CN104443404A - S-shaped air inlet structure of aircraft - Google Patents
S-shaped air inlet structure of aircraft Download PDFInfo
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- CN104443404A CN104443404A CN201410675068.XA CN201410675068A CN104443404A CN 104443404 A CN104443404 A CN 104443404A CN 201410675068 A CN201410675068 A CN 201410675068A CN 104443404 A CN104443404 A CN 104443404A
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Abstract
The invention relates to the field of air inlets of aircrafts, in particular to an S-shaped air inlet structure of an aircraft. The S-shaped air inlet structure of the aircraft comprises an aircraft shell and an S-shaped air channel. The S-shaped air channel comprises an air inlet passage, an air inlet and an air outlet, wherein the air inlet and the air outlet are formed in the front and the back of the air inlet passage respectively. The air outlet enters the interior of the aircraft shell, the air inlet is installed on the windward face of the surface of the aircraft shell, and a plurality of vortex generators are arranged inside the air inlet passage. The vortex generators are arranged on the upstream position, having the potential for air flow separation, of a flow diversion face on the upper portion of the air inlet passage. Each vortex generator comprises four flow diversion pieces, the flow diversion pieces are arranged in pairs and distributed in the air inlet passage shaped like the Chinese character 'ba'. The S-shaped air inlet structure of the aircraft has the advantages of improving the outlet total pressure recovery coefficient and reducing the distortion index, and achieving the technical purposes of being small in size and light in weight.
Description
Technical field
The present invention relates to the inlet channel field of aircraft, relate to a kind of S shape inlet structure of aircraft specifically.
Background technology
S shape inlet channel can utilize incoming flow punching press, and passage flow field is relatively more even, and exit flow distortion index is lower, and total pressure recovery coefficient is higher, usually can reach 0.98 ~ 0.99.Therefore, S shape inlet channel is widely used on multi-form aircraft.But S shape inlet channel is subject to the restriction of weight and size sometimes, require that inlet channel length is shorter, line of centers turns round relatively more anxious, and at this moment in passage, friction layer is easily separated, and causes the decline of S shape inlet characteristic, and inlet channel can not meet operating needs.
Summary of the invention
The object of the invention is to solve the problem, a kind of S shape inlet structure of aircraft is provided.
In order to realize object of the present invention, the technical solution used in the present invention is:
A kind of S shape inlet structure of aircraft, comprise aircraft casing, S shape air flue, S shape air flue comprises free air diffuser and the admission port before and after it and air extractor duct, air extractor duct enters the inside of aircraft casing, admission port be arranged on aircraft casing surface towards windward side, some vortex generators are set in free air diffuser.
Vortex generator is arranged on the upstream position of the potential generation burbling of upper guide stream interface of free air diffuser.
Vortex generator is four flow deflectors, and flow deflector is that two the one symmetrical "eight" shape of composition are arranged in free air diffuser.
Beneficial effect of the present invention is: improve outlet total pressure recovery coefficient and reduce distortion index, achieving the technical goal of small size and light weight S shape inlet channel.
Accompanying drawing explanation
Fig. 1 is S shape air flue of the present invention and aircraft interior schematic diagram, the figure shows the state that aircraft is cut open from the plane of symmetry,
Fig. 2 structural representation of the present invention (showing vortex generator).
Detailed description of the invention
Below in conjunction with drawings and Examples, the present invention is further described:
Embodiment: see Fig. 1, Fig. 2.
A kind of S shape inlet structure of aircraft, comprise aircraft casing 1, S shape air flue 2, S shape air flue 2 comprises free air diffuser 203 and the admission port before and after it 201 and air extractor duct 202, air extractor duct 202 enters the inside of aircraft casing 1, admission port 201 be arranged on aircraft casing 1 surface towards windward side, some vortex generators 204 are set in free air diffuser 203.
Vortex generator 204 is arranged on the upstream position of the potential generation burbling of upper guide stream interface of free air diffuser 203.
Vortex generator 204 is four flow deflectors, and flow deflector is that two the one symmetrical "eight" shape of composition are arranged in free air diffuser 203.
Principle of work: be provided with vortex generator 204 on the inwall of free air diffuser 203.After air-flow enters free air diffuser 203 from admission port 201, when being about to due to strongly turning round of free air diffuser 203 separation of boundary layer occurs, vortex generator 204 is arranged at the upstream position of the potential generation burbling of the upper guide stream interface of free air diffuser 203, vortex generator 204 can form whirlpool at boundary layer region thus the blending of stiffened edge interlayer low energy stream and main flow, improves the performance of the Submerged Inlet based on injection venting with this.
Embodiments of the invention announce be one of preferred embodiment also; but be not limited thereto; those of ordinary skill in the art; very easily according to above-described embodiment; understand spirit of the present invention; and make different amplifications and change, but only otherwise depart from spirit of the present invention, all in protection scope of the present invention.
Claims (3)
1. the S shape inlet structure of an aircraft, comprise aircraft casing, S shape air flue, S shape air flue comprises free air diffuser and the admission port before and after it and air extractor duct, air extractor duct enters the inside of aircraft casing, admission port be arranged on aircraft casing surface towards windward side, it is characterized in that: some vortex generators are set in free air diffuser.
2. the S shape inlet structure of a kind of aircraft according to claim 1, is characterized in that: vortex generator is arranged on the upstream position of the potential generation burbling of upper guide stream interface of free air diffuser.
3. the S shape inlet structure of a kind of aircraft according to claim 2, is characterized in that: vortex generator is four flow deflectors, and flow deflector is that two the one symmetrical "eight" shape of composition are arranged in free air diffuser.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410675068.XA CN104443404A (en) | 2014-11-24 | 2014-11-24 | S-shaped air inlet structure of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410675068.XA CN104443404A (en) | 2014-11-24 | 2014-11-24 | S-shaped air inlet structure of aircraft |
Publications (1)
| Publication Number | Publication Date |
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| CN104443404A true CN104443404A (en) | 2015-03-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410675068.XA Pending CN104443404A (en) | 2014-11-24 | 2014-11-24 | S-shaped air inlet structure of aircraft |
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| CN (1) | CN104443404A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104832291A (en) * | 2015-04-22 | 2015-08-12 | 北京航空航天大学 | Half split hierarchical S-shaped air inlet channel design method |
| CN107380457A (en) * | 2017-07-31 | 2017-11-24 | 西安天拓航空科技有限公司 | A kind of stealthy unmanned plane dynamical system of Flying-wing |
| CN109353527A (en) * | 2018-08-13 | 2019-02-19 | 北京航空航天大学 | Using the BLI air intake duct of mixed flow control method |
| CN115030817A (en) * | 2022-04-14 | 2022-09-09 | 中国航天空气动力技术研究院 | Wide-speed-range adjustable air inlet channel with controllable wave system structure and engine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070241229A1 (en) * | 2006-04-12 | 2007-10-18 | The Boeing Company | Inlet distortion and recovery control system |
| US20080164378A1 (en) * | 2007-01-04 | 2008-07-10 | Administrator Of The National Aeronautics And Space Administration | Boundary-Layer-Ingesting Inlet Flow Control System |
| CN103422987A (en) * | 2013-07-31 | 2013-12-04 | 北京航空航天大学 | Pressure gradient controllable S-shaped inlet channel design method |
| CN103935524A (en) * | 2014-04-29 | 2014-07-23 | 南京航空航天大学 | High-performance subsonic speed air inlet duct integrated with inner auxiliary air inlet duct |
| CN204250375U (en) * | 2014-11-24 | 2015-04-08 | 江西洪都航空工业集团有限责任公司 | A kind of S shape inlet structure of aircraft |
-
2014
- 2014-11-24 CN CN201410675068.XA patent/CN104443404A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070241229A1 (en) * | 2006-04-12 | 2007-10-18 | The Boeing Company | Inlet distortion and recovery control system |
| US20080164378A1 (en) * | 2007-01-04 | 2008-07-10 | Administrator Of The National Aeronautics And Space Administration | Boundary-Layer-Ingesting Inlet Flow Control System |
| CN103422987A (en) * | 2013-07-31 | 2013-12-04 | 北京航空航天大学 | Pressure gradient controllable S-shaped inlet channel design method |
| CN103935524A (en) * | 2014-04-29 | 2014-07-23 | 南京航空航天大学 | High-performance subsonic speed air inlet duct integrated with inner auxiliary air inlet duct |
| CN204250375U (en) * | 2014-11-24 | 2015-04-08 | 江西洪都航空工业集团有限责任公司 | A kind of S shape inlet structure of aircraft |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104832291A (en) * | 2015-04-22 | 2015-08-12 | 北京航空航天大学 | Half split hierarchical S-shaped air inlet channel design method |
| CN107380457A (en) * | 2017-07-31 | 2017-11-24 | 西安天拓航空科技有限公司 | A kind of stealthy unmanned plane dynamical system of Flying-wing |
| CN109353527A (en) * | 2018-08-13 | 2019-02-19 | 北京航空航天大学 | Using the BLI air intake duct of mixed flow control method |
| CN115030817A (en) * | 2022-04-14 | 2022-09-09 | 中国航天空气动力技术研究院 | Wide-speed-range adjustable air inlet channel with controllable wave system structure and engine |
| CN115030817B (en) * | 2022-04-14 | 2024-06-11 | 中国航天空气动力技术研究院 | Wide-speed-range adjustable air inlet channel with controllable wave system structure and engine |
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| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150325 |