CN103487229A - Trisonics wind tunnel test section expansion angle adjusting mechanism - Google Patents
Trisonics wind tunnel test section expansion angle adjusting mechanism Download PDFInfo
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- CN103487229A CN103487229A CN201310390437.6A CN201310390437A CN103487229A CN 103487229 A CN103487229 A CN 103487229A CN 201310390437 A CN201310390437 A CN 201310390437A CN 103487229 A CN103487229 A CN 103487229A
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Abstract
The invention relates to a trisonics wind tunnel test section expansion angle adjusting mechanism. Two sets of expansion angle adjusting mechanisms are symmetrically arranged along the horizontal plane of the axis of a trisonics wind tunnel test section respectively in an up and down mode. Each set of expansion angle adjusting mechanism comprises an adjusting piece and a lifting mechanism. Each adjusting piece comprises a connection section, a variable angle section and a rigid section, wherein, one end of the connection section is fixedly connected with the trisonics wind tunnel test section, the other end of the connection section is integrally connected with the rigid section through the variable angle section, and the lifting mechanism is connected with the end, away from the variable angle section, of the rigid section and used for lifting the adjusting piece. According to the trisonics wind tunnel test section expansion angle adjusting mechanism, the lifting mechanisms are used for driving the suspension ends of the adjusting pieces to move, so that the variable angle sections of the adjusting pieces elastically deform and are expanded according to a certain angle, the adjusting pieces are in smooth transition from front to rear, turning points and seams do not exist in a wall board, and influences on a flow field of a wind tunnel test section are small.
Description
Technical field
The present invention relates to a kind of trisonic wind tunnel test section and expand the angle governor motion.
Background technology
Test section is tunnel simulation flight flow field, and the parts that carry out the test of Model Space aerodynamics, be the core of whole wind-tunnel.Conventional trisonic wind tunnel test section is the test section of remaining silent, and test section and front end jet pipe are smoothly connected, and for meeting testing requirements, the test section flow field uniformity requires very high.Air-flow, in the test section flow process, along the boundary layer progressive additive of wall, reduces the significance bit flow section of air-flow gradually, thereby causes along the axial Mach number of test section and reduce gradually and static pressure raises, and affects flow field uniformity.Use experience shows both at home and abroad, and it is not identical that the wallboard of the actual use of different wind-tunnel expands angle, in same seat test chamber, and the different tests Mach number, it is also different that best wallboard expands angle.Therefore general trisonic wind tunnel test section two side is fixing parallel walls, and on test section lower wall be adjustable, expand the use value at angle according to lower wall on flow field calibration of wind tunnel confirmed test section as a result.Current all trisonic wind tunnel adjustment sheets expand angle and all are no more than 1.5 °.
Current domestic trisonic wind tunnel test section expands the angle governor motion and usually all adopts the rotating shaft pattern, be that adjustment sheet and test section junction arrange rotating shaft, by rotating shaft, rotate, produce certain angle that expands, rotating shaft pattern test section expands the angle governor motion because the rotating shaft size is subject to structural limitations, and while expanding, the angle turnover obviously, simultaneously after long-time the use, adjustment sheet and chain connection position, because gap appears in wearing and tearing, can produce and expand or wave of compression in the supersonic speed condition, and the impact of stream field homogeneity is larger.
Summary of the invention
Technical matters to be solved by this invention is: overcome the deficiencies in the prior art, provide effective, the jointless trisonic wind tunnel test section of a kind of smooth transition to expand the angle governor motion.
The technical scheme that the present invention solves the problems of the technologies described above is as follows:
A kind of trisonic wind tunnel test section expands the angle governor motion, along trisonic wind tunnel test section axis horizontal face, upper and lower symmetry is respectively arranged a set of angle governor motion that expands, and every cover expands the angle governor motion and includes adjustment sheet and hoisting gear, and adjustment sheet comprises again linkage section, varied angle section and rigid section;
One end of linkage section is fixedly connected with described trisonic wind tunnel test section, and the other end of linkage section connects as one by varied angle section and rigid section, and hoisting gear is connected with the end away from the varied angle section of rigid section for promoting described adjustment sheet.
Hoisting gear is connected with described rigid section by hinge arrangement.
The varied angle section comprises thin elastic plate, front hinge seat, rear hinge seat and hinge.
The bottom of front hinge seat is fixedly connected with linkage section, and the bottom of rear hinge seat is fixedly connected with rigid section, and the two ends of thin elastic plate connect respectively rigid section and linkage section, between front hinge seat and rear hinge seat, is connected through the hinge together.
Thin elastic plate, rigid section and linkage section are one-body molded.
The present invention's beneficial effect compared with prior art is:
(1) Elastic plate of the present invention has than big-length, and during elastic deformation, angle changes smoothly, less on the airflow homogeneity impact.
(2) adjustment sheet integral manufacturing, elastic plate and adjustment sheet are an integral body, only, there is not seam in thinner thickness, under the supersonic speed condition, can not produce rarefaction wave or wave of compression.
Embodiment
As shown in Figure 1, the invention provides a kind of trisonic wind tunnel test section and expand the angle governor motion, along trisonic wind tunnel test section axis horizontal face, upper and lower symmetry is respectively arranged a set of angle governor motion that expands, every cover expands the angle governor motion and includes adjustment sheet 1 and hoisting gear 2, and adjustment sheet 1 comprises again linkage section 11, varied angle section 12 and rigid section 13.In figure, 3 mean airflow direction.
One end of linkage section 11 is fixedly connected with described trisonic wind tunnel test section, the other end of linkage section 11 connects as one by varied angle section 12 and rigid section 13, and hoisting gear 2 is connected with the end away from varied angle section 12 of rigid section 13 for promoting described adjustment sheet 1.Hoisting gear 2 is connected with described rigid section 13 by hinge arrangement.
As shown in Figure 2, varied angle section 12 comprises thin elastic plate 121, front hinge seat 122, rear hinge seat 123 and hinge 124; The bottom of front hinge seat 122 is fixedly connected with linkage section 11, the bottom of rear hinge seat 123 is fixedly connected with rigid section 13, the two ends of thin elastic plate 121 connect respectively rigid section 13 and linkage section 11, between front hinge seat 122 and rear hinge seat 123, by hinge 124, link together.Expanding angle governor motion (adjustment sheet 1 in horizontality time) hinge 124 when zero expands position is 3～5 degree with the vertical direction angle.
Thin elastic plate 121, rigid section 13 and linkage section 11 are one-body molded.Adjustment sheet 1 is the processing of monoblock steel plate, become elastic plate at varied angle section 12 attenuate wall thickness, on linkage section 11 and rigid section 13, arrange reinforcement, make it there is certain rigidity, when hoisting gear 2 drive adjustment sheets 1 move up, only thin elastic plate 121 deforms like this.For avoiding causing thin elastic plate 121 distortion because of gravity or stream pressure, above thin elastic plate 121, be provided with hinge by rigid section 13 together with linkage section 11, bear gravity and stream pressure load by hinge axis, be 3～5 degree expanding angle governor motion hinge 124 when zero expands position with the vertical direction angle, prevent from expanding in the adjustment process of angle stuck.
Hoisting gear 2 passes the test section housing by connecting rod, with adjustment sheet 1 hoist point, is connected, and connecting rod and test section housing adopt certain motive seal measure.Axially there is displacement while expanding due to adjustment sheet, need to arrange hinge between connecting rod and hinge.
Claims (6)
1. a trisonic wind tunnel test section expands the angle governor motion, it is characterized in that: along trisonic wind tunnel test section axis horizontal face, upper and lower symmetry is respectively arranged a set of angle governor motion that expands, every cover expands the angle governor motion and includes adjustment sheet (1) and hoisting gear (2), and adjustment sheet (1) comprises again linkage section (11), varied angle section (12) and rigid section (13);
One end of linkage section (11) is fixedly connected with described trisonic wind tunnel test section, the other end of linkage section (11) connects as one by varied angle section (12) and rigid section (13), and hoisting gear (2) is connected with the end away from varied angle section (12) of rigid section (13) for promoting described adjustment sheet (1).
2. a kind of trisonic wind tunnel test section according to claim 1 expands angle mechanism, it is characterized in that: described hoisting gear (2) is connected with described rigid section (13) by hinge arrangement.
3. a kind of trisonic wind tunnel test section according to claim 1 expands angle mechanism, it is characterized in that: described varied angle section (12) comprises thin elastic plate (121), front hinge seat (122), rear hinge seat (123) and hinge (124);
The bottom of front hinge seat (122) is fixedly connected with linkage section (11), the bottom of rear hinge seat (123) is fixedly connected with rigid section (13), the two ends of thin elastic plate (121) connect respectively rigid section (13) and linkage section (11), between front hinge seat (122) and rear hinge seat (123), by hinge (124), link together.
4. a kind of trisonic wind tunnel test section according to claim 3 expands angle mechanism, it is characterized in that: described thin elastic plate (121), rigid section (13) and linkage section (11) are one-body molded.
5. a kind of trisonic wind tunnel test section according to claim 1 expands angle mechanism, it is characterized in that: on linkage section (11) and rigid section (13), be furnished with reinforcement.
6. a kind of trisonic wind tunnel test section according to claim 3 expands angle mechanism, it is characterized in that: to expand angle governor motion hinge (124) when zero expands position be 3～5 degree with the vertical direction angle described.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310390437.6A CN103487229B (en) | 2013-08-30 | 2013-08-30 | A kind of trisonic wind tunnel test section expands angle governor motion |
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| CN201310390437.6A CN103487229B (en) | 2013-08-30 | 2013-08-30 | A kind of trisonic wind tunnel test section expands angle governor motion |
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| CN103487229A true CN103487229A (en) | 2014-01-01 |
| CN103487229B CN103487229B (en) | 2016-03-30 |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106840585A (en) * | 2016-12-29 | 2017-06-13 | 中国航天空气动力技术研究院 | A kind of supersonic wind tunnel test section adjusting means for possessing angle regulating function |
| CN109029900A (en) * | 2018-07-26 | 2018-12-18 | 河北工业大学 | The intelligent wind-tunnel of test section section-variable |
| CN110346107A (en) * | 2018-04-03 | 2019-10-18 | 上海汽车集团股份有限公司 | It is a kind of for testing the wind-tunnel of automotive performance |
| CN112556969A (en) * | 2020-12-07 | 2021-03-26 | 江苏中信博新能源科技股份有限公司 | Wind tunnel for testing photovoltaic solar system |
| CN112985745A (en) * | 2021-04-13 | 2021-06-18 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel test section wall plate expansion angle adjusting mechanism capable of keeping inner runner surface curvature continuous |
| CN114441132A (en) * | 2022-04-08 | 2022-05-06 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Side wall plate pulling device for large wind tunnel jet pipe section and pulling method thereof |
| CN115326346A (en) * | 2022-10-18 | 2022-11-11 | 中国航空工业集团公司哈尔滨空气动力研究所 | Easily-adjusted convertible side wall structure for closed test section |
| CN116577064A (en) * | 2023-07-12 | 2023-08-11 | 中国空气动力研究与发展中心高速空气动力研究所 | Manual adjustment mechanism for wind tunnel test section wallboard expansion angle and adjustment method thereof |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4751987B2 (en) * | 2004-11-22 | 2011-08-17 | 国立大学法人三重大学 | Wind power generator |
-
2013
- 2013-08-30 CN CN201310390437.6A patent/CN103487229B/en not_active Expired - Fee Related
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4751987B2 (en) * | 2004-11-22 | 2011-08-17 | 国立大学法人三重大学 | Wind power generator |
Non-Patent Citations (5)
| Title |
|---|
| 孙勇堂 等: "微型飞行器研究用极低速风洞的特点", 《试验流体力学》, vol. 20, no. 1, 31 March 2006 (2006-03-31), pages 58 - 61 * |
| 廖达雄 等: "连续式跨声速风洞设计关键技术", 《试验流体力学》, vol. 25, no. 4, 31 August 2011 (2011-08-31), pages 74 - 78 * |
| 张乃平 等: "跨音速翼型风洞的洞壁干扰及流动二元性的实验研究", 《西北工业大学学报》, vol. 2, no. 2, 31 December 1984 (1984-12-31), pages 151 - 160 * |
| 陈德华 等: "2.4m跨声速风洞流场性能调试研究", 《空气动力学学报》, vol. 22, no. 3, 30 September 2004 (2004-09-30), pages 279 - 282 * |
| 黄知龙 等: "暂冲式风洞大开角扩散段性能的实验研究", 《试验流体力学》, vol. 25, no. 3, 30 June 2011 (2011-06-30), pages 20 - 23 * |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106840585A (en) * | 2016-12-29 | 2017-06-13 | 中国航天空气动力技术研究院 | A kind of supersonic wind tunnel test section adjusting means for possessing angle regulating function |
| CN110346107A (en) * | 2018-04-03 | 2019-10-18 | 上海汽车集团股份有限公司 | It is a kind of for testing the wind-tunnel of automotive performance |
| CN109029900A (en) * | 2018-07-26 | 2018-12-18 | 河北工业大学 | The intelligent wind-tunnel of test section section-variable |
| CN109029900B (en) * | 2018-07-26 | 2024-01-19 | 河北工业大学 | Intelligent wind tunnel with variable section of test section |
| CN112556969A (en) * | 2020-12-07 | 2021-03-26 | 江苏中信博新能源科技股份有限公司 | Wind tunnel for testing photovoltaic solar system |
| CN112985745A (en) * | 2021-04-13 | 2021-06-18 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel test section wall plate expansion angle adjusting mechanism capable of keeping inner runner surface curvature continuous |
| CN114441132A (en) * | 2022-04-08 | 2022-05-06 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Side wall plate pulling device for large wind tunnel jet pipe section and pulling method thereof |
| CN114441132B (en) * | 2022-04-08 | 2022-06-17 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Side wall plate pulling device for large wind tunnel jet pipe section and pulling method thereof |
| CN115326346A (en) * | 2022-10-18 | 2022-11-11 | 中国航空工业集团公司哈尔滨空气动力研究所 | Easily-adjusted convertible side wall structure for closed test section |
| CN115326346B (en) * | 2022-10-18 | 2023-01-24 | 中国航空工业集团公司哈尔滨空气动力研究所 | Easily-adjusted convertible side wall structure for closed test section |
| CN116577064A (en) * | 2023-07-12 | 2023-08-11 | 中国空气动力研究与发展中心高速空气动力研究所 | Manual adjustment mechanism for wind tunnel test section wallboard expansion angle and adjustment method thereof |
| CN116577064B (en) * | 2023-07-12 | 2023-11-21 | 中国空气动力研究与发展中心高速空气动力研究所 | Manual adjustment mechanism for wind tunnel test section wallboard expansion angle and adjustment method thereof |
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| CN103487229B (en) | 2016-03-30 |
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