CN102826218B - A kind of Afterbody rectification structure of twin-engine aircraft - Google Patents
A kind of Afterbody rectification structure of twin-engine aircraft Download PDFInfo
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- CN102826218B CN102826218B CN201210333811.4A CN201210333811A CN102826218B CN 102826218 B CN102826218 B CN 102826218B CN 201210333811 A CN201210333811 A CN 201210333811A CN 102826218 B CN102826218 B CN 102826218B
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Abstract
The present invention relates to a kind of aerodynamic configuration of aircraft design field, particularly a kind of Afterbody rectification structure of twin-engine aircraft, comprising: rectification aft end face (1), rectification lower surface (2) and rectification upper surface (4), and form the rectifier structure of outer Shape closed with rear body engine shield (3). This rectification contour structures can ensure that between aircraft two engine shield, rectification profile has less angle of throat, can avoid the pneumatic separation of aircraft upper and lower surface, and height is relatively big with space, contributes to alleviating structural weight and increasing structural strength.
Description
Technical field
The present invention relates to a kind of Hang Qi aerodynamic arrangement design field, particularly a kind of Afterbody rectification structure of twin-engine aircraft.
Background technology
To general military aircraft, engine is arranged on fuselage interior, after airframe, section (hereinafter referred to as rear body) has concentrated the parts such as vertical fin, tailplane and engine jet pipe, complex contour, between parts, aerodynamical interference is bigger, causing resistance that identical infiltration area produces far above other positions of aircraft, after usually, body resistance accounts for the nearly half that aircraft zero hinders. In addition, not good rear body rectification profile also can bring pneumatic separation, thus causes the problems such as aircraft vibration. Therefore airplane design teacher needs to design, according to rear body characteristicses such as engine quantity, nozzle space, engine performance, carriage requirement and empennage forms, the rear body rectification profile mated mutually, to reduce rear body pneumatic separation, and body resistance after reducing.
Summary of the invention
(1) object of the present invention
For arranging the rear bodily form formula that two engine spacing are less in airframe, it is provided that a kind of Afterbody rectification structure of twin-engine aircraft, to reduce rear body pneumatic separation, body resistance after reducing.
(2) technical scheme of the present invention
The technical scheme of the present invention is: a kind of Afterbody rectification structure of twin-engine aircraft, comprising: rectification aft end face, rectification lower surface and rectification upper surface, and forms the rectifier structure of outer Shape closed with rear body engine shield; Rectification lower surface and rectification upper surface are positioned at after aircraft in the middle of body two engine shields, and rectification aft end face connects rectification upper surface and rectification lower surface up and down, and left and right connects two engine shields.
Described rectification aft end face is the plane of vertical air-flow.
Described rectification upper surface seamlessly transits along rear body upper profile downstream direction, and upper surface angle of throat is less than 9 °.
Described rectification lower surface seamlessly transits along rear body lower profile downstream direction, and lower surface angle of throat is less than 12 °.
(3) the useful effect of the present invention
This rectifier structure can ensure that between aircraft two engine shield, rectification profile has less angle of throat, can avoid the pneumatic separation of aircraft upper and lower surface; The separation air-flow (similar with wing wingtip vortex) of rectification aft end face is not applied directly on aircraft components, and aircraft can not be caused to shake.When jet cutting car flow (pressure ratio that falls is greater than 1.89) produces following current to inverse pressure gradient in jet pipe district, this rectification aft end face can reduce rear body resistance. Structure height and space are relatively big in addition, contribute to alleviating structural weight and increasing structural strength.
Accompanying drawing explanation
Accompanying drawing 1 is body rectifier structure schematic diagram after aircraft.
Embodiment
Embodiments of the present invention are as follows: as shown in Figure 1, and a kind of Afterbody rectification structure of twin-engine aircraft, comprising: rectification aft end face 1, rectification lower surface 2 and rectification upper surface 4, and form the rectifier structure of outer Shape closed with rear body engine shield 3; After rectification lower surface 2 and rectification upper surface 4 are positioned at aircraft, body two engine shields 3 are middle, and rectification aft end face about 1 connects rectification upper surface 4 and rectification lower surface 2, and left and right connects two engine shields 3.
Rectification upper surface 4 seamlessly transits along rear body upper profile downstream direction, ensures that upper surface angle of throat is less than 9 °; Rectification lower surface 2 seamlessly transits along rear body lower profile downstream direction, ensures that lower surface angle of throat is less than 12 °. Rectification aft end face 1 is the plane of vertical air-flow, connects the trailing edge of rectification upper surface 4 and rectification upper surface 2, and its center is as far as possible at two line places, engine shield center, and rectification upper surface 4, rectification lower surface 2 and rectification aft end face 1 hand over line not need to do down circle or fairing processing.
When ensureing that rectification upper surface 4 and rectification lower surface 2 do not have pneumatic separation (can judge by CFD numerical evaluation), can suitably adjust area size and the upper-lower position of rectification aft end face 1, to obtain on the whole drag reduction, effectiveness in vibration suppression preferably.
Claims (4)
1. an Afterbody rectification structure of twin-engine aircraft, comprising: rectification aft end face (1), rectification lower surface (2) and rectification upper surface (4), and with rear body engine shield (3) form outer Shape closed rectifier structure, it is characterised in that; After rectification lower surface (2) and rectification upper surface (4) are positioned at aircraft, body two engine shields (3) are middle, rectification aft end face (1) connects rectification upper surface (4) and rectification lower surface (2) up and down, left and right connects two engine shields (3), the plane that rectification aft end face (1) is vertical air-flow.
2. a kind of Afterbody rectification structure of twin-engine aircraft according to claim 1, is characterized in that rectification aft end face (1) central position is as far as possible at two line places, engine shield center.
3. a kind of Afterbody rectification structure of twin-engine aircraft according to claim 1, is characterized in that rectification upper surface (4) seamlessly transits along rear body upper profile downstream direction, and upper surface angle of throat is less than 9 °.
4. a kind of Afterbody rectification structure of twin-engine aircraft according to claim 1, is characterized in that rectification lower surface (2) seamlessly transits along rear body lower profile downstream direction, and lower surface angle of throat is less than 12 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210333811.4A CN102826218B (en) | 2012-09-11 | 2012-09-11 | A kind of Afterbody rectification structure of twin-engine aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210333811.4A CN102826218B (en) | 2012-09-11 | 2012-09-11 | A kind of Afterbody rectification structure of twin-engine aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102826218A CN102826218A (en) | 2012-12-19 |
| CN102826218B true CN102826218B (en) | 2016-06-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201210333811.4A Active CN102826218B (en) | 2012-09-11 | 2012-09-11 | A kind of Afterbody rectification structure of twin-engine aircraft |
Country Status (1)
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106762144B (en) * | 2016-11-30 | 2018-07-13 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft interior conduit method for designing profile |
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| US5249762A (en) * | 1990-08-21 | 1993-10-05 | Eidetics Internation, Inc. | Strakes for landing speed reduction |
| CN101472797A (en) * | 2006-06-20 | 2009-07-01 | 法国空中巴士公司 | Fairing for a pylon via which a turbine engine is suspended from a wing of an aircraft |
| CA2711594A1 (en) * | 2008-01-07 | 2009-07-16 | Rohr, Inc | A method and component for determining load on a latch assembly |
| CN201362366Y (en) * | 2009-01-08 | 2009-12-16 | 江西昌河航空工业有限公司 | Cowling lock mechanism of helicopter nacelle |
| CN102202973A (en) * | 2008-10-30 | 2011-09-28 | 斯奈克玛 | Airplane having engines partially encased in the fuselage |
| CN202783775U (en) * | 2012-09-11 | 2013-03-13 | 江西洪都航空工业集团有限责任公司 | Rectification structure of twin-engine airplane after-body |
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2012
- 2012-09-11 CN CN201210333811.4A patent/CN102826218B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5249762A (en) * | 1990-08-21 | 1993-10-05 | Eidetics Internation, Inc. | Strakes for landing speed reduction |
| CN101472797A (en) * | 2006-06-20 | 2009-07-01 | 法国空中巴士公司 | Fairing for a pylon via which a turbine engine is suspended from a wing of an aircraft |
| CA2711594A1 (en) * | 2008-01-07 | 2009-07-16 | Rohr, Inc | A method and component for determining load on a latch assembly |
| CN102202973A (en) * | 2008-10-30 | 2011-09-28 | 斯奈克玛 | Airplane having engines partially encased in the fuselage |
| CN201362366Y (en) * | 2009-01-08 | 2009-12-16 | 江西昌河航空工业有限公司 | Cowling lock mechanism of helicopter nacelle |
| CN202783775U (en) * | 2012-09-11 | 2013-03-13 | 江西洪都航空工业集团有限责任公司 | Rectification structure of twin-engine airplane after-body |
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| 超机动能力对于未来空战是否还重要;邱贞玮;《网易博客》;20091212;http://skulkdragon.blog.163.com/blog/static/94463239200911122376237/ * |
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| CN102826218A (en) | 2012-12-19 |
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Effective date of registration: 20170516 Address after: 330024 South flying point, hi tech Industrial Development Zone, Jiangxi, Nanchang Patentee after: Jiangxi Hongdu Aviation Industry Limited by Share Ltd Address before: 330000 Jiangxi city in Nanchang Province, the new bridge box 460 box 5001 Patentee before: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. |