CN102829946B - A kind of abdomen supporting mechanism being applicable to high wind tunnel testing - Google Patents
A kind of abdomen supporting mechanism being applicable to high wind tunnel testing Download PDFInfo
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- CN102829946B CN102829946B CN201210294398.5A CN201210294398A CN102829946B CN 102829946 B CN102829946 B CN 102829946B CN 201210294398 A CN201210294398 A CN 201210294398A CN 102829946 B CN102829946 B CN 102829946B
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- abdomen
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- speed reduction
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- reduction unit
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- 238000012360 testing method Methods 0.000 title claims abstract description 29
- 210000001015 abdomen Anatomy 0.000 title claims abstract description 22
- 238000009434 installation Methods 0.000 claims abstract description 10
- 238000004088 simulation Methods 0.000 description 3
- 238000012937 correction Methods 0.000 description 2
- 230000007812 deficiency Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 238000004064 recycling Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
Be applicable to an abdomen supporting mechanism for high wind tunnel testing, comprise left side plate, slide rail, slide block, web joint, speed reduction unit, motor, worm gear, worm screw, installation frame, it is characterized in that: described slide rail, slide block are arranged on left plate and right plate; Left plate, right plate are arranged on base plate; Web joint, worm gear, worm screw, speed reduction unit, motor are all arranged on stays indoor, model is connected with abdomen pole at central fuselage place, described worm gear, worm screw, speed reduction unit, motor are installed in wind-tunnel side, described slide rail, slide block are installed in mechanism both sides, and described installation frame is equiped with chain block.The present invention has compact conformation, is equipped with special tooling, is easy to install.
Description
Technical field
The invention belongs to aviation aerodynamic test technical field, especially a kind of novel abdomen supporting mechanism being applicable to high wind tunnel testing.
Background technology
Along with development in science and technology, the direction numerous and complicated day by day various at field of airplane design aerodynamic configuration, function is day by day complete, initiation aerodynamic force is studied, wind tunnel test is one of Main Means of aerodynamic force research, and the emulator of test model has direct impact to test figure.Have a lot of airplane tail group profile narrow, if use conventional tail to support, afterbody must be amplified, being bound to can not Reality simulation aircraft configuration.The supporting way of existing abdomen props up (or the back of the body)+circular arc pole, its rigidity is poor, increases strut thickness for ensureing rigidity, and blockage percentage is large, all has adverse effect to test.Even some test, as jet flow, can not use tail to support; And for reducing tail support interference, preferably do not use abdomen to prop up the support of (or back of the body)+circular arc pole.In sum, in the urgent need to developing a kind of new supporting way, simulation profile and support stiffness can be taken into account.
Summary of the invention
The present invention be directed to deficiency of the prior art and a kind of novel abdomen supporting mechanism being applicable to high wind tunnel testing designed, this mechanism can the true profile of simulated aircraft, and there is good rigidity, can test accuracy be improved, and be applicable to ventilating model test.
The technical scheme adopted is:
Be applicable to an abdomen supporting mechanism for high wind tunnel testing, comprise left side plate, slide rail, slide block, web joint, speed reduction unit, motor, worm gear, worm screw, installation frame, it is characterized in that: described slide rail, slide block are arranged on left plate and right plate; Left plate, right plate are arranged on base plate; Web joint, worm gear, worm screw, speed reduction unit, motor are all arranged on stays indoor, model is connected with abdomen pole at central fuselage place, described worm gear, worm screw, speed reduction unit, motor are installed in wind-tunnel side, described slide rail, slide block are installed in mechanism both sides, and described installation frame is equiped with chain block.
Advantage of the present invention adopts new abdomen supporting way, can make up the deficiency of existing supporting way, can realize the angle of attack 0 ~ 30 °, and the pre-drift angle of supporting abdomen pole is different, and range of angles of attack is also different.Mechanism structure is compact, is furnished with special tooling, installs easy to operate, this mechanism can be arranged on high-speed wind tunnel and stay in space less between room and test section.Only have abdomen pole and model in 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 arrange vent line, and test model afterbody, without any support interference, is applicable to the special test such as jet test and support interference correction, can Reality simulation aircraft configuration, improves test precision.The present invention had now carried out 2 groups of model tests, respond well.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Fig. 2 is the A-A cut-open view of Fig. 1.
Embodiment
Be applicable to an abdomen supporting mechanism for high wind tunnel testing, comprise 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, slide rail 7, slide block 8 are arranged on left plate 10 and right plate 6; Left plate 10, right plate 6 are arranged on base plate 12; Web joint 11, worm gear 9, worm screw 13, speed reduction unit 4, motor 5 etc. are all staying indoor, and only have abdomen pole 3 and model in test section, blockage percentage is little.Abdomen pole 3 and model are connected with abdomen pole 3 at central fuselage place.Worm gear 9, worm screw 13, speed reduction unit 4, motor 5 are arranged on wind-tunnel side, one-sided driving.Vent line etc., without other parts, can be arranged in mechanism center, is applicable to the special test such as jet test and support interferences correction.Slide rail 7, slide block 8 are arranged on mechanism both sides, have guiding and carrying abdomen pole and the effect of model, assurance mechanism running precision and operating steadily.This mechanism's weight is comparatively large, need install by hanging device, and indoor are being stayed in installation site, can not utilize existing crane in factory building, therefore on installation frame 14, be provided with frock 1.Frock 1 is equipped with chain block 2 above, can factory building crane be utilized together to be placed in test section frock 1 and mechanism, and recycling chain block 2, is arranged on mechanism and stays indoor.Frock 1 is shifted out after installation.
Claims (1)
1. one kind is applicable to the abdomen supporting mechanism of high wind tunnel testing, comprise left plate (10), right plate (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), it is characterized in that: described slide rail (7), slide block (8) are arranged on left plate (10) and right plate (6); Left plate (10), right plate (6) are arranged on base plate (12); Web joint (11), worm gear (9), worm screw (13), speed reduction unit (4), motor (5) all staying indoor, only have abdomen pole (3) and model in test section, abdomen pole (3) and model are connected with abdomen pole (3) at central fuselage place; Worm gear (9), worm screw (13), speed reduction unit (4), motor (5) are arranged on wind-tunnel side, one-sided driving; Mechanism center is without other parts, and arrange vent line, slide rail (7), slide block (8) are arranged on mechanism both sides; Installation frame (1) is provided with frock; Chain block (2) is equipped with above frock.
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 |
|---|---|
| CN102829946A CN102829946A (en) | 2012-12-19 |
| CN102829946B true CN102829946B (en) | 2015-08-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| 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 |
Country Status (1)
| Country | Link |
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| CN (1) | CN102829946B (en) |
Families Citing this family (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 |
| 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 |
| 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 |
| 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 |
| CN112014063B (en) * | 2020-11-02 | 2021-07-16 | 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 |
| CN114166457B (en) * | 2021-11-24 | 2023-05-23 | 厦门理工学院 | Wind tunnel laboratory is with preventing wind installation component |
| CN115326350B (en) * | 2022-10-14 | 2022-12-27 | 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 test equivalent simulation device and application method thereof |
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| US4658635A (en) * | 1985-03-13 | 1987-04-21 | Deutsche Forschungs- Und Versuchsanstalt | Simulator for aerodynamic investigations of models in a wind tunnel |
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| CN102288381A (en) * | 2011-05-05 | 2011-12-21 | 西北工业大学 | Wing tip support device for wind tunnel test |
| CN102494866A (en) * | 2011-12-13 | 2012-06-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Framework-type support component for wind tunnel test model |
| CN202853876U (en) * | 2012-08-24 | 2013-04-03 | 中国航空工业集团公司沈阳空气动力研究所 | Belly-supporting mechanism applicable to high speed wind tunnel experiments |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05322692A (en) * | 1992-05-26 | 1993-12-07 | Mitsubishi Heavy Ind Ltd | Wind tunnel test device |
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2012
- 2012-08-20 CN CN201210294398.5A patent/CN102829946B/en not_active Expired - Fee Related
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| GB820061A (en) * | 1957-04-09 | 1959-09-16 | Boeing Co | Wind tunnel model support |
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| CN102829946A (en) | 2012-12-19 |
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Granted publication date: 20150819 Termination date: 20180820 |