CN103950543A - 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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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 Flight Vehicle Design field, 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, bearing the multiple functions such as traffic capture and adjusting, incoming flow kinetic transformation and utilization, exit velocity size and homogeneity adjusting, upstream and downstream disturbance isolation, the work efficiency of propulsion system, operating envelope etc. are all being had to direct impact.Meanwhile, Supersonic Inlet is also on the interface in propulsion system and aircraft, therefore the aerodynamic characteristics of aircraft, structural weight, Stealth Fighter etc. are also had to remarkable impact.According to one's analysis, for conventional aero-turbine (flight Mach number is generally below 2.0), the every rising 1% of inlet total pres sure recovery coefficient, can make its thrust increase by 1.5%, unit fuel consumption rate declines 2.5%, and for the punching engine of higher Mach work, its total thrust more than 50% derive from complicated air inlet system and exhaust system.
Because the deceleration pressurization of supersonic flow need to rely on the compression wave systems such as shock wave to realize, and inlet channel also has boundary 1ayer development in its inside when sucking upstream body boundary 1ayer, therefore Shock/Boundary-Layer interference phenomenon is inevitable in Supersonic Inlet.And be subject to exit flow to be necessary for subsonic velocity restriction (conventionally export Mach number and be less than 0.6), the reduction ratio of importing and exporting air-flow in Supersonic Inlet is large (may reach 7:1) often, generally need to jointly complete by processes such as oblique shock wave supercharging, normal shock wave supercharging and subsonic velocity superchargings, this makes the Shock/Boundary-Layer interference problem facing in Supersonic Inlet become complicated and various.Conventionally, serious Shock/Boundary-Layer interference phenomenon can be brought out significant flow separation, and causes a series of adverse effect, as air intake port total pressure recovery coefficient reduces, distortion index increases, subcritical stability margin reduces or starting envelope curve dwindles etc.For this reason, it is the important flow phenomenon of a class troubling in all kinds of Supersonic Inlet pneumatic design and assessment all the time that Shock/Boundary-Layer disturbs, and wherein lip cover Shock/Boundary-Layer interference phenomenon is often outstanding.
In order to guarantee safety, the efficient operation within the scope of whole envelope curve, the Supersonic Inlet of most practicality all be unable to do without boundary 1ayer venting measure of control.This measure is a kind of active control technology, by many discharge air clefts or air bleed hole are set at lip cover Shock/Boundary-Layer interference range, and the pressure stabilizing cavity being attached thereto and current limliting outlet, such measure of control can be discharged near low energy air-flow between Shock/Boundary-Layer interference range outside inlet channel, therefore can control effectively to Shock/Boundary-Layer interference phenomenon.Yet, for the Supersonic Inlet of wide range of Mach numbers work, in its passage, may there is many places Shock/Boundary-Layer interference phenomenon, and along with this interference range position of variation and the interference strength at flight Mach number, flight attitude angle also can change thereupon, existing boundary 1ayer venting is controlled and be difficult to successfully manage.For this reason, need to develop a kind of novel boundary 1ayer venting measure of control, with the actual condition according to inlet channel, deflation characteristic be regulated, thereby in wide region, remain on efficient state of a control.
Summary of the invention
For effectively thering is variable and Shock/Boundary-Layer interference phenomenon multi-region feature, the aircraft Supersonic Inlet that the invention provides a kind of variable blow-off system and use it in the wide Mach number Supersonic Inlet of inhibition.By venting seam or air bleed hole, air discharge cavity, current limliting outlet and removable air discharge cavity dividing plate are set at Shock/Boundary-Layer interference range, the present invention can regulate deflation characteristic according to the actual condition of inlet channel, thereby obtain within the scope of wider Mach number and the angle of attack, controls preferably effect.
For achieving the above object, the aircraft Supersonic Inlet that the present invention has variable blow-off system can adopt following technical scheme:
An aircraft Supersonic Inlet with variable blow-off system, comprises supersonic speed precursor compressing surface, inlet channel lip cover, inlet channel side plate, the inner panel extending internally from supersonic speed precursor compressing surface; Between described inlet channel lip cover and inner panel, form inlet throat; Described inner panel is provided with air discharge cavity, covers in air discharge cavity and towards many seams or the Perforated decking of inlet throat, the air discharge cavity dividing plate that is positioned at air discharge cavity, the dividing plate connecting rod that connects 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, stitch more or Perforated decking in the face of the face of air discharge cavity be air discharge cavity upper surface, described air discharge cavity lower surface is provided with at least two current limlitings outlets; Described air discharge cavity dividing plate becomes at least two independently sub-chambeies by air discharge cavity isolation, the corresponding sub-chamber independently of each current limliting outlet.
The present invention has the aircraft Supersonic Inlet of variable blow-off system by a plurality of current limliting outlets and removable air discharge cavity dividing plate being set in the air discharge cavity under many discharges air cleft/hole, can change by mobile air discharge cavity dividing plate the size to each sub-chamber according to the work Mach number of Supersonic Inlet and attitude angle, seam/the number of perforations of the many seams of every individual sub-chamber correspondence or Perforated decking, the keying of current limliting outlet regulates, the deflation characteristic in real time lip cover Shock/Boundary-Layer being disturbed regulates, thereby within the scope of wider operating envelope, obtain good boundary 1ayer and control effect, save discharge quantity, even also can close where necessary the venting stream in certain district.For this reason, employing of the present invention all has remarkable result for the aeroperformances such as operating envelope scope, raising total pressure recovery coefficient and coefficient of flow of widening Supersonic Inlet.In addition, the present invention also has simple in 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, to the seam/number of perforations of the size in each sub-chamber, the many seams of every individual sub-chamber correspondence or Perforated decking,, the keying of current limliting outlet regulates, can change drain position and the discharge rate of boundary 1ayer; Comprise: when flight Mach number increases, move in inlet channel the position of lip cover Shock/Boundary-Layer interference phenomenon, now air discharge cavity dividing plate moves to direction in inlet channel; When flight Mach number reduces, move outside inlet channel the position of lip cover Shock/Boundary-Layer interference phenomenon, and now the position of air discharge cavity dividing plate direction outside inlet channel moves; And, due to flight Mach number when lower first shock incidence in lip cover shock wave at the bossing of inlet channel lower surface, cause Shock/Boundary-Layer interference phenomenon to die down, make air discharge cavity dividing plate by that current limliting port closing 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.Constitution diagram when wherein Fig. 2 (a) is divided into a plurality of independently sub-chamber for air discharge cavity dividing plate by air discharge cavity; Constitution diagram when Fig. 2 (b) moves to direction in inlet channel for air discharge cavity dividing plate when flight Mach number increases; Fig. 2 (c) is for when flight Mach number reduces, the constitution diagram of air discharge cavity dividing plate when direction moves outside inlet channel.
the specific embodiment
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 extending internally from supersonic speed precursor compressing surface 1, the inlet channel expansion segment 5 extending internally from inlet throat 4, and these inlet channel expansion segment 5 outlets are connected with turbine or punching engine 13; Between described inlet channel lip cover 2 and inner panel 30, form inlet throat 4; Described inner panel 30 is provided with air discharge cavity 7, covers in air discharge cavity 7 and towards many seams or the Perforated decking 6 of inlet throat 4, the air discharge cavity dividing plate 8 that is positioned at air discharge cavity 7, the dividing plate connecting rod 9 that connects 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, the face that many seams or Perforated decking 6 are faced air discharge cavity 7 is air discharge cavity upper surface 18, and described air discharge cavity lower surface 19 is provided with the quantity of at least two current limlitings outlet 11(current limlitings outlet 11 all the time than many one of the quantity of air discharge cavity dividing plate 8); Described air discharge cavity dividing plate 8 becomes at least two independently sub-chambeies by air discharge cavity 7 isolation, the corresponding sub-chamber independently of each current limliting outlet 11.The transverse shape of air discharge cavity dividing plate 8 is trapezoidal or rectangle, and when needs air discharge cavity dividing plate 8 can be realized current limliting outlet 11 keying function, its transverse shape is designed to trapezoidal, otherwise is rectangle.
Described precursor compressing surface 1 is comprised 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 are comprised of three sections of following swash plates, and one-level swash plate is wherein replaceable is bent plate.
Leading edge seamed edge 23 one end of described inlet channel side plate 3 are 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 upstreams, 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 size by 8 pairs of each sub-chambeies of mobile air discharge cavity dividing plate, every many seam of sub-chamber correspondence or Perforated decking 6 seam/number of perforations, the keying of current limliting outlet 11 regulate.The concrete effect producing in inlet channel working process, refer to Fig. 2 (a), described precursor compressing surface 1 is generally comprised of a plurality of inclined-planes, 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 when work.The boundary 1ayer 16 developing on lip cover shock wave 15 and precursor compressing surface 1 interacts, and has formed a place or many places Shock/Boundary-Layer interference phenomenon 17.For fear of causing significant flow losses and wild effect, near every place lip cover Shock/Boundary-Layer interference phenomenon 17, be all provided with many seams or breaker plate 6, air discharge cavity 7 and current limliting outlet 11 to boundary 1ayer 16 processing of exitting.Due to the continuous compression along with lip cover shock wave 15, near air-flow pressure Shock/Boundary-Layer interference phenomenon 17 also can constantly raise along flow direction everywhere, for fear of flowing in air discharge cavity 7, because pressure reduction is different, forming crossfire is coupled, the air discharge cavity dividing plate 8 using can play buffer action, air discharge cavity 7 is divided into a plurality of independently sub-chambeies, and corresponding with it by a current limliting outlet 11 respectively, there is the feature that many air discharge cavity are controlled.And 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, size to each sub-chamber, seam/the number of perforations of the many seams of every individual sub-chamber correspondence or Perforated decking 6, the keying of current limliting outlet 11 regulates, therefore can change drain position and the discharge rate of boundary 1ayer 16, that is realized the adjusting to deflation characteristic, thereby within the scope of broad operating envelope, obtain good Shock/Boundary-Layer and disturb control effect.Further, specifically comprise two kinds of situations:
(1), as shown in Fig. 2 (b), when flight Mach number increases, move in inlet channel the position of lip cover Shock/Boundary-Layer interference phenomenon 17, 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, move outside inlet channel the position of lip cover Shock/Boundary-Layer interference phenomenon 17, and now the position of air discharge cavity dividing plate 8 direction outside inlet channel moves; And, due to the bossing 20 of the first shock incidence in lip cover shock wave 18 now at inlet channel lower surface, cause Shock/Boundary-Layer interference phenomenon 21 to die down, can utilize air discharge cavity dividing plate 8 that current limliting outlet 11 near outside is closed for this reason.
Method and the approach of this technical scheme of specific implementation of the present invention are 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.In the present embodiment not clear and definite each component part all available prior art realized.
Claims (6)
1. an aircraft Supersonic Inlet with variable blow-off system, 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) extending internally from supersonic speed precursor compressing surface (1); Between described inlet channel lip cover (2) and inner panel (30), form inlet throat (4); Described inner panel (30) is provided with air discharge cavity (7), covers in air discharge cavity (7) and towards many seams or the Perforated decking (6) of inlet throat (4), the air discharge cavity dividing plate (8) that is positioned at air discharge cavity (7), the dividing plate connecting rod (9) that connects 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), stitch more or Perforated decking (6) in the face of the face of air discharge cavity (7) be air discharge cavity upper surface (18), described air discharge cavity lower surface (19) is provided with at least two current limlitings outlets (11); Described air discharge cavity dividing plate (8) becomes at least two independently sub-chambeies by air discharge cavity (7) isolation, the corresponding sub-chamber independently of each current limliting outlet (11).
2. the aircraft Supersonic Inlet with variable blow-off system according to claim 1, it is characterized in that: further comprise the inlet channel expansion segment (5) extending internally from inlet throat (4), this inlet channel expansion segment (5) outlet 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: than the quantity of air discharge cavity dividing plate (8) many one all the time of the quantity of current limliting outlet (11).
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 be realized current limliting outlet (11) keying function, its transverse shape is designed to trapezoidal, otherwise is rectangle.
5. the aircraft Supersonic Inlet with variable blow-off system according to claim 1 and 2, it is characterized in that: described precursor compressing surface (1) is comprised of 2～4 grades of slant compression plate/bent plates, inlet throat (4) upstream portion of the inside face (12) of described inlet channel lip cover (2) is comprised of three sections of following swash plates, and one-level swash plate is wherein replaceable is bent plate.
6. a control method with 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), size to each sub-chamber, seam/the number of perforations of the many seams of every individual sub-chamber correspondence or Perforated decking (6), the keying of current limliting outlet (11) regulates and can change drain position and the discharge rate of boundary 1ayer (16), comprise:
When flight Mach number increases, move in inlet channel the position of lip cover Shock/Boundary-Layer interference phenomenon (17), and now air discharge cavity dividing plate (8) moves to direction in inlet channel;
When flight Mach number reduces, move outside inlet channel the position of lip cover Shock/Boundary-Layer interference phenomenon (17), and now position direction outside inlet channel of air discharge cavity dividing plate (8) moves; And, due to the bossing (20) of the first shock incidence in lip cover shock wave (18) now at inlet channel lower surface, cause Shock/Boundary-Layer interference phenomenon (21) to die down, can utilize air discharge cavity dividing plate (8) that current limliting outlet (11) near outside is closed for this reason.
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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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| CN201410158906.6A CN103950543B (en) | 2014-04-18 | 2014-04-18 | Aircraft supersonic air inlet channel with variable deflation system |
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| CN104401498A (en) * | 2014-11-19 | 2015-03-11 | 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 |
| CN104819056A (en) * | 2015-05-05 | 2015-08-05 | 江西洪都航空工业集团有限责任公司 | DSI air inlet with mix-compression profile surface and construction method of same |
| CN106225606A (en) * | 2016-07-29 | 2016-12-14 | 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 |
| CN107091158A (en) * | 2017-06-08 | 2017-08-25 | 南京航空航天大学 | Low extrernal resistance is super/hypersonic inlet and Shock/Boundary-Layer interference control method |
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| 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 |
| CN110059417A (en) * | 2019-04-22 | 2019-07-26 | 南京航空航天大学 | A kind of two-dimensional supersonic inlet self-starting performance prediction method |
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| CN114263533A (en) * | 2021-12-20 | 2022-04-01 | 中国人民解放军国防科技大学 | Shock wave/boundary layer interference control device based on secondary flow circulation array and self-adaptive control method |
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| CN104401498A (en) * | 2014-11-19 | 2015-03-11 | 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 |
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| CN106225606A (en) * | 2016-07-29 | 2016-12-14 | 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 |
| CN109689500A (en) * | 2016-08-22 | 2019-04-26 | 通用电气公司 | Gas handling system and its assemble method |
| CN109689500B (en) * | 2016-08-22 | 2022-06-14 | 通用电气公司 | Air intake system and method of assembling the same |
| CN107091158A (en) * | 2017-06-08 | 2017-08-25 | 南京航空航天大学 | Low extrernal resistance is super/hypersonic inlet and Shock/Boundary-Layer interference control method |
| 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 |
| CN108533405A (en) * | 2018-03-19 | 2018-09-14 | 南京航空航天大学 | Two-dimensional supersonic inlet with aerial drainage air cleft |
| 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 |
| CN110059417A (en) * | 2019-04-22 | 2019-07-26 | 南京航空航天大学 | A kind of two-dimensional supersonic 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 |
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| CN113107681A (en) * | 2021-04-21 | 2021-07-13 | 南京航空航天大学 | Continuously adjustable air inlet duct air bleeding device |
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| CN113107681B (en) * | 2021-04-21 | 2022-02-08 | 南京航空航天大学 | Continuously adjustable air inlet duct air bleeding device |
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| CN114542288A (en) * | 2022-01-10 | 2022-05-27 | 南京航空航天大学 | Self-adaptive flow-discharge hypersonic inlet channel |
| CN114542288B (en) * | 2022-01-10 | 2024-04-30 | 南京航空航天大学 | Self-adaptive drainage hypersonic air inlet channel |
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