CN109050869A - A kind of ram-air bleed structure - Google Patents
A kind of ram-air bleed structure Download PDFInfo
- Publication number
- CN109050869A CN109050869A CN201810784664.XA CN201810784664A CN109050869A CN 109050869 A CN109050869 A CN 109050869A CN 201810784664 A CN201810784664 A CN 201810784664A CN 109050869 A CN109050869 A CN 109050869A
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- CN
- China
- Prior art keywords
- bleed
- towards
- machine
- aircraft
- air
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/0009—Aerodynamic aspects
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/10—Constructional aspects of UAVs for stealth, e.g. reduction of cross-section detectable by radars
Abstract
The present invention relates to airplane design technical field, in particular to a kind of ram-air bleed structure.The structure includes: air entraining device, axially disposed several bleed holes, towards machine outside one end and fuselage it is conformal；Support device, one end are fixedly connected with the bleed structure towards one end in machine, are used to support the bleed structure, and be connected to the bleed hole and internal body.By the structure setting in the bleed ports that body opens up, it is not protruded after being installed in engine body exterior, realization is merged with the height of body, to maintain the aerodynamic configuration of aircraft, the flight resistance of aircraft is reduced with this, keep aircraft flight steady, and the Stealth Fighter of aircraft can be avoided damage to a certain extent；In addition, the structure is simple, it is easy to spread to replace existing ram-air bleed mouth structure design convenient for manufacture, installation.
Description
Technical field
The present invention relates to airplane design technical field, in particular to a kind of ram-air bleed structure.
Background technique
Air of the ram-air in machine external environment is that one of airplane design is important heat sink, and multi-pass, which is crossed, to be set
It sets in the ram-air bleed ports introducing machine at fuselage or wing.It can according to the shape of ram-air bleed ports and installation site
It is divided into leading edge bleed ports and infundibulate bleed ports as shown in Figures 1 and 2.
Above-mentioned leading edge bleed ports and infundibulate bleed ports, or directly in leading edge opening or prominent aircraft skin, which increase fly
The flight resistance of machine also causes in various degree the Stealth Fighter of aircraft in addition, showing in relation to the stealthy technical data of aircraft
Destruction, cause Stealth Fighter to decline.
Summary of the invention
The object of the present invention is to provide a kind of ram-air bleed structures, to overcome or alleviated by above-mentioned at least one aspect
Problem.
The technical scheme is that
A kind of ram-air bleed structure, comprising:
Air entraining device, axially disposed several bleed holes, towards machine outside one end and fuselage it is conformal；
Support device, one end are fixedly connected with bleed structure towards one end in machine, are used to support bleed structure, and
It is connected to bleed hole and internal body.
Preferably, air entraining device includes:
Bleed cylinder, towards machine outside one end and fuselage it is conformal；
Bleed ring is fixedly connected with the outer wall of bleed cylinder towards one end outside machine, and it is total to towards the side outside machine with fuselage
Shape；
Bleed grid is fixed in bleed cylinder, bleed hole is constituted between adjacent grid item, and towards one outside machine
It holds conformal with fuselage.
Preferably, support device includes:
Support tube, one end-face are fixedly connected with bleed cylinder 1 towards one end end face cooperation in machine；
Support ring, the outer wall with support tube backwards to bleed cylinder one end are fixedly connected.
Preferably, bleed ports section assumes diamond in shape.
Preferably, bleed ports section is square.
The present invention has the advantages that providing a kind of ram-air bleed structure, which can be set opens up in body
Bleed ports in, design that its external margin is conformal with body, match with the theoretical shape of body, in body after being installed
Outside does not protrude, and realization is merged with the height of body, to maintain the aerodynamic configuration of aircraft, the flight of aircraft is reduced with this
Resistance keeps aircraft flight steady, and can avoid damage to the Stealth Fighter of aircraft to a certain extent；In addition, the structure is simple,
It is easy to spread to replace existing ram-air bleed mouth structure design convenient for manufacturing, installing.
Detailed description of the invention
Fig. 1 is leading edge bleed ports structural schematic diagram.
Fig. 2 is infundibulate bleed ports structural schematic diagram.
Fig. 3 is ram-air bleed structure mounting structure schematic diagram of the present invention.
Fig. 4 is A direction view of the invention.
Specific embodiment
To keep the purposes, technical schemes and advantages of the invention implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention in conjunction with attached drawing.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the present invention
The limitation of range.
3-4 is described in further details the present invention with reference to the accompanying drawing.
The present invention provides a kind of ram-air bleed structures, comprising:
Air entraining device, axially disposed several bleed holes, towards machine outside one end and fuselage it is conformal；
Support device, one end are fixedly connected with bleed structure towards one end in machine, are used to support bleed structure, and
It is connected to bleed hole and internal body.
Further, above-mentioned air entraining device includes:
Bleed cylinder 1, towards machine outside one end and fuselage it is conformal；
Bleed ring 3 is fixedly connected with the outer wall of bleed cylinder 1 towards one end outside machine, and its towards outside machine side and fuselage
It is conformal；
Bleed grid 2 is fixed in bleed cylinder 1, bleed hole is constituted between adjacent grid item, and towards outside machine
One end is conformal with fuselage.
The design that air entraining device is cooperated using bleed grid 2 and bleed cylinder 1, grille strip is interspersed forms bleed therebetween
Hole, structure is simple, quality light weight, while design can be facilitated to adjust the size in bleed hole to meet to aircraft to ram-air
The requirement of amount, and its stable structure is reliable.
Further, above-mentioned support device includes:
Support tube 4, one end-face are fixedly connected with bleed cylinder 1 towards one end end face cooperation in machine；
Support ring 5, the outer wall with support tube 4 backwards to 1 one end of bleed cylinder are fixedly connected.
The ram-air amount that the size of above-mentioned support tube 4 is as needed is designed, and the fixed form with bleed cylinder 1 can
It selects in known range in those skilled in the art, is preferably welded and fixed herein.Above-mentioned support ring 5 is arranged can be square
Just support device and body are fixedly connected, and it matches clamping body in the axial direction with bleed ring 3 makes the bleed structure
It is solid and reliable.
Further, the section for the bleed ports that grille strip is formed can be designed to assume diamond in shape, on the one hand using such design
The flow distortion that bleed ports surrounding flow can be reduced suppresses or eliminates the whirlpool of air-flow, reduces radar scattering area, another
Aspect, design grid is closeer, forms the latus rectum of very little in a thickness direction, and most of radar waves cannot be introduced into because wavelength is too long
Most of energy of interior of aircraft, radar wave is reflected by grid face, to protect the Stealth Fighter of aircraft.Studies have shown that
When grille strip is orthogonal, i.e., when bleed hole section is square, the radar wave energy for reaching grid surface can be to 45° angle direction
Reflection, radar curtain effect are more preferable.
The above description is merely a specific embodiment, but scope of protection of the present invention is not limited thereto, any
In the technical scope disclosed by the present invention, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
It is included within the scope of the present invention.Therefore, protection scope of the present invention should be with the scope of protection of the claims
It is quasi-.
Claims (5)
1. a kind of ram-air bleed structure characterized by comprising
Air entraining device, axially disposed several bleed holes, towards machine outside one end and fuselage it is conformal；
Support device, one end are fixedly connected with the bleed structure towards one end in machine, are used to support the bleed knot
Structure, and it is connected to the bleed hole and internal body.
2. bleed structure according to claim 1, which is characterized in that the air entraining device includes:
Bleed cylinder (1), towards machine outside one end and fuselage it is conformal；
Bleed ring (3) is fixedly connected with the outer wall of described bleed cylinder (1) towards one end outside machine, and its towards outside machine side with
Fuselage is conformal；
Bleed grid (2) is fixed in the bleed cylinder (1), and the bleed hole, and court are constituted between adjacent grid item
One end and fuselage to outside machine is conformal.
3. bleed structure according to claim 2, which is characterized in that the support device includes:
Support tube (4), one end-face are fixedly connected with the bleed cylinder (1) towards one end end face cooperation in machine；
Support ring (5), the outer wall with the support tube (4) backwards to described bleed cylinder (1) one end are fixedly connected.
4. bleed structure according to claim 2 or 3, which is characterized in that the bleed ports section assumes diamond in shape.
5. bleed structure according to claim 2 or 3, which is characterized in that the bleed ports section is square.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810784664.XA CN109050869A (en) | 2018-07-17 | 2018-07-17 | A kind of ram-air bleed structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810784664.XA CN109050869A (en) | 2018-07-17 | 2018-07-17 | A kind of ram-air bleed structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109050869A true CN109050869A (en) | 2018-12-21 |
Family
ID=64816987
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810784664.XA Pending CN109050869A (en) | 2018-07-17 | 2018-07-17 | A kind of ram-air bleed structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109050869A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110466735A (en) * | 2019-08-26 | 2019-11-19 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of lid having both intake and exhaust functions |
| CN114248937A (en) * | 2021-12-30 | 2022-03-29 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Air entraining window of RAT generator |
Citations (7)
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|---|---|---|---|---|
| CN102143889A (en) * | 2008-09-03 | 2011-08-03 | 埃尔塞乐公司 | Method for making an acoustic panel for the air intake lip of a nacelle |
| CN102348600A (en) * | 2009-03-27 | 2012-02-08 | 空中客车运营简化股份公司 | Aircraft nacelle comprising a reinforced outer wall |
| CN202596897U (en) * | 2012-04-06 | 2012-12-12 | 中国航空工业集团公司沈阳发动机设计研究所 | Bleed air baffle plate structure |
| JP2016008040A (en) * | 2014-06-23 | 2016-01-18 | 井上 冨士夫 | Boundary layer control device of aircraft |
| CN105752347A (en) * | 2016-02-29 | 2016-07-13 | 薛忠群 | Airplane air inlet structure |
| CN105775147A (en) * | 2016-04-08 | 2016-07-20 | 中国空气动力研究与发展中心高速空气动力研究所 | Aircraft inlet closed-loop flow control device and control method |
| CN207360559U (en) * | 2017-10-27 | 2018-05-15 | 西安深瞳智控技术有限公司 | A kind of blowing structure for improving horizontal tail flow field characteristic when taking off |
-
2018
- 2018-07-17 CN CN201810784664.XA patent/CN109050869A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102143889A (en) * | 2008-09-03 | 2011-08-03 | 埃尔塞乐公司 | Method for making an acoustic panel for the air intake lip of a nacelle |
| CN102348600A (en) * | 2009-03-27 | 2012-02-08 | 空中客车运营简化股份公司 | Aircraft nacelle comprising a reinforced outer wall |
| CN202596897U (en) * | 2012-04-06 | 2012-12-12 | 中国航空工业集团公司沈阳发动机设计研究所 | Bleed air baffle plate structure |
| JP2016008040A (en) * | 2014-06-23 | 2016-01-18 | 井上 冨士夫 | Boundary layer control device of aircraft |
| CN105752347A (en) * | 2016-02-29 | 2016-07-13 | 薛忠群 | Airplane air inlet structure |
| CN105775147A (en) * | 2016-04-08 | 2016-07-20 | 中国空气动力研究与发展中心高速空气动力研究所 | Aircraft inlet closed-loop flow control device and control method |
| CN207360559U (en) * | 2017-10-27 | 2018-05-15 | 西安深瞳智控技术有限公司 | A kind of blowing structure for improving horizontal tail flow field characteristic when taking off |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110466735A (en) * | 2019-08-26 | 2019-11-19 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of lid having both intake and exhaust functions |
| CN114248937A (en) * | 2021-12-30 | 2022-03-29 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Air entraining window of RAT generator |
| CN114248937B (en) * | 2021-12-30 | 2023-12-08 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Air entraining window of RAT generator |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20181221 |
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| RJ01 | Rejection of invention patent application after publication |