CN102817715A - Third-generation heavy fighter novel gas inlet channel lip - Google Patents
Third-generation heavy fighter novel gas inlet channel lip Download PDFInfo
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- CN102817715A CN102817715A CN2011101547892A CN201110154789A CN102817715A CN 102817715 A CN102817715 A CN 102817715A CN 2011101547892 A CN2011101547892 A CN 2011101547892A CN 201110154789 A CN201110154789 A CN 201110154789A CN 102817715 A CN102817715 A CN 102817715A
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- lip
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- folding
- inlet channel
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The invention discloses a third-generation heavy fighter novel gas inlet channel lip. The novel gas inlet channel lip comprises a gas inlet channel lip and a boundary layer separation plate, the fixed gas inlet channel lip of a present heavy fighter is changed to a retractable movable lip, the retractable movable lip is arranged on two sides of the front portion of the boundary layer separation plate through a hinge shaft, a movable lip folding and unfolding hydraulic actuation cylinder on a mounting joint on the inside wall of the air inlet channel is connected with a folding and unfolding pull rod on the rear portion of the inner end of the movable lip through a connection bolt to realize the folding and the unfolding of the movable lip, a fixed lip having a radius larger than the radius of the movable lip is arranged on the rear portion of the movable lip, and a rectification box having a leading edge radius same with the radius of the movable lip is arranged outside the hinge shaft, and enables the third-generation heavy fighter to have relatively large engine push force on a relatively short running track such as when the third-generation heavy fighter launches on an aircraft carrier or flights in a low-altitude and low-speed manner, and to correspondingly increase the launching weight, the fighting capability and the use flexibility of the fighter.
Description
Technical field:
The present invention relates to the military aviation device, particularly can obviously increase the novel inlet lip of third generation heavy weight fighter of motor power when third generation heavy weight fighter takes off and low-altitude low-speed flies.
Background technique:
The inlet lip of existing third generation heavy weight fighter is fixed; For making third generation heavy weight fighter have the flying speed more than two Mach; Adopted the less taper shape inlet lip of lip radius; This inlet lip is because the lip radius is less, the shock wave drag in the time of can reducing the above high-speed flight of two Mach numbers significantly.Fighter during with normal or high-speed flight as long as suck the air of suction port dead ahead or less amount; Just can satisfy the needs of motor; And when fighter when taking off and low-altitude low-speed when flight; Need to suck around the suction port or even the air at rear portion because speed is too little, to satisfy motor to the needs of air with increase the thrust of motor as far as possible.Because the lip radius of this inlet lip is less, can make the intake duct ambient air when flowing through suction port, produce separation, be unfavorable for that air gets into intake duct and influences air inflow; Can't make engine producing than high thrust,, be directly proportional and slide running velocity degree and takeoff thrust and ground run distance because the take-off weight of fighter and a root of runaway speed are directly proportional; Therefore; The reducing of takeoff thrust influenced sliding running velocity degree, and Gu Er has influenced the take-off weight of fighter again, in the ordinary course of things; Fighter can utilize long ground run distance to remedy the deficiency of takeoff thrust; The fight function is taken off with bigger take-off weight, can not influence the performance of fighter fighting capacity, and fighter is at short runway.Like the words of taking off with the no external force mode of taking off on the airplane carrier; Can can't prolong ground run distance again because of motor power is less; Can only take off with less relatively take-off weight, thereby obviously influence the performance of fighter fighting capacity, therefore; The inlet lip of existing third generation heavy weight fighter makes fighter that very big use narrow limitation arranged under a stable condition.
Summary of the invention:
The purpose of this invention is to provide a kind of novel inlet lip of third generation fighter that can increase third generation heavy weight fighter takeoff thrust.Technical solution of the present invention is accomplished as follows, and it includes inlet lip, boundary layer demarcation strip and air inlet road junction, it is characterized in that: the fixedly inlet lip that will have heavy weight fighter now has made the movable lip of deployable and collapsible into; Be installed in air inlet road junction boundary layer front part sides through hinging shaft; End rear portion at movable lip article has one to reel bar, a movable lip article folding and unfolding hydraulic actuator is arranged, through erection joint in the intake duct wall; Be installed in the intake duct wall; Link together through coupling bar and folding and unfolding pull bar, can make movable lip realize that packing up and decontrol movable lip rear portion is the bigger fixedly lip of relative lip radius, movable lip is decontroled when taking off with low-altitude low-speed flight; The bigger fixedly lip of relative lip radius is come out; Make air listen the place ahead from the air inlet road junction and get into intake duct on every side, increased the thrust of motor under this state, and movable lip is packed up when normal flight; Because the lip radius of movable lip is the same with the existing lip radius of third generation heavy weight fighter, can make fighter have the flight performance the same with having inlet lip now.Have identical air inflow for making movable inlet lip pack up the back with present inlet lip, inlet flow field and flight resistance coefficient have a leading-edge radius and the movable the same rectification box of lip radius outside hinging shaft; Can make movable lip the same with the intake duct of existing lip after packing up, separate, also can block the air entering intake duct of a part although the movable lip of decontroling also can make air-flow produce; And can produce certain resistance of air, but because movable lip has certain distance apart from the bigger fixedly lip of lip radius relatively after going into out, all less because of its area and volume again; Its influence to air inflow of Gu Er is very limited, and the resistance of air that produces also is very little, can not cause much influences to fighter basically; For reducing the rolling inertia of third generation heavy weight fighter when the roll; And do not influence the auxiliary intake valve on the intake duct, movable lip folding and unfolding pull bar and movable lip folding and unfolding hydraulic actuator are installed in the intake duct madial wall, because movable lip is the inlet lip that has to be separated do not increase supernumerary structure weight; Just increased the weight of movable lip folding and unfolding pull bar and movable lip folding and unfolding hydraulic actuator; Gu Er can obviously not increase the structure weight of fighter, because this invention can not exert an influence to the housing construction intensity of fighter using with place, the disjunct air inlet of fighter road junction; More can not reduce the maximum operating overload of fighter; Its air combat maneuvering performance is reduced, and this invention can make third generation heavy weight fighter at relatively short runway, for example on the airplane carrier; Have relatively large takeoff thrust when taking off with no external force mode; Thereby increase the take-off weight and the fighting capacity of fighter relatively, can make army, have sizable flexibility and less relatively use narrow limitation using on the third generation heavy weight fighter.
Description of drawings:
Accompanying drawing is a basic structure schematic representation of the present invention, and wherein 10 are the fixing lip lower edge of intake duct, and 13 are the air inlet road junction.
Embodiment:
The present invention is that the fixedly inlet lip with existing intake duct 15 is separated into movable lip 1 and the bigger fixedly lip 2 of lip radius relatively; And rectification box 3 is equipped with in bottom at the anterior two ends of boundary layer dividing plate 12; Movable lip is installed in the intake duct wall front upper part of both sides through hinging shaft 4; Movable lip folding and unfolding hydraulic actuator 7 is installed in the inside of intake duct madial wall 9 erection joint 8; Link together through the movable lip folding and unfolding pull bar 5 of coupling bar 6 with movable lip inside back, the same with existing third generation heavy weight fighter, on intake duct outer side wall 11, still leave auxiliary intake valve 14.
Claims (3)
1. the novel inlet lip of third generation heavy weight fighter; It includes inlet lip and boundary layer demarcation strip, it is characterized in that: the fixedly inlet lip that will have heavy weight fighter now has made the movable lip of deployable and collapsible into, is installed in air inlet road junction boundary layer demarcation strip front part sides through hinging shaft; There is a folding and unfolding pull bar at one end rear portion of movable lip; A movable lip folding and unfolding hydraulic actuator is arranged in airway walls, be installed in the airway walls, link together through coupling bar and movable lip folding and unfolding pull bar through erection joint; Can make variable lip pack up and decontrol, be the bigger fixedly lip of relative lip radius at the rear portion of movable lip.
2. like the novel inlet lip of claims 1 described a kind of third generation heavy weight fighter, it is characterized in that: leading-edge radius and the movable the same rectification box of lip radius are arranged outside hinging shaft.
3. like the novel inlet lip of claims 1 described a kind of third generation heavy weight fighter, it is characterized in that: movable lip folding and unfolding pull bar and movable lip folding and unfolding hydraulic actuator are installed in the intake duct madial wall.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011101547892A CN102817715A (en) | 2011-06-06 | 2011-06-06 | Third-generation heavy fighter novel gas inlet channel lip |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011101547892A CN102817715A (en) | 2011-06-06 | 2011-06-06 | Third-generation heavy fighter novel gas inlet channel lip |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102817715A true CN102817715A (en) | 2012-12-12 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011101547892A Pending CN102817715A (en) | 2011-06-06 | 2011-06-06 | Third-generation heavy fighter novel gas inlet channel lip |
Country Status (1)
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| CN (1) | CN102817715A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104346499A (en) * | 2014-11-19 | 2015-02-11 | 上海交通大学 | Multi-fan turbine engine design method based on computer platform |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2699906A (en) * | 1949-10-25 | 1955-01-18 | Northrop Aircraft Inc | Air inlet for airplane gaseous combustion turbine engines |
| US3430640A (en) * | 1964-02-17 | 1969-03-04 | Gen Electric | Supersonic inlet |
| US3664612A (en) * | 1969-12-22 | 1972-05-23 | Boeing Co | Aircraft engine variable highlight inlet |
| US3900177A (en) * | 1972-10-14 | 1975-08-19 | Rolls Royce 1971 Ltd | Jet propulsion powerplant |
| CN1382903A (en) * | 2002-03-21 | 2002-12-04 | 高恒伟 | Supersonic swirl boosted propulsion engine |
-
2011
- 2011-06-06 CN CN2011101547892A patent/CN102817715A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2699906A (en) * | 1949-10-25 | 1955-01-18 | Northrop Aircraft Inc | Air inlet for airplane gaseous combustion turbine engines |
| US3430640A (en) * | 1964-02-17 | 1969-03-04 | Gen Electric | Supersonic inlet |
| US3664612A (en) * | 1969-12-22 | 1972-05-23 | Boeing Co | Aircraft engine variable highlight inlet |
| US3900177A (en) * | 1972-10-14 | 1975-08-19 | Rolls Royce 1971 Ltd | Jet propulsion powerplant |
| CN1382903A (en) * | 2002-03-21 | 2002-12-04 | 高恒伟 | Supersonic swirl boosted propulsion engine |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104346499A (en) * | 2014-11-19 | 2015-02-11 | 上海交通大学 | Multi-fan turbine engine design method based on computer platform |
| CN104346499B (en) * | 2014-11-19 | 2017-10-10 | 上海交通大学 | A kind of windy turbofan engines design method based on computer platform |
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| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
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Application publication date: 20121212 |