CN102829946A - Abdominal support mechanism suitable for high-speed wind tunnel test - Google Patents
Abdominal support mechanism suitable for high-speed wind tunnel test Download PDFInfo
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- CN102829946A CN102829946A CN2012102943985A CN201210294398A CN102829946A CN 102829946 A CN102829946 A CN 102829946A CN 2012102943985 A CN2012102943985 A CN 2012102943985A CN 201210294398 A CN201210294398 A CN 201210294398A CN 102829946 A CN102829946 A CN 102829946A
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Abstract
An abdominal support mechanism suitable for a high-speed wind tunnel test comprises a left lateral plate, a right lateral plate, a slide, a slider, a connecting plate, a reducer, a motor, a worm gear, a worm and a mounting frame and is characterized in that the slide and the slider are mounted on the left lateral plate and the right lateral plate. The left lateral plate and the right lateral plate are mounted on a bottom plate. The connecting plate, the worm gear, the worm, the reducer and the motor are all arranged in a plenum chamber. A model is connected with an abdominal support rod in the middle of an airplane body. The worm gear, the worm, the reducer and the motor are mounted on one side of a wind tunnel. The slide and the slider are mounted on two sides of the abdominal support mechanism. A chain block is mounted on the mounting frame. The abdominal support mechanism is compact in structure, provided with special fixture and easy to mount.
Description
Technical field
The invention belongs to aviation aerodynamic test technical field, especially a kind of novel abdomen supporting mechanism that is applicable to the high-speed wind tunnel test.
Background technology
Along with development in science and technology; Aerodynamic configuration is various day by day in the airplane design field, function is complete day by day, cause the direction numerous and complicated that aerodynamic force is studied; Wind tunnel test is one of main means of aerodynamic force research, and the emulation degree of test model has direct influence to test figure.There are a lot of airplane tail group profiles narrow,, must afterbody be amplified, certainly will can not simulate true aircraft configuration if use conventional tail to support.Existing abdomen props up the supporting way of (or the back of the body props up)+circular arc pole, and its rigidity is relatively poor, and desire guarantees rigidity and increase strut thickness that blockage percentage is big, all test is had adverse effect.Even some test, like jet flow, can not use tail to support; And, preferably do not use abdomen to prop up the support of (or the back of the body props up)+circular arc pole for reducing afterbody support interference.In sum, press for a kind of new supporting way of development, can take into account simulation profile and support stiffness.
Summary of the invention
A kind of novel abdomen supporting mechanism that is applicable to the high-speed wind tunnel test that The present invention be directed to deficiency of the prior art and design; This mechanism can simulated aircraft true profile; And have rigidity preferably, can improve test accuracy, and be applicable to the ventilating model test.
The technical scheme that adopts is:
A kind of abdomen supporting mechanism that is applicable to the high-speed wind tunnel test comprises left side plate, slide rail, slide block, web joint, speed reduction unit, motor, worm gear, worm screw, installation frame, and it is characterized in that: described slide rail, slide block are installed on left plate and the right plate; Left plate, right plate are installed on the base plate; Web joint, worm gear, worm screw, speed reduction unit, motor all are arranged in indoor; Model is connected with abdomen pole at the central fuselage place; Described worm gear, worm screw, speed reduction unit, motor are installed in wind-tunnel one side; Described slide rail, slide block are installed in the mechanism both sides, are equiped with chain block on the described installation frame.
Advantage of the present invention is to adopt new abdomen supporting way, can remedy the deficiency of existing supporting way, can realize 0～30 ° of the angle of attack, and the preparatory drift angle of supporting abdomen pole is different, and angle of attack scope is also different.Mechanism structure is compact, is furnished with special tooling, and convenient installation and operation can be installed in high-speed wind tunnel with this mechanism and stay in the space less between chamber and the test section.Have only abdomen pole and model in the test section, blockage percentage is little, and stiffness is better, is applicable to the model aircraft test that afterbody is narrow and small; Mechanism's center hollow can be arranged vent line, and the test model afterbody has no support to disturb, and is applicable to jet test and supports extraordinary tests such as disturbing correction, can simulate true aircraft configuration, improves the test precision.The present invention had carried out 2 groups of model tests at present, and was respond well.
Description of drawings
Fig. 1 is a structural representation of the present invention.
Fig. 2 is the A-A cut-open view of Fig. 1.
Embodiment
A kind of abdomen supporting mechanism that is applicable to the high-speed wind tunnel test comprises left side plate 10,6, slide rail 7, slide block 8, web joint 11, speed reduction unit 4, motor 5, worm gear 9, worm screw 13 and installation frame 1, and slide rail 7, slide block 8 are installed on left plate 10 and the right plate 6; Left plate 10, right plate 6 are installed on the base plate 12; Web joint 11, worm gear 9, worm screw 13, speed reduction unit 4, motor 5 etc. all in indoor, have only abdomen pole 3 and model in the test section, blockage percentage is little.Abdomen pole 3 is connected with abdomen pole 3 with model at the central fuselage place.Worm gear 9, worm screw 13, speed reduction unit 4, motor 5 are installed in wind-tunnel one side, one-sided driving.Mechanism does not have at the center other parts, can arrange vent line etc., is applicable to that jet test and support disturb extraordinary tests such as correction.Slide rail 7, slide block 8 are installed in the mechanism both sides, have guiding and carry abdomen pole and the effect of model, assurance mechanism running precision and operating steadily.This mechanism's weight is bigger, need to install by hanging device, and the installation site can not utilize existing crane in the factory building in indoor, and therefore frock 1 is installed on installation frame 14.Be equipped with chain block 2 above the frock 1, can utilized the factory building crane to be placed in the test section together frock 1 and mechanism, utilized chain block 2 again, mechanism has been installed in indoor.Shift out frock 1 after the installation.
Claims (1)
1. an abdomen supporting mechanism that is applicable to the high-speed wind tunnel test comprises left side plate, slide rail, slide block, web joint, speed reduction unit, motor, worm gear, worm screw, installation frame, and it is characterized in that: described slide rail, slide block are installed on left plate and the right plate; Left plate, right plate are installed on the base plate; Web joint, worm gear, worm screw, speed reduction unit, motor all are arranged in indoor; Model is connected with abdomen pole at the central fuselage place; Described worm gear, worm screw, speed reduction unit, motor are installed in wind-tunnel one side; Described slide rail, slide block are installed in the mechanism both sides, are equiped with chain block on the described installation frame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210294398.5A CN102829946B (en) | 2012-08-20 | 2012-08-20 | A kind of abdomen supporting mechanism being applicable to high wind tunnel testing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210294398.5A CN102829946B (en) | 2012-08-20 | 2012-08-20 | A kind of abdomen supporting mechanism being applicable to high wind tunnel testing |
Publications (2)
| Publication Number | Publication Date |
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| CN102829946A true CN102829946A (en) | 2012-12-19 |
| CN102829946B CN102829946B (en) | 2015-08-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201210294398.5A Expired - Fee Related CN102829946B (en) | 2012-08-20 | 2012-08-20 | A kind of abdomen supporting mechanism being applicable to high wind tunnel testing |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103048111A (en) * | 2012-12-28 | 2013-04-17 | 中国航空工业空气动力研究院 | Ventral strut |
| CN105258915A (en) * | 2015-11-18 | 2016-01-20 | 中国空气动力研究与发展中心高速空气动力研究所 | Sideslip angle-varying blade belly supporting device in high-speed wind tunnel test |
| CN105258916A (en) * | 2015-11-18 | 2016-01-20 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for correcting influence of high-speed wind tunnel model afterbody distortion on lateral-directional aerodynamic characteristics |
| CN107621349A (en) * | 2017-08-29 | 2018-01-23 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of wind-tunnel half model varied angle mechanism |
| CN107631855A (en) * | 2017-09-01 | 2018-01-26 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of model that a variety of supporting way can be achieved |
| CN112014063A (en) * | 2020-11-02 | 2020-12-01 | 中国空气动力研究与发展中心低速空气动力研究所 | A stores pylon for wind-tunnel test |
| CN114166457A (en) * | 2021-11-24 | 2022-03-11 | 厦门理工学院 | Wind-proof mounting component for wind tunnel laboratory |
| CN115326350A (en) * | 2022-10-14 | 2022-11-11 | 中国空气动力研究与发展中心高速空气动力研究所 | Motor-driven wind tunnel jet flow test equivalent simulation device and application method thereof |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103048111A (en) * | 2012-12-28 | 2013-04-17 | 中国航空工业空气动力研究院 | Ventral strut |
| CN105258915A (en) * | 2015-11-18 | 2016-01-20 | 中国空气动力研究与发展中心高速空气动力研究所 | Sideslip angle-varying blade belly supporting device in high-speed wind tunnel test |
| CN105258916A (en) * | 2015-11-18 | 2016-01-20 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for correcting influence of high-speed wind tunnel model afterbody distortion on lateral-directional aerodynamic characteristics |
| CN105258916B (en) * | 2015-11-18 | 2017-09-01 | 中国空气动力研究与发展中心高速空气动力研究所 | The modification method that body distortion influences on horizontal course aerodynamic characteristic after a kind of high-speed wind tunnel model |
| CN105258915B (en) * | 2015-11-18 | 2017-09-29 | 中国空气动力研究与发展中心高速空气动力研究所 | Become yaw angle blade belly stay device in a kind of high-speed wind tunnel |
| CN107621349A (en) * | 2017-08-29 | 2018-01-23 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of wind-tunnel half model varied angle mechanism |
| CN107621349B (en) * | 2017-08-29 | 2024-04-12 | 中国航空工业集团公司沈阳空气动力研究所 | Wind tunnel half-mode angle-changing mechanism |
| CN107631855A (en) * | 2017-09-01 | 2018-01-26 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of model that a variety of supporting way can be achieved |
| CN112014063A (en) * | 2020-11-02 | 2020-12-01 | 中国空气动力研究与发展中心低速空气动力研究所 | A stores pylon for wind-tunnel test |
| CN114166457A (en) * | 2021-11-24 | 2022-03-11 | 厦门理工学院 | Wind-proof mounting component for wind tunnel laboratory |
| CN114166457B (en) * | 2021-11-24 | 2023-05-23 | 厦门理工学院 | Wind tunnel laboratory is with preventing wind installation component |
| CN115326350A (en) * | 2022-10-14 | 2022-11-11 | 中国空气动力研究与发展中心高速空气动力研究所 | Motor-driven wind tunnel jet flow test equivalent simulation device and application method thereof |
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| CN102829946B (en) | 2015-08-19 |
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