CN103950543B - Aircraft supersonic air inlet channel with variable deflation system - Google Patents
Aircraft supersonic air inlet channel with variable deflation system Download PDFInfo
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- CN103950543B CN103950543B CN201410158906.6A CN201410158906A CN103950543B CN 103950543 B CN103950543 B CN 103950543B CN 201410158906 A CN201410158906 A CN 201410158906A CN 103950543 B CN103950543 B CN 103950543B
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- air discharge
- discharge cavity
- inlet channel
- dividing plate
- deflation
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Abstract
The invention provides an aircraft supersonic air inlet channel with a variable deflation system. The aircraft supersonic air inlet channel with the variable deflation system comprises a supersonic front body compression surface, an air inlet channel lip cover, an air inlet channel side plate, an inner plate which extends inwards from the supersonic front body compression surface; a deflation chamber, a multi-seam or porous cover plate, a deflation chamber partition plate and flow limiting openings are arranged in the inner plate, wherein the multi-seam or porous cover plate covers the deflation chamber; the deflation chamber partition plate is positioned in the deflation chamber; the flow limiting openings are formed in the lower surface of the deflation chamber; the deflation chamber is partitioned into independent sub-chambers by the deflation chamber partition plate. The size of each sub-chamber, the number of the seams/pores of the multi-seam or porous cover plate corresponding to each sub-chamber and the opening and the closing of the flow limiting openings are adjusted by moving the deflation partition chamber according to the working Mach number and the attitude angle change of the supersonic air inlet channel, so that the deflation characteristics interfered by a lip cover shock wave/boundary layer are adjusted; therefore a good boundary layer control effect can be achieved in a wider work envelope range; the air emission amount is saved; a deflation flow channel in a certain area can even be closed when necessary.
Description
Technical field
The present invention relates to field of flight vehicle design, especially a kind of aircraft Supersonic Inlet.
Background technology
Supersonic Inlet is one of important Pneumatic component of high speed aerospace flight vehicle, it is positioned at airbreathing propulsion system foremost, bear traffic capture and the multiple function such as adjustment, incoming flow kinetic transformation and utilization, exit velocity size and homogeneity regulate, upstream and downstream disturbance isolation, all have direct impact to the work efficiency, operating envelope etc. of propulsion system.Meanwhile, Supersonic Inlet is also on the interface of propulsion system and aircraft, therefore also has remarkable impact to the aerodynamic characteristics, structural weight, Stealth Fighter etc. of aircraft.According to analysis, for conventional aero-turbine (flight Mach number is generally below 2.0), inlet total pres sure recovery coefficient often rises 1%, its thrust can be made to increase by 1.5%, unit fuel consumption rate declines 2.5%, and for the punching engine of higher Mach work, more than 50% of its total thrust derives from complicated air inlet system and exhaust system.
Deceleration pressurization due to supersonic flow needs to rely on the compression wave systems such as shock wave to realize, and inlet channel also has boundary 1ayer development in its inside while the body boundary 1ayer of suction upstream, therefore Shock/Boundary-Layer interference phenomenon is inevitable in Supersonic Inlet.And be necessary for subsonic velocity restriction (usual exit Mach number is less than 0.6) by exit flow, often comparatively large (7:1 may be reached) reduction ratio of air-flow is imported and exported in Supersonic Inlet, generally need jointly to be completed by processes such as oblique shock wave supercharging, normal shock wave supercharging and subsonic velocity superchargings, this makes the Shock/Boundary-Layer interference problem faced in Supersonic Inlet become complicated and various.Usually, serious Shock/Boundary-Layer interference phenomenon can bring out significant flow separation, and causes a series of adverse effect, and as the reduction of air intake port total pressure recovery coefficient, distortion index increases, subcritical stability margin reduces or starting envelope curve reduces.For this reason, Shock/Boundary-Layer interference is all kinds of Supersonic Inlet pneumatic design and the important flow phenomenon of a class troubling in assessing all the time, and wherein lip cover Shock/Boundary-Layer interference phenomenon is often outstanding.
In order to ensure in whole envelope safe, efficiently work, the Supersonic Inlet of current most of practicality all be unable to do without boundary 1ayer venting measure of control.This measure is a kind of Active control technology, by arranging many discharge air clefts or air bleed hole at lip cover Shock/Boundary-Layer interference range, and the pressure stabilizing cavity be attached thereto and flow restricting outlets, low energy air-flow neighbouring between Shock/Boundary-Layer interference range can be discharged outside inlet channel by such measure of control, therefore can control effectively to Shock/Boundary-Layer interference phenomenon.But, for the Supersonic Inlet of wide range of Mach numbers work, many places Shock/Boundary-Layer interference phenomenon may be there is in its passage, and along with this interference range position of change at flight Mach number, flight attitude angle and interference strength also can change thereupon, make the control of exitting of existing boundary 1ayer be difficult to successfully manage.For this reason, need a kind of novel boundary 1ayer venting of development measure of control, with the actual condition according to inlet channel, deflation characteristic is regulated, thus in wide region, remain on efficient state of a control.
Summary of the invention
For effectively suppressing that there is in wide Mach number Supersonic Inlet variable and Shock/Boundary-Layer interference phenomenon that is multi-region feature, the invention provides a kind of variable blow-off system and using its aircraft Supersonic Inlet.By arranging venting seam or air bleed hole, air discharge cavity, flow restricting outlets and removable air discharge cavity dividing plate at Shock/Boundary-Layer interference range, the present invention can regulate deflation characteristic according to the actual condition of inlet channel, thus obtains good control effects in wider Mach number and range of angles of attack.
For achieving the above object, the aircraft Supersonic Inlet that the present invention has variable blow-off system can adopt following technical scheme:
There is an aircraft Supersonic Inlet for variable blow-off system, comprise supersonic speed precursor compressing surface, inlet channel lip cover, inlet channel side plate, the inner panel that extends internally from supersonic speed precursor compressing surface; Inlet throat is formed between described inlet channel lip cover and inner panel; Described inner panel is provided with air discharge cavity, cover in air discharge cavity and towards many seams of inlet throat or Perforated decking, be positioned at air discharge cavity air discharge cavity dividing plate, connect the dividing plate connecting rod of air discharge cavity dividing plate, the dividing plate actuating device of connecting partition connecting rod; The bottom of described air discharge cavity is air discharge cavity lower surface, and many seams or Perforated decking are air discharge cavity upper surface in the face of the face of air discharge cavity, and described air discharge cavity lower surface is provided with at least two flow restricting outlets; Air discharge cavity isolation is become at least two independently sub-chambeies by described air discharge cavity dividing plate, each flow restricting outlets correspondence one independently sub-chamber.
The aircraft Supersonic Inlet that the present invention has a variable blow-off system by arranging multiple flow restricting outlets and removable air discharge cavity dividing plate discharging in the air discharge cavity under air cleft/hole more, can change by the size of mobile air discharge cavity dividing plate to each sub-chamber according to the work Mach number of Supersonic Inlet and attitude angle, every sub-chamber correspondence is stitched or the seam/number of perforations of Perforated decking more, the keying of flow restricting outlets regulates, in real time the deflation characteristic of lip cover Shock/Boundary-Layer interference is regulated, thus within the scope of wider operating envelope, obtain good Boundary layer flow effect, save discharge quantity, even also can close the venting stream in certain district where necessary.For this reason, employing of the present invention for widen Supersonic Inlet operating envelope scope, improve the aeroperformance such as total pressure recovery coefficient and coefficient of flow and all there is remarkable result.In addition, it is simple that the present invention also has structure, is easy to the advantages such as realization.
The control method that the present invention has the aircraft Supersonic Inlet of variable blow-off system can adopt following technical scheme:
When the work Mach number of inlet channel and attitude angle change, the position of lip cover Shock/Boundary-Layer interference phenomenon can move forward and backward thereupon, now air discharge cavity dividing plate moves under the driving of dividing plate connecting rod and dividing plate actuating device in air discharge cavity, and to the size in each sub-chamber, every sub-chamber correspondence is stitched more or the seam/number of perforations of Perforated decking, the keying of flow restricting outlets regulate and can change drain position and the discharge rate of boundary 1ayer; Comprise: when flight Mach number increases, the position of lip cover Shock/Boundary-Layer interference phenomenon is moved in inlet channel, and now air discharge cavity dividing plate moves to direction in inlet channel; When flight Mach number reduces, the position of lip cover Shock/Boundary-Layer interference phenomenon is moved outside inlet channel, and now the position of air discharge cavity dividing plate is moved to direction outside inlet channel; Further, due to flight Mach number lower time lip cover shock wave in first shock incidence at the bossing of inlet channel lower surface, cause Shock/Boundary-Layer interference phenomenon to die down, make air discharge cavity dividing plate be closed by that flow restricting outlets near outside for this reason.
Accompanying drawing explanation
Fig. 1 is the cross-sectional view that the present invention has the aircraft Supersonic Inlet of variable blow-off system.
Fig. 2 (a), Fig. 2 (b), Fig. 2 (c) are the working state figures that the present invention has the aircraft Supersonic Inlet of variable blow-off system.Wherein Fig. 2 (a) is constitution diagram when air discharge cavity to be divided into multiple independently sub-chamber by air discharge cavity dividing plate; Fig. 2 (b) is constitution diagram when air discharge cavity dividing plate moves to direction in inlet channel when flight Mach number increases; Fig. 2 (c) is when flight Mach number reduces, constitution diagram when air discharge cavity dividing plate moves to direction outside inlet channel.
detailed description of the invention
Refer to Fig. 1, the invention discloses a kind of aircraft Supersonic Inlet with variable blow-off system, it comprises supersonic speed precursor compressing surface 1, inlet channel lip cover 2, inlet channel side plate 3, the inner panel 30 extended internally from supersonic speed precursor compressing surface 1, the inlet channel expansion segment 5 that extends internally from inlet throat 4, and this inlet channel expansion segment 5 exports and is connected with turbine or punching engine 13; Inlet throat 4 is formed between described inlet channel lip cover 2 and inner panel 30; Described inner panel 30 is provided with air discharge cavity 7, cover in air discharge cavity 7 and towards many seams of inlet throat 4 or Perforated decking 6, be positioned at air discharge cavity 7 air discharge cavity dividing plate 8, connect the dividing plate connecting rod 9 of air discharge cavity dividing plate 8, the dividing plate actuating device 10 of connecting partition connecting rod 9; The bottom of described air discharge cavity 7 is air discharge cavity lower surface 19, many seams or Perforated decking 6 are air discharge cavity upper surface 18 in the face of the face of air discharge cavity 7, and described air discharge cavity lower surface 19 is provided with the quantity more than the quantity of air discharge cavity dividing plate 8 one all the time of at least two flow restricting outlets 11(flow restricting outlets 11); Air discharge cavity 7 isolation is become at least two independently sub-chambeies by described air discharge cavity dividing plate 8, each flow restricting outlets 11 correspondence one independently sub-chamber.The transverse shape of air discharge cavity dividing plate 8 is trapezoidal or rectangle, when needs air discharge cavity dividing plate 8 can realize flow restricting outlets 11 open and close function time, its transverse shape is designed to trapezoidal, otherwise is rectangle.
Described precursor compressing surface 1 is made up of 2 ~ 4 grades of slant compression plate/bent plates, and inlet throat 4 upstream portion of the inside face 12 of described inlet channel lip cover 2 is made up of the swash plate of less than three sections, and one-level swash plate wherein can be replaced bent plate.
Leading edge seamed edge 23 one end of described inlet channel side plate 3 is connected with the leading edge cusp of inlet channel lip cover 2, the other end can be connected with the leading edge cusp of inlet channel precursor compressing surface 1, also can be connected with the at a point on precursor compressing surface 1 seamed edge of inlet throat 4 upstream, any one as shown in leading edge seamed edge 24.
The aircraft Supersonic Inlet with variable blow-off system of the present invention can according to the work Mach number of Supersonic Inlet and attitude angle change by mobile air discharge cavity dividing plate 8 to the size in each sub-chamber, every sub-chamber correspondence is stitched more or the seam/number of perforations of Perforated decking 6, the keying of flow restricting outlets 11 regulate.The concrete effect produced in inlet channel working process, refer to Fig. 2 (a), described precursor compressing surface 1 is generally made up of multiple inclined-plane, operationally can produce multiple tracks precursor oblique shock wave 14, and described lip cover inner surface 12 also can induce one or multi-channel lip cover shock wave 15.The boundary 1ayer 16 that lip cover shock wave 15 and precursor compressing surface 1 develop interacts, and namely defines a place or many places Shock/Boundary-Layer interference phenomenon 17.In order to avoid causing significant flow losses and wild effect, often locating near lip cover Shock/Boundary-Layer interference phenomenon 17, seam more than being all provided with or breaker plate 6, air discharge cavity 7 and flow restricting outlets 11 carry out venting process to boundary 1ayer 16.Due to the continuous compression along with lip cover shock wave 15, air flow pressure everywhere near Shock/Boundary-Layer interference phenomenon 17 also constantly can raise along flow direction, in order to avoid the flowing in air discharge cavity 7 forms crossfire coupling because pressure reduction is different, the air discharge cavity dividing plate 8 used can play buffer action, air discharge cavity 7 is divided into multiple independently sub-chamber, and corresponding with it by a flow restricting outlets 11 respectively, namely there is the feature that many air discharge cavity control.Further, the upper surface 18 of described air discharge cavity 7, lower surface 19 are designed to two planes parallel to each other.When the work Mach number of inlet channel and attitude angle change, the position of lip cover Shock/Boundary-Layer interference phenomenon 17 can move forward and backward thereupon, now air discharge cavity dividing plate 8 moves under the driving of dividing plate connecting rod 9 and dividing plate actuating device 10 in air discharge cavity 7, to the size in each sub-chamber, every sub-chamber correspondence is stitched or the seam/number of perforations of Perforated decking 6 more, the keying of flow restricting outlets 11 regulates, therefore drain position and the discharge rate of boundary 1ayer 16 can be changed, that is the adjustment achieved deflation characteristic, thus within the scope of the operating envelope of broadness, obtain good Shock/Boundary-Layer interference control effects.Further, two kinds of situations are specifically comprised:
(1), as shown in Fig. 2 (b), when flight Mach number increases, the position of lip cover Shock/Boundary-Layer interference phenomenon 17 is moved in inlet channel, and now air discharge cavity dividing plate 8 moves to direction in inlet channel;
(2), as shown in Figure 2 (c), when flight Mach number reduces, the position of lip cover Shock/Boundary-Layer interference phenomenon 17 is moved outside inlet channel, and now the position of air discharge cavity dividing plate 8 is moved to direction outside inlet channel; Further, because the first shock incidence in now lip cover shock wave 18 is at the bossing 20 of inlet channel lower surface, cause Shock/Boundary-Layer interference phenomenon 21 to die down, air discharge cavity dividing plate 8 can be utilized for this reason to be closed by that flow restricting outlets 11 near outside.
The method and access of this technical scheme of specific implementation of the present invention is a lot, and the above is only the preferred embodiment of the present invention.It should be pointed out that for those skilled in the art, under the premise without departing from the principles 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 (5)
1. there is an aircraft Supersonic Inlet for variable blow-off system, it is characterized in that: comprise supersonic speed precursor compressing surface (1), inlet channel lip cover (2), inlet channel side plate (3), the inner panel (30) that extends internally from supersonic speed precursor compressing surface (1); Inlet throat (4) is formed between described inlet channel lip cover (2) and inner panel (30); Described inner panel (30) is provided with air discharge cavity (7), cover air discharge cavity (7) upper and towards many seams of inlet throat (4) or Perforated decking (6), be positioned at air discharge cavity (7) air discharge cavity dividing plate (8), connect the dividing plate connecting rod (9) of air discharge cavity dividing plate (8), the dividing plate actuating device (10) of connecting partition connecting rod (9); The bottom of described air discharge cavity (7) is air discharge cavity lower surface (19), many seams or Perforated decking (6) are air discharge cavity upper surface (18) in the face of the face of air discharge cavity (7), and described air discharge cavity lower surface (19) is provided with at least two flow restricting outlets (11); Air discharge cavity (7) isolation is become at least two independently sub-chambeies by described air discharge cavity dividing plate (8), each flow restricting outlets (11) correspondence one independently sub-chamber.
2. the aircraft Supersonic Inlet with variable blow-off system according to claim 1, it is characterized in that: comprise the inlet channel expansion segment (5) extended internally from inlet throat (4) further, the outlet of this inlet channel expansion segment (5) is connected with turbine or punching engine (13).
3. the aircraft Supersonic Inlet with variable blow-off system according to claim 1 and 2, is characterized in that: the quantity of flow restricting outlets (11) more than the quantity of air discharge cavity dividing plate (8) one all the time.
4. the aircraft Supersonic Inlet with variable blow-off system according to claim 3, it is characterized in that: the transverse shape of air discharge cavity dividing plate (8) is trapezoidal or rectangle, when needs air discharge cavity dividing plate (8) can realize flow restricting outlets (11) keying function, its transverse shape is designed to trapezoidal, otherwise is rectangle.
5. one kind has the control method of the aircraft Supersonic Inlet of variable blow-off system as claimed in claim 1, it is characterized in that: when the work Mach number of inlet channel and attitude angle change, the position of lip cover Shock/Boundary-Layer interference phenomenon (17) can move forward and backward thereupon, now air discharge cavity dividing plate (8) is mobile in air discharge cavity (7) under the driving of dividing plate connecting rod (9) and dividing plate actuating device (10), to the size in each sub-chamber, every sub-chamber correspondence is stitched or the seam/number of perforations of Perforated decking (6) more, the keying of flow restricting outlets (11) is carried out regulating and can change drain position and the discharge rate of boundary 1ayer (16), comprise:
When flight Mach number increases, the position of lip cover Shock/Boundary-Layer interference phenomenon (17) is moved in inlet channel, and now air discharge cavity dividing plate (8) moves to direction in inlet channel;
When flight Mach number reduces, the position of lip cover Shock/Boundary-Layer interference phenomenon (17) is moved outside inlet channel, and now the position of air discharge cavity dividing plate (8) is moved to direction outside inlet channel; And, because the first shock incidence in now lip cover shock wave (18) is at the bossing (20) of inlet channel lower surface, cause Shock/Boundary-Layer interference phenomenon (21) to die down, air discharge cavity dividing plate (8) can be utilized for this reason to be closed by that flow restricting outlets (11) near outside.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410158906.6A CN103950543B (en) | 2014-04-18 | 2014-04-18 | Aircraft supersonic air inlet channel with variable deflation system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410158906.6A CN103950543B (en) | 2014-04-18 | 2014-04-18 | Aircraft supersonic air inlet channel with variable deflation system |
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| CN103950543A CN103950543A (en) | 2014-07-30 |
| CN103950543B true CN103950543B (en) | 2015-02-11 |
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| CN104401498B (en) * | 2014-11-19 | 2017-04-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Adaptive bulging air inlet channel deformation driving device based on flexible skin |
| CN104819056B (en) * | 2015-05-05 | 2016-06-15 | 江西洪都航空工业集团有限责任公司 | A kind of DSI air intake duct mixing compression profile and building method thereof |
| CN106225606B (en) * | 2016-07-29 | 2018-10-12 | 江西洪都航空工业集团有限责任公司 | A kind of Supersonic Inlet boundary layer control device |
| IT201600086511A1 (en) * | 2016-08-22 | 2018-02-22 | Gen Electric | Air intake systems and related assembly methods |
| CN107091158B (en) * | 2017-06-08 | 2018-05-18 | 南京航空航天大学 | Low extrernal resistance surpasses/hypersonic inlet and Shock/Boundary-Layer interference control method |
| CN108533405B (en) * | 2018-03-19 | 2019-06-14 | 南京航空航天大学 | Two-dimensional supersonic inlet with aerial drainage air cleft |
| CN109606707A (en) * | 2018-10-26 | 2019-04-12 | 南京理工大学 | A kind of wide area Supersonic Inlet based on plasma flow control |
| CN110059417B (en) * | 2019-04-22 | 2023-05-23 | 南京航空航天大学 | Binary supersonic air inlet self-starting performance prediction method |
| CN110043368A (en) * | 2019-05-22 | 2019-07-23 | 中国科学院工程热物理研究所 | A kind of inlet structure and preparation method thereof |
| CN110805495B (en) * | 2019-12-05 | 2021-10-01 | 江西洪都航空工业集团有限责任公司 | Fixed-geometry wide-speed-range supersonic air inlet, working method thereof and aircraft |
| CN111255569B (en) * | 2020-01-13 | 2021-06-22 | 南京航空航天大学 | Mode conversion and variable geometry combined adjusting internal parallel type air inlet and control method |
| CN113074048B (en) * | 2021-03-18 | 2022-02-08 | 南京航空航天大学 | Hypersonic-speed continuously-adjustable air bleeding channel design method |
| CN113107680B (en) * | 2021-04-21 | 2022-04-19 | 南京航空航天大学 | Hypersonic-speed high-internal-contraction-ratio air inlet channel with stepless adjustable air release valve and control method |
| CN113107681B (en) * | 2021-04-21 | 2022-02-08 | 南京航空航天大学 | Continuously adjustable air inlet duct air bleeding device |
| CN114263533B (en) * | 2021-12-20 | 2023-06-27 | 中国人民解放军国防科技大学 | Shock wave/boundary layer interference control device and adaptive control method based on secondary flow circulation array |
| CN114458448B (en) * | 2022-01-26 | 2023-05-26 | 南京航空航天大学 | Self-adaptive suction orifice plate for inhibiting shock wave boundary layer interference |
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| JP3050860B1 (en) * | 1998-12-25 | 2000-06-12 | 川崎重工業株式会社 | Supersonic intake and method of starting the same |
| US6793175B1 (en) * | 1999-08-25 | 2004-09-21 | The Boeing Company | Supersonic external-compression diffuser and method for designing same |
| RU2353550C1 (en) * | 2007-11-26 | 2009-04-27 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" | Air intake with variable geometry for supersonic aircraft (versions) |
| US8974177B2 (en) * | 2010-09-28 | 2015-03-10 | United Technologies Corporation | Nacelle with porous surfaces |
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