CN102249004A - Aircraft using submerged intake - Google Patents
Aircraft using submerged intake Download PDFInfo
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- CN102249004A CN102249004A CN2011101347148A CN201110134714A CN102249004A CN 102249004 A CN102249004 A CN 102249004A CN 2011101347148 A CN2011101347148 A CN 2011101347148A CN 201110134714 A CN201110134714 A CN 201110134714A CN 102249004 A CN102249004 A CN 102249004A
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Abstract
The invention provides an aircraft using a submerged intake. In the invention, a plurality of pairs of air-blowing tanks are arranged on the surface of a projectile body using the submerged intake so as to blow off a boundary layer on the surface of the projectile body through high-pressure jet, which effectively improves the characteristic of the boundary layer in front of the entrance of the submerged intake and enhances quality of air flow entering the submerged intake so as to greatly improve total pressure recovery coefficient and lower flow field distortion index at the exit of the submerged intake.
Description
Technical field
The present invention relates to a kind of aircraft, especially a kind of aircraft that uses Submerged Inlet.
Background technology
Submerged Inlet is a kind of import to be imbedded among fuselage or the wing, does not present the special inlet channel of any jut.Such design can actv. reduces the wind area of aircraft, and it is long-pending to reduce frontal resistance and RCS, thereby has stealthy preferably performance.Except above-mentioned advantage, because itself and bomb body/fuselage are melted into a whole, the aircraft circumferential size is reduced relatively, help laying, carrying and box emission of aircraft.More than many advantages make Submerged Inlet more and more receive domestic and international researcher's concern.
But, place the boundary 1ayer on fuselage/bomb body surface fully just because of the import of Submerged Inlet, can't make full use of incoming flow punching press air inlet as traditional inlet channel, lip is perpendicular to the vortex air inlet of pressure gradient that comes flow path direction and incline generation before only relying on.This just makes Submerged Inlet inflow point suck a large amount of bomb bodys/fuselage boundary 1ayer low energy stream, and pitot loss in the internal channel and Gas Mixing in Cross flow loss are bigger, thereby total pressure recovery coefficient is lower, and the exit flow field distortion is bigger.At present, Submerged Inlet has developed comparatively maturation as the correlation technique of additional-air inlet system, and has obtained using widely.But because the existence of the problems referred to above, Submerged Inlet has been subjected to bigger restriction as the application of main air system.
Therefore, need a kind of new technical scheme to address the above problem.
Summary of the invention
The problem lower in order to solve existing Submerged Inlet total pressure recovery coefficient, that the exit flow field distortion is bigger, it is higher to the invention provides a kind of total pressure recovery coefficient, the aircraft of the use Submerged Inlet that the exit flow field distortion is less.
For achieving the above object, the present invention can adopt following technical scheme:
A kind of aircraft that uses Submerged Inlet, the aircraft of this use Submerged Inlet comprise body portion and are positioned at the Submerged Inlet of body portion; Described Submerged Inlet comprises admission port and internal channel; Described body portion is provided with the seam of blowing.
The aircraft of use Submerged Inlet of the present invention, by offering the boundary layer bleed of seam of blowing in the aircraft body portion before the Submerged Inlet import with body portion surface, improved the preceding behavior of boundary layer of Submerged Inlet import preferably, improved the flow quality that entrainments into Submerged Inlet, thereby improved the total pressure recovery coefficient of Submerged Inlet, reduce the flow distortion of outlet, had the good engineering application prospect.
Description of drawings
Fig. 1 is the upward view that the present invention uses the aircraft of Submerged Inlet.
Fig. 2 is the schematic internal view that the present invention uses the aircraft of Submerged Inlet, this schematic diagram shows the state cut open from the plane of symmetry of this aircraft.
Fig. 3 is the schematic internal view that the present invention uses the aircraft of Submerged Inlet, this schematic diagram shows the state cut open from the B-B cross section of Fig. 2 of this aircraft.
The specific embodiment
See also shown in Figure 1ly, the invention discloses a kind of aircraft that uses Submerged Inlet.In the present embodiment, described Submerged Inlet type is the Submerged Inlet of blowing based on the body surface.
The aircraft 1 of described use Submerged Inlet has body portion 2, and described Submerged Inlet of blowing based on body surface is embedded in the described body portion 2, and admission port 5 is positioned at the bottom of body portion 2.Described body portion 2 is provided with the seam 3 of blowing, and described air blowing seam 3 is that symmetry is offered in body portion 2.Described body portion 2 has head (not label) that is positioned at front end and the afterbody (not label) that is positioned at the rear end, blew seam 3 before the admission port 5 that is positioned at Submerged Inlet in the body portion 2, and symmetry is offered some row successively, and each row is offered at least one air blowing seam 3.The angle α angle of the plane of symmetry of these blow seam 3 and body portion 2 longitudinallies is between 0 °～90 °.It is some right that described air blowing seam (3) can be offered along the axial symmetry of body portion (2)
See also shown in Figure 2ly, described Submerged Inlet of blowing based on body surface has admission port 5 and the internal channel 6 that is positioned at front end.Described internal channel 6 is provided with and is positioned at the preceding lip guide face 7 of admission port 5 tops in order to steering current, and the bumper/spoiler 8 on the lip guide face 7 before placing.Described bumper/spoiler 8 can be placed some row along preceding lip guide face 7 symmetry successively, and each row placement a slice or two bumper/spoilers of parallel placement, also can symmetry place plurality of rows simultaneously.Described bumper/spoiler 8 can scan out admission port 5 through the wall both sides of internal channel 6 with the part low energy air-flow that the place ahead flows into.Certainly, in other embodiments of the present invention, also can not place described bumper/spoiler 8.
See also shown in Figure 3, also be provided with high pressure chest 4 in the described body portion 2, air blowing seam 3 in the described body portion 2 that is arranged on the aircraft 1 that uses Submerged Inlet links to each other with high pressure chest 4, produce high pressure jet by differential pressure action, change the direction of jet simultaneously by the angle β that changes high pressure chest 4 and body portion 2 lower surfaces, boundary layer bleed with body portion 2 surfaces, thereby improved the behavior of boundary layer before the Submerged Inlet admission port 5, make that the air-flow of higher-energy is entrainmented into Submerged Inlet, and then the lifting of realization Submerged Inlet performance, not only improved the total pressure recovery coefficient of Submerged Inlet, reduced the flow distortion of outlet, and simple in structure, be easy to realize having the good engineering application prospect.Angle β angle between described high pressure chest 4 and body portion 2 lower surfaces is between 0 °～180 °.
The method and the approach of this technical scheme of specific implementation of the present invention are a lot, and the above only is a preferred implementation of the present invention.Should be pointed out that for those skilled in the art under the prerequisite that does not break away from the principle of the invention, can also make some improvements and modifications, these improvements and modifications also should be considered as protection scope of the present invention.The all available prior art of each component part not clear and definite in the present embodiment is realized.
Claims (9)
1. aircraft that uses Submerged Inlet, it is characterized in that: the aircraft of this use Submerged Inlet (1) comprises body portion (2) and is positioned at the Submerged Inlet of body portion (2); Described Submerged Inlet comprises admission port (5) and internal channel (6); Described body portion (2) is provided with the seam (3) of blowing.
2. the aircraft of use Submerged Inlet according to claim 1 is characterized in that: also be provided with high pressure chest (4) in the described body portion (2), described air blowing seam (3) links to each other with high pressure chest (4).
3. the aircraft of use Submerged Inlet according to claim 2 is characterized in that: described air blowing seam (3) is that symmetry is offered in body portion (2).
4. according to the aircraft of claim 1 or 2 or 3 described use Submerged Inlet, it is characterized in that: described body portion (2) has head that is positioned at front end and the afterbody that is positioned at the rear end, the seam (3) of blowing is positioned at Submerged Inlet in body portion (2) admission port (5) before, and symmetry is offered some row successively, and each row is offered at least one air blowing seam (3).
5. the aircraft of use Submerged Inlet according to claim 4 is characterized in that: it is some right that described air blowing seam (3) is offered along the axial symmetry of body portion (2).
6. according to the aircraft of claim 1 or 2 or 3 described use Submerged Inlet, it is characterized in that: the angle angle (α) between the plane of symmetry of described air blowing seam (3) and body portion (2) longitudinally is between 0 °～90 °.
7. the aircraft of use Submerged Inlet according to claim 6 is characterized in that: the angle angle (β) between the lower surface of described high pressure chest (4) and body portion (2) is between 0 °～180 °.
8. the aircraft of use Submerged Inlet according to claim 1 is characterized in that: have the preceding lip guide face (7) that is positioned at admission port (5) top on the described internal channel (6) and be located at before bumper/spoiler (8) on the lip guide face (7).
9. the aircraft of use Submerged Inlet according to claim 1 is characterized in that: the Submerged Inlet of described Submerged Inlet type for blowing based on the body surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011101347148A CN102249004A (en) | 2011-05-23 | 2011-05-23 | Aircraft using submerged intake |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011101347148A CN102249004A (en) | 2011-05-23 | 2011-05-23 | Aircraft using submerged intake |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102249004A true CN102249004A (en) | 2011-11-23 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011101347148A Pending CN102249004A (en) | 2011-05-23 | 2011-05-23 | Aircraft using submerged intake |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN104108470A (en) * | 2014-07-03 | 2014-10-22 | 南京航空航天大学 | Planar embedded type air inlet channel based on embedded type separation channel layout and design method |
| CN104389681A (en) * | 2014-11-26 | 2015-03-04 | 江西洪都航空工业集团有限责任公司 | Embedded type gas charging channel for supplementing gas for gas charging channel based on high-pressure gas cylinder |
| CN104386255A (en) * | 2014-11-26 | 2015-03-04 | 江西洪都航空工业集团有限责任公司 | Aircraft employing embedded air inlet channel |
| CN105109698A (en) * | 2015-09-24 | 2015-12-02 | 江西洪都航空工业集团有限责任公司 | Submerged air inlet of aircraft based on diverter air introduction |
| CN105129098A (en) * | 2015-09-24 | 2015-12-09 | 江西洪都航空工业集团有限责任公司 | Aircraft S bend and embedded type combination air inlet channel |
| EP3109153A1 (en) * | 2015-06-25 | 2016-12-28 | Northrop Grumman Systems Corporation | Swept gradient boundary layer diverter |
| CN106553760A (en) * | 2015-09-25 | 2017-04-05 | 北京机电工程研究所 | The method for designing of Submerged Inlet lip |
| CN107187608A (en) * | 2017-05-24 | 2017-09-22 | 江西洪都航空工业集团有限责任公司 | A kind of air blowing type afterbody flowfield fairing |
| CN107762633A (en) * | 2017-09-15 | 2018-03-06 | 江西洪都航空工业集团有限责任公司 | Bullet high-performance Submerged Inlet and boundary-layer minimizing technology |
| CN109159902A (en) * | 2018-08-23 | 2019-01-08 | 广州创链科技有限公司 | A kind of unmanned vehicle engine air inlet drainage mechanism |
| CN109367796A (en) * | 2018-09-17 | 2019-02-22 | 江西洪都航空工业集团有限责任公司 | A kind of Submerged Inlet boundary layer control device based on fluid oscillator |
| CN110758752A (en) * | 2019-12-05 | 2020-02-07 | 江西洪都航空工业集团有限责任公司 | Swirl air inlet embedded type air inlet channel, working mode thereof and aircraft |
| CN117326073A (en) * | 2023-11-09 | 2024-01-02 | 北京北航天宇长鹰无人机科技有限公司 | Buried air inlet channel with stepped boundary layer separation channel and unmanned aerial vehicle |
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| US6793175B1 (en) * | 1999-08-25 | 2004-09-21 | The Boeing Company | Supersonic external-compression diffuser and method for designing same |
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| CN101994570A (en) * | 2010-11-19 | 2011-03-30 | 南京航空航天大学 | Embedded air inlet based on vortex excretion and aircraft using embedded air inlet |
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2011
- 2011-05-23 CN CN2011101347148A patent/CN102249004A/en active Pending
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| US6793175B1 (en) * | 1999-08-25 | 2004-09-21 | The Boeing Company | Supersonic external-compression diffuser and method for designing same |
| CN101348170A (en) * | 2008-09-01 | 2009-01-21 | 北京航空航天大学 | Wing structure having lamellar flow flowing control and separation control |
| CN101994570A (en) * | 2010-11-19 | 2011-03-30 | 南京航空航天大学 | Embedded air inlet based on vortex excretion and aircraft using embedded air inlet |
Non-Patent Citations (1)
| Title |
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| 郭荣伟等: "埋入式进气道设计", 《南京航空航天大学学报》, vol. 33, no. 1, 28 February 2001 (2001-02-28), pages 8 - 12 * |
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN104108470A (en) * | 2014-07-03 | 2014-10-22 | 南京航空航天大学 | Planar embedded type air inlet channel based on embedded type separation channel layout and design method |
| CN104108470B (en) * | 2014-07-03 | 2016-04-13 | 南京航空航天大学 | Based on flush type every the planar hexagonal crystal of road layout and method of designing |
| CN104389681A (en) * | 2014-11-26 | 2015-03-04 | 江西洪都航空工业集团有限责任公司 | Embedded type gas charging channel for supplementing gas for gas charging channel based on high-pressure gas cylinder |
| CN104386255A (en) * | 2014-11-26 | 2015-03-04 | 江西洪都航空工业集团有限责任公司 | Aircraft employing embedded air inlet channel |
| US9758253B2 (en) | 2015-06-25 | 2017-09-12 | Northrop Grumman Systems Corporation | Swept gradient boundary layer diverter |
| EP3109153A1 (en) * | 2015-06-25 | 2016-12-28 | Northrop Grumman Systems Corporation | Swept gradient boundary layer diverter |
| CN105109698A (en) * | 2015-09-24 | 2015-12-02 | 江西洪都航空工业集团有限责任公司 | Submerged air inlet of aircraft based on diverter air introduction |
| CN105129098A (en) * | 2015-09-24 | 2015-12-09 | 江西洪都航空工业集团有限责任公司 | Aircraft S bend and embedded type combination air inlet channel |
| CN106553760A (en) * | 2015-09-25 | 2017-04-05 | 北京机电工程研究所 | The method for designing of Submerged Inlet lip |
| CN106553760B (en) * | 2015-09-25 | 2019-03-22 | 北京机电工程研究所 | The design method of Submerged Inlet lip |
| CN107187608A (en) * | 2017-05-24 | 2017-09-22 | 江西洪都航空工业集团有限责任公司 | A kind of air blowing type afterbody flowfield fairing |
| CN107762633A (en) * | 2017-09-15 | 2018-03-06 | 江西洪都航空工业集团有限责任公司 | Bullet high-performance Submerged Inlet and boundary-layer minimizing technology |
| CN109159902A (en) * | 2018-08-23 | 2019-01-08 | 广州创链科技有限公司 | A kind of unmanned vehicle engine air inlet drainage mechanism |
| CN109367796A (en) * | 2018-09-17 | 2019-02-22 | 江西洪都航空工业集团有限责任公司 | A kind of Submerged Inlet boundary layer control device based on fluid oscillator |
| CN109367796B (en) * | 2018-09-17 | 2022-03-15 | 江西洪都航空工业集团有限责任公司 | Embedded air inlet boundary layer control device based on fluid oscillator |
| CN110758752A (en) * | 2019-12-05 | 2020-02-07 | 江西洪都航空工业集团有限责任公司 | Swirl air inlet embedded type air inlet channel, working mode thereof and aircraft |
| CN110758752B (en) * | 2019-12-05 | 2023-08-18 | 江西洪都航空工业集团有限责任公司 | Rotational flow air inlet embedded type air inlet channel, working mode thereof and aircraft |
| CN117326073A (en) * | 2023-11-09 | 2024-01-02 | 北京北航天宇长鹰无人机科技有限公司 | Buried air inlet channel with stepped boundary layer separation channel and unmanned aerial vehicle |
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Application publication date: 20111123 |