNICAL UNIV
Publication Date
2013-04-17

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Abstract

The invention relates to a wing tip support device for wind tunnel test. The upper connecting surface and the lower connecting surface of a force measuring balance are respectively connected with a support beam top plate and a force platform, two variable attack angle mechanisms are respectively arranged at the top end of a support upright post positioned at the outer sides of two side walls of the middle part of the wind tunnel test section, passing holes of a flange spline shaft are symmetrically arranged on the wind tunnel side wall of the equal height part of the center line of the flangespline shaft of the variable attack angle mechanism, one end of the flange spline shaft passes through the passing hole arranged on the wind tunnel side wall and is positioned in a wind tunnel, the other end of the flange spline shaft is connected with the variable attack angle mechanism arranged outside the wind tunnel, two variable side slide angle mechanisms are positioned in the wind tunnel and are fixed on a flange plate arranged at the end surface of the flange spline shaft positioned in the wind tunnel through a slide plate, and slide flanges of the two variable side slide angle mechanisms are connected with the wing tip of an airplane model through a model connecting element. The wing tip support device is applicable to airplane airdrop and airborne wind tunnel test, and airplane fuselages, high lift devices and afterbody drag wind tunnel tests, and has the characteristics that the structure is simple, the use is convenient, and the test data is reliable.
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Description

technical field

[0001] The invention relates to the technical field of aircraft ground tests such as airplanes, and is an essential device for precise measurement of aircraft resistance, non-interference simulation of aircraft surface flow, and airdrop and airborne wind tunnel drop tests of aircraft. Background technique

[0002] The technology related to the present invention is the abdominal support, back support, tail support and suspension wire (tension wire) support measurement system of the wind tunnel test model. When carrying out fine measurement of aircraft resistance, airdrop and airborne wind tunnel test, aircraft fuselage, high-lift device, rear body resistance wind tunnel test research, the flow around the fuselage, the inner section of the wing (with high-lift device) and the empennage It is very important, but the above-mentioned model support methods will interfere with the flow of these components, thereby affecting the reliability of the test results; espec...

Claims

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