A wingtip support device for wind tunnel test

A technology of wind tunnel test and support device, which is used in measurement devices, aerodynamic tests, and testing of machine/structural components, etc., can solve the disturbance of airflow flow, affect the reliability of test results, and cannot achieve model angle of attack and sideslip angle change and other issues, to facilitate research and improve reliability.

Active Publication Date: 2011-12-21
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In order to overcome the problems existing in the prior art or interfere with the flow of the airflow, thereby affecting the reliability of the test results, or the change of the angle of attack and sideslip a

Method used

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  • A wingtip support device for wind tunnel test
  • A wingtip support device for wind tunnel test
  • A wingtip support device for wind tunnel test

Examples

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Embodiment Construction

[0027] This embodiment is an aircraft model wingtip support device. It can not only be used to measure the aerodynamic force of the aircraft model in the wind tunnel, but also use the delivery mechanism to drop the airdrop model from the hollow aircraft model, and use the camera to record the trajectory of the airdrop model.

[0028] This embodiment includes a force-measuring balance 1 , a single-component resistance balance 10 , a force platform 11 , a support beam 2 , a support column 3 , a mechanism for changing the angle of attack 4 , a mechanism for changing the angle of sideslip 6 and a model connector 7 . Variable angle of attack mechanism 4 consists of motor 12, reducer 13, gear pair 14, worm screw 15, turbine 16, internal spline shaft 19, turbine bearing 20, turbine bearing seat 21, flange spline shaft 5, worm bearing 18, worm bearing Seat 17 and some screws are formed; Variable side slip angle mechanism 6 is made up of slide plate 22, sliding flange 23, bearing pin 2...

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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.

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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Application Information

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IPC IPC(8): G01M9/08
Inventor 焦予秦张彬乾解亚军惠增宏肖春生金承信
Owner NORTHWESTERN POLYTECHNICAL UNIV
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