CN102887230A - Re-improved inlet for third-generation light fighter - Google Patents
Re-improved inlet for third-generation light fighter Download PDFInfo
- Publication number
- CN102887230A CN102887230A CN2011102178128A CN201110217812A CN102887230A CN 102887230 A CN102887230 A CN 102887230A CN 2011102178128 A CN2011102178128 A CN 2011102178128A CN 201110217812 A CN201110217812 A CN 201110217812A CN 102887230 A CN102887230 A CN 102887230A
- Authority
- CN
- China
- Prior art keywords
- inlet channel
- inlet
- fighter
- generation light
- light fighter
- 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.)
- Pending
Links
Landscapes
- Characterised By The Charging Evacuation (AREA)
Abstract
The invention discloses a re-improved inlet for a third-generation light fighter, comprising an inlet side wall, an inlet lower wall and a boundary layer push bump. The front edge of the inlet lower wall is provided with an adjustable lower lip edge; the inlet side wall causes the upper edge firstly to be arranged outwards at the same horizontal position with a wing and then to be changed into an inward-retracting shape; and the bending position of the inlet side wall is provided with an obvious adjacent line. The re-improved inlet for the third-generation light fighter has the advantages that the radar cross section, flight drag, maintenance workload and structural weight of the third-generation light fighter are reduced; and the re-improved inlet allows the light fighter to fly at the speed of 2 Mach.
Description
Technical field:
The present invention relates to the aeroplane structure design field, particularly a kind ofly can reduce third generation light fighter radar return sectional area, flight resistance, maintenance workload and structural weight, can make again it with the third generation light fighter of two Mach of speed flights improved type inlet channel again simultaneously.
Background technology:
What active service third generation light fighter used is rectangle three wave system variable geometry inlet Cai Yongjinqidaojihechicunkebiandefangshi，Shi Boxihuos, no matter this inlet channel can make fighter plane is during with subsonic, transonic or supersonic flight, can make fighter plane have normal required suction quantity, can also fly with two Mach speed, make fighter plane have more comprehensive air battle airworthiness.But this inlet channel complex structure, weight are larger, the resistance that produces during flight is also larger, this inlet channel makes the radar return sectional area of fighter plane larger in addition, the vertical metal sheet of its sidewall such as same particularly, reflection strength to radar wave is larger, even if use the antiradar coatings effect also undesirable, make the difficult distance of being found by radar that reduces of fighter plane.Because this inlet channel inside has the movable parts such as air inlet adjustment plate and air inlet adjustment plate hydraulic actuator to need to safeguard, makes the maintenance workload of fighter plane larger.Recently in a period of time, on the up-to-date improved type of third generation light fighter, adopted a kind of improved type inlet channel, this inlet channel has adopted at present advanced in boundary-layer dividing plate supersonic inlet technology in the world.Because it adopts fixed inlet channel structure, therefore saved movable part and the structural weights such as air inlet adjustment plate and air inlet adjustment plate hydraulic actuator.Because this inlet channel can be in the same place with airframe structure, the structural weights such as boundary-layer dividing plate and reinforcement point have been saved again, the resistance when also having reduced fighter flight simultaneously.Block the radar wave that partly enters inlet channel inside owing to the boundary-layer that is positioned at this place, air inlet road junction pushes away bulge, therefore can significantly reduce the radar return sectional area in fighter plane dead ahead, be conducive to improve the stealthy level of fighter plane.This inlet channel so basically need not safeguard it, has been saved the maintenance workload of fighter plane because there is not movable part to need to safeguard.But because this inlet channel is fixed can't the adjusting suction quantity, and fighter plane suction quantity under different flying speeds is different, suction quantity can just meet requirements when normal flight to cause fighter plane, and suction quantity is very little in utmost point low-speed operations and when taking off, can't satisfy the driving engine needs and affect engine thrust, if too large again with the high-speed flight suction quantity, can make the engine operation mal even " surge " phenomenon can occur.Therefore cause the fighter plane maximum speed to fly less than two Mach, affected the air battle airworthiness of fighter plane.Because this inlet channel has been continued to use old-fashioned inlet channel shape, its sidewall is similarly vertical configuration and side direction radar return sectional area is not a bit reduced in addition.Above two kinds of inlet channels have certain weak point, can't satisfy the needs of fighter plane improving performance.
Summary of the invention:
The purpose of this invention is to provide a kind of minimizing third generation light fighter radar return sectional area, flight resistance, maintenance workload and structural weight, can make again simultaneously it with the third generation light fighter of two Mach of speed flights improved type inlet channel again.
Technical solution of the present invention is finished as follows, it still belongs to without boundary-layer dividing plate supersonic inlet, include inlet channel sidewall, inlet channel lower wall and boundary-layer and push away bulge, it is characterized in that: an adjustable lower lip is arranged in the forward position of inlet channel lower wall.This adjustable lower lip is slightly upwards packed up when normal flight, forms containing shape air inlet road junction, can on existing basis without attached area dividing plate supersonic inlet, further reduce the radar return sectional area in fighter plane dead ahead.General Design of Inlet scheme all is to calculate the inlet channel open area according to the normal flight speed of fighter plane, and generally all is as normal flight speed with about 300 meters of per seconds.When low-speed operations, increase suction quantity satisfying the needs of driving engine by auxiliary intake valve, and when high-speed flight by reducing the way of inlet channel open area and air relief, reduce suction quantity and make engine work and " surge " can not occur.And this third generation light fighter the improved type inlet channel walks again is opposite path, so that fighter plane can be to equal even to fly greater than two Mach speed when design inlet channel open area, be used as the calculating standard of inlet channel open area, and the area that increases the air inlet road junction when low-speed operations increases suction quantity to satisfy the needs of driving engine.This third generation light fighter is the improved type inlet channel again, mainly is to utilize adjustable lower lip to strengthen the admission port area to strengthen suction quantity, with the typhoon fighter plane identical thinking is arranged, but the typhoon fighter plane can't increase the admission port area.Adjustable lower lip is slightly upwards packed up when normal flight, when reducing the fighter radar reflection cross section, also blocked partial admission road open area, adjustable lower lip is concordant with the inlet channel lower wall when low-speed maneuver is flown, the area at air inlet road junction can be suitably increased, the suction quantity of inlet channel can be increased to a certain extent.But can increase in this state the radar return sectional area of fighter plane, but fighter plane generally all is just to carry out the fixed war of low-speed maneuver fistfight in visual range, this moment, whether fighter plane was stealthy unimportant, therefore can not reduce the fighting efficiency of fighter plane.Adjustable lower lip is downward-sloping when takeoff condition, although the inlet channel open area is increased, inlet channel lower wall lip radius is increased, and can increase equally the suction quantity of inlet channel when taking off, to satisfy driving engine to the demand of air.Adopt again improved type inlet channel of this third generation light fighter, can make fighter plane have existing without boundary-layer dividing plate supersonic inlet advantage in, can also have comparatively comprehensively air battle airworthiness, and have higher fighting efficiency.But because this third generation light fighter improved type inlet channel again can only appropriateness change the suction quantity of inlet channel, and can't change quantity and the position of inlet channel " shock wave ", exert an influence in the time of may between one Mach to two Mach, flying to fighter plane.Third generation light fighter uses the rectangle inlet channel, in order to make things convenient for the moving around in inlet channel of air inlet adjustment plate, but adopt without after the boundary-layer dividing plate supersonic inlet, just there is no need to have adopted the rectangle inlet channel, can adopt the inlet channel shape that can reduce side direction radar return sectional area fully.In general want to reduce the side direction radar return sectional area of inlet channel, preferably adopt the inlet channel sidewall of inclination.If but adopt complete exterior wing or the fully interior inlet channel sidewall of receiving, because the area at air inlet road junction does not change, can make inlet channel too give prominence to the fighter plane fuselage, make the fighter plane aerodynamic configuration not conform to area occupation ratio, can increase the flight resistance of fighter plane.This third generation light fighter is the sidewall of improved type inlet channel again, changes inside receipts during from the top first to exterior wing to the level attitude identical with wing into again, and tearing the crook open at it has and significantly adjoin together line, and the ship side profile of this profile and Stealth ship is more similar.Adopt this profile decapacitation to reduce beyond the widely different radar return sectional area of inlet channel, can also make inlet channel can obviously not give prominence to the fighter plane fuselage, add that its outshot and wing are on same level attitude, therefore can not make the aerodynamic configuration of fighter plane not conform to area occupation ratio, can not increase the flight resistance of fighter plane.Because this third generation light fighter is the improved type inlet channel again, mainly be in existing lower wall forward position without boundary-layer dividing plate supersonic inlet, increased an adjustable lower lip, therefore its structure is compared adjustable inlet channel and is wanted simple many, weight is also than light many of adjustable inlet channel, and the flight resistance that produces also is much smaller, the more important thing is its maintenance workload also than adjustable inlet channel lack many, need not pierce in the inlet channel and safeguard, the thing of relatively working hard and pierce inlet channel, particularly when fighter plane just lands.Because the adjustable lower lip volume and weight that its increases is all less, and does not increase the volume of inlet channel, therefore compare existingly without boundary-layer dividing plate supersonic inlet, the structural weight of its increase is less.Owing to only need to adjustable lower lip and its control mechanism be safeguarded, its maintenance workload is compared and existingly also can not increased much without the boundary-layer supersonic inlet.Therefore this third generation light fighter improved type inlet channel again has and can reduce third generation light fighter radar return sectional area, flight resistance, maintenance workload and structural weight, can make again it with the advantage of two Mach of speed flights simultaneously.
Description of drawings:
This accompanying drawing is takeoff condition of the present invention signal sketch, wherein 1 refers to boundary-layer and pushes away bulge, and 3 refer to the inlet channel sidewall adjoins line, and 4 refer to the leading edge wing root part of wing, and 8 refer under the head along part.
The specific embodiment:
The invention belongs to the improvement of prior art, mainly is in existing light-duty third generation fighter plane adjustable lower lip 7 of leading edge increase without boundary-layer dividing plate supersonic inlet lower wall 6.The inlet channel sidewall of perpendicular shape made into the shape that consisted of by 5 two parts of receiving portions in inlet channel sidewall exterior wing part 2 and the inlet channel sidewall, adjoin together line 3 in its bending part formation, and inlet channel sidewall outshot is on the identical level attitude with wing.
Claims (2)
1. third generation light fighter improved type inlet channel again, it includes inlet channel sidewall, inlet channel lower wall and boundary-layer and pushes away bulge, it is characterized in that: an adjustable lower lip is arranged in the forward position of inlet channel lower wall.
2. third generation light fighter improved type inlet channel again as claimed in claim 1 is characterized in that: the inlet channel sidewall cause the top to exterior wing to and change again the shape of interior receipts during wing par position into.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011102178128A CN102887230A (en) | 2011-07-22 | 2011-07-22 | Re-improved inlet for third-generation light fighter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011102178128A CN102887230A (en) | 2011-07-22 | 2011-07-22 | Re-improved inlet for third-generation light fighter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102887230A true CN102887230A (en) | 2013-01-23 |
Family
ID=47530949
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011102178128A Pending CN102887230A (en) | 2011-07-22 | 2011-07-22 | Re-improved inlet for third-generation light fighter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102887230A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043668A (en) * | 2016-07-06 | 2016-10-26 | 中国人民解放军海军航空工程学院 | Aerodynamic configuration of three-surface aircraft |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3430640A (en) * | 1964-02-17 | 1969-03-04 | Gen Electric | Supersonic inlet |
| US3879941A (en) * | 1973-05-21 | 1975-04-29 | Gen Electric | Variable cycle gas turbine engine |
| EP0810357A1 (en) * | 1996-05-28 | 1997-12-03 | Lockheed Martin Corporation | Diverting boundary layer air |
| CN1384794A (en) * | 1999-08-25 | 2002-12-11 | 波音公司 | Supersonic external-compression diffuser and method for designing same |
-
2011
- 2011-07-22 CN CN2011102178128A patent/CN102887230A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3430640A (en) * | 1964-02-17 | 1969-03-04 | Gen Electric | Supersonic inlet |
| US3879941A (en) * | 1973-05-21 | 1975-04-29 | Gen Electric | Variable cycle gas turbine engine |
| EP0810357A1 (en) * | 1996-05-28 | 1997-12-03 | Lockheed Martin Corporation | Diverting boundary layer air |
| CN1384794A (en) * | 1999-08-25 | 2002-12-11 | 波音公司 | Supersonic external-compression diffuser and method for designing same |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043668A (en) * | 2016-07-06 | 2016-10-26 | 中国人民解放军海军航空工程学院 | Aerodynamic configuration of three-surface aircraft |
| CN106043668B (en) * | 2016-07-06 | 2019-07-19 | 中国人民解放军海军航空大学 | Aerodynamic layout of a triplane aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US5407153A (en) | System for increasing airplane fuel mileage and airplane wing modification kit | |
| CN104691739B (en) | A high lift laminar airfoil with low drag and high drag divergent Mach number | |
| US3960345A (en) | Means to reduce and/or eliminate vortices, caused by wing body combinations | |
| CN206318014U (en) | A kind of trailing edge and the flying wing with it | |
| CN203666966U (en) | Canard wing configuration aircraft provided with movable strakes | |
| US20070262205A1 (en) | Retractable multiple winglet | |
| CN201023653Y (en) | Aerodynamic layout of large aspect ratio forward-swept wing aircraft | |
| US8317128B2 (en) | Laminar flow wing optimized for transonic cruise aircraft | |
| US20200156787A1 (en) | Double wing aircraft | |
| CN110498037B (en) | High lift-drag ratio laminar flow wing section suitable for low-altitude low-speed unmanned aerial vehicle | |
| CN106672205B (en) | Layout of a Large Variable Sweep Supersonic Aircraft | |
| CN103231795A (en) | Corporate aircraft engine upper placement and front swept wing duck type layout | |
| CN103171766A (en) | Short distance rising and landing unmanned all-wing aircraft | |
| CN109367795A (en) | Fuselage bilateral air inlet high-speed aircraft aerodynamic arrangement | |
| CN103419933B (en) | Based on wing layout vertically taking off and landing flyer before and after high lift device | |
| CN102826216A (en) | Aerodynamic configuration of aircraft | |
| CN105015795A (en) | Airplane design method and scheme | |
| CN203740128U (en) | Wave-rider aircraft | |
| CN113942651A (en) | A Novel Flight Control Device for SACCON Type Aircraft | |
| CN119389421A (en) | A wing tip trapped vortex lift enhancement device | |
| CN113148105A (en) | Double-head wing body fusion low-detectable layout | |
| CN113619772B (en) | Jet-type second grade spout circulation control wing section in coordination | |
| CN103171758A (en) | Lift-rising method of flying wing type airplane | |
| CN102887230A (en) | Re-improved inlet for third-generation light fighter | |
| CN208647149U (en) | A kind of UAV aerodynamic layout |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C05 | Deemed withdrawal (patent law before 1993) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20130123 |