CN106218913A - Turbine ejector - Google Patents
Turbine ejector Download PDFInfo
- Publication number
- CN106218913A CN106218913A CN201610738820.XA CN201610738820A CN106218913A CN 106218913 A CN106218913 A CN 106218913A CN 201610738820 A CN201610738820 A CN 201610738820A CN 106218913 A CN106218913 A CN 106218913A
- Authority
- CN
- China
- Prior art keywords
- main frame
- aircraft
- ejector
- turbine
- turbogenerator
- 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.)
- Granted
Links
- 239000002828 fuel tank Substances 0.000 claims abstract description 10
- 230000001133 acceleration Effects 0.000 claims description 7
- 235000007164 Oryza sativa Nutrition 0.000 claims description 4
- 235000009566 rice Nutrition 0.000 claims description 4
- 239000007787 solid Substances 0.000 claims 2
- 240000007594 Oryza sativa Species 0.000 claims 1
- 238000012423 maintenance Methods 0.000 abstract description 9
- 230000007903 penetration ability Effects 0.000 abstract description 3
- 241000209094 Oryza Species 0.000 description 3
- 238000011065 in-situ storage Methods 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 210000000080 chela (arthropods) Anatomy 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
- B64F1/06—Ground or aircraft-carrier-deck installations for launching aircraft using catapults
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Jet Pumps And Other Pumps (AREA)
- Braking Arrangements (AREA)
Abstract
nullThe present invention relates to turbine ejector，Can effectively solve the problem that carrier-based aircraft launches，Technical scheme is，The fuel tank being contained on main frame including main frame、Turbogenerator、Power supply and controller，Road wheel it is provided with bottom main frame，The front hydraulic tongs being connected with aircraft pintle it is provided with on the main frame in main frame direction of travel front，The posterior fixation devices for stationary body frame it is provided with on the main frame at direction of travel rear，The oil-out of fuel tank is connected with the oil-in of turbogenerator by oil pipe，The present invention can be under the structure situation not changing existing aircraft carrier，It is rapidly assembled and disassembled，And can use with control，Easy to maintenance，Take up an area little，Save big quantity space，Penetration ability is strong，Maintenance is convenient，Good work environment，Working cycle is short，Quick requirement can be reached，And it is safe and reliable，Can the most more transducer set after damage，And can on-the-spot change，The turbine power of ejector can be determined according to take-off weight，As long as power reaches requirement.
Description
Technical field
The present invention relates to aircraft ejection kit, particularly a kind of turbine ejector.
Background technology
In existing aircraft catapult, disclosed in have steam ejector and Electromagnetical ejector two kinds, steam ejector lead to
Crossing use and have multinomial technological difficulties, it is difficult to safeguard, be not suitable for the needs of modern aircraft carrier, electromagnetic launch is the product developed in recent years
Product, are integrated in technical difficulty on aircraft carrier big, are better than steam and launch, and but without under battle conditions, the big cost of difficulty is high-leveled and difficult in maintenance,
Specifically:
Steam catapult: produce complexity, technology requires High Temperature High Pressure, and difficulty is big, poor working environment, fragile maintenance difficulty
Greatly, equipment occupation space is big, and each operating interval time is long, does not reaches the demand of quickly lift-off, and big parts can not be changed；
Electromagnetical ejector: reliable operation is single, can work the most continuously, but frequency conversion rectifier difficulty is big, and power subsystem accounts for greatly
Space, and complex circuit, because of power supply high temperature impact work continuously, maintenance difficulty is big, changes inconvenience.
Therefore, its innovation is imperative.
Summary of the invention
For above-mentioned situation, for overcoming the defect of prior art, the purpose of the present invention is just to provide a kind of turbine ejector,
Can effectively solve the problem that carrier-based aircraft launches.
The technical scheme that the present invention solves is, a kind of turbine ejector, the fuel tank that is contained on main frame including main frame, whirlpool
Turbine, power supply and controller, be provided with road wheel bottom main frame, the main frame in main frame direction of travel front is arranged
There is the front hydraulic tongs being connected with aircraft pintle, the main frame at direction of travel rear is provided with and fixes for the rear of stationary body frame
Device, the oil-out of fuel tank is connected with the oil-in of turbogenerator by oil pipe, and power supply is connected with controller, and controller is through control
Line processed is connected with turbogenerator, front hydraulic tongs and posterior fixation devices respectively, for controlling the keying of turbogenerator and front liquid
Pressing tongs, the connection status of posterior fixation devices, during use, be placed on turbine ejector on the deck of aircraft carrier, be positioned at aircraft
Takeoff runway rear end, when aircraft needs catapult-assisted take-off, is passed through front hydraulic tongs by the front end of controller operating main body frame and is flown
Tail hook lock even, by posterior fixation devices with the pillar lock being fixedly installed on aircraft-carrier-deck even, open by the rear end of stake body
Turbogenerator on dynamic main frame and aircraft, when initial acceleration reaches 20m/s2, the posterior fixation devices solution of turbine ejector
Lock, turbine ejector runs forward together with aircraft, and turbine ejector acceleration implementation aircraft moves ahead after 40-50 rice, unclamps turbine bullet
The front hydraulic tongs of emitter front end, aircraft takes off under the own dynamic action of powerful inertia and aircraft, and turbine ejector is simultaneously
Brake, hooks after the resistance hurdle rope on aircraft-carrier-deck slows down by walking samsara finally by the pintle being arranged on main frame
To in situ, carry out launching next time.
Present configuration novelty is unique, and advantages of simple quickly can be pacified under the structure situation not changing existing aircraft carrier
Assembly and disassembly, are suitable for aircraft carrier and launch fighter plane, transporter, unmanned plane, increase and decrease according to launching load, and can be with control
Use, easy to maintenance, to take up an area little, save big quantity space, penetration ability is strong, and maintenance is convenient, good work environment, and the working cycle is short,
Quick requirement can be reached, and safe and reliable, after damage can the most more transducer set, and can on-the-spot change, can be according to aircraft
Take-off weight determines the turbine power of ejector, as long as power reaches requirement, easy to use, effective, is aircraft carrier
Innovation on aircraft ejection kit.
Accompanying drawing explanation
Fig. 1 is the axonometric chart of the present invention.
Detailed description of the invention
Below in conjunction with accompanying drawing, the detailed description of the invention of the present invention is described in further detail.
Being given by Fig. 1, the present invention includes fuel tank 2, turbogenerator 3, power supply 4 and the control that main frame 1 is contained on main frame
Device 5 processed, is provided with road wheel bottom main frame, the main frame in main frame direction of travel front is provided with and is connected with aircraft pintle
Front hydraulic tongs, the main frame at direction of travel rear is provided with the posterior fixation devices for stationary body frame, fuel tank 2 fuel-displaced
Mouthful being connected with the oil-in of turbogenerator 3 by oil pipe 9, power supply 4 is connected with controller, controller through control line respectively with whirlpool
Turbine 3, front hydraulic tongs are connected with posterior fixation devices, for controlling keying and the front hydraulic tongs of turbogenerator, fixing afterwards
The connection status of device, during use, is placed on turbine ejector on the deck of aircraft carrier, is positioned at after taking off runway
End, when aircraft needs catapult-assisted take-off, by the front end of controller operating main body frame by front hydraulic tongs with airplane tail hook lock even,
The rear end of stake body by posterior fixation devices with the pillar lock being fixedly installed on aircraft-carrier-deck even, starts on main frame
Turbogenerator and aircraft, when initial acceleration reaches 20m/s2, the posterior fixation devices of turbine ejector unlocks, turbine ejector
Running forward together with aircraft, turbine ejector acceleration implementation aircraft moves ahead after 40-50 rice, unclamps the front liquid of turbine ejector front end
Pressing tongs, aircraft takes off under the own dynamic action of powerful inertia and aircraft, and turbine ejector brakes simultaneously, finally by setting
Return in situ by road wheel, under carrying out after putting the resistance hurdle rope deceleration that the pintle 6 on main frame hooks on aircraft-carrier-deck
Launching once.
For ensureing using effect, described front hydraulic tongs includes front hydraulic cylinder 12 and is arranged on the front pincers of front cylinder ends
13；
Described posterior fixation devices includes being arranged on the rear fixing bar 10 of rear end on main frame, and the end of rear fixing bar 10 sets
It is equipped with forceps major bolt 14, is fixedly installed on the pillar on aircraft-carrier-deck and is provided with the rear hydraulic tongs corresponding with forceps major bolt,
Rear hydraulic tongs includes rear hydraulic cylinder 16 and is arranged on rear cylinder ends and the rear binding clip 15 corresponding with forceps major bolt, rear hydraulic tongs
Being fixed on fixing seat 17, fixing seat is arranged on pillar；
Described road wheel has two groups, is lift, and one of which is the driving wheel 8 used during main frame advance, separately
One group is the reset line travelling wheel 11 used during main frame return, and the mode of lifting is routine techniques, as used hydraulic control, drives
Brake is set on driving wheel；
Described turbogenerator 3 has and is symmetricly set on 2 of main frame both sides；
The head of the trumpet 7 for refueling it is provided with on described fuel tank 2；
Described controller through control line respectively with turbogenerator, front hydraulic cylinder and after hydraulic cylinder be connected, overall to it
Work controls comprehensively, it should be noted that controller is commercially available prod (prior art) such as cyclelog, and single-chip microcomputer control
Device 8051 processed etc., can be controlled the duty of turbogenerator, front hydraulic cylinder and rear hydraulic cylinder, and this technology is this
The technological means that skilled person is usual, time actually used, also can use Remote.
The working condition of the present invention is: is placed on the deck of aircraft carrier by turbine ejector, is positioned at and takes off race
Rear end, road, when aircraft needs catapult-assisted take-off, by the front end of controller operating main body frame by front hydraulic tongs and aircraft pintle
Lock even, makes aircraft integral with turbine ejector, walks together, can discharge aircraft simultaneously in walking process in time, allows aircraft
Free flight, the rear end of stake body by posterior fixation devices with the pillar lock being fixedly installed on aircraft-carrier-deck even, starts
Turbogenerator on main frame and aircraft, when initial acceleration reaches 20m/s2, the posterior fixation devices of turbine ejector unlocks,
Turbine ejector runs forward together with aircraft, and turbine ejector acceleration implementation aircraft moves ahead after 40-50 rice, unclamps turbine ejector
The front hydraulic tongs of front end, aircraft takes off under the own dynamic action of powerful inertia and aircraft, and turbine ejector brakes simultaneously,
Returned to former hook the resistance hurdle rope deceleration on aircraft-carrier-deck finally by the pintle 6 being arranged on main frame after by road wheel
Position, carries out launching next time.Compared with prior art, present configuration novelty is unique, advantages of simple, can not change existing
Under the structure situation of aircraft carrier, it is rapidly assembled and disassembled, is suitable for aircraft carrier and launches fighter plane, transporter, unmanned plane, root
Increase and decrease according to launching load, and can use with control, easy to maintenance, to take up an area little, save big quantity space, penetration ability is strong, maintenance
Convenient, good work environment, the working cycle is short, can reach quick requirement, and safe and reliable, can change rapidly one after damage
Set, and can on-the-spot change, the turbine power of ejector can be determined according to take-off weight, as long as power reaches requirement,
Easy to use, effective, it is the innovation on carrier-based aircraft catapult-launching gear.
Applicant, it is noted that the above-mentioned a kind of embodiment pointed out of the application, is not meant to limit this Shen
Protection domain please, every equivalent or equivalent alternative means are made the technical side the most identical with technical scheme
Case belongs to the protection domain of the application.
Claims (6)
1. a turbine ejector, it is characterised in that include fuel tank (2), turbogenerator that main frame (1) is contained on main frame
(3), power supply (4) and controller (5), be provided with road wheel bottom main frame, the main frame in main frame direction of travel front set
Being equipped with the front hydraulic tongs being connected with aircraft pintle, the main frame at direction of travel rear is provided with for stationary body frame is rear solid
Determining device, the oil-out of fuel tank (2) is connected with the oil-in of turbogenerator (3) by oil pipe (9), power supply (4) and controller
Being connected, controller is connected with turbogenerator (3), front hydraulic tongs and posterior fixation devices respectively through control line, during use, by turbine
Ejector is placed on the deck of aircraft carrier, is positioned at and takes off runway rear end, when aircraft needs catapult-assisted take-off, by control
By front hydraulic tongs with airplane tail hook lock even, posterior fixation devices is passed through with solid in the rear end of stake body in the front end of device operating main body frame processed
Surely the pillar lock being arranged on aircraft-carrier-deck even, starts the turbogenerator on main frame and aircraft, works as initial acceleration
Reach 20m/s2, the posterior fixation devices of turbine ejector unlocks, and turbine ejector runs forward together with aircraft, and turbine ejector adds
Speed implementation aircraft moves ahead after 40-50 rice, unclamps the front hydraulic tongs of turbine ejector front end, and aircraft is in powerful inertia and aircraft basis
Take off under body dynamic action, and turbine ejector brakes simultaneously, hook aviation finally by the pintle (6) being arranged on main frame
Resistance hurdle rope on mother ship carrier deck returns to original position by road wheel after slowing down, and carries out launching next time.
Turbine ejector the most according to claim 1, it is characterised in that described front hydraulic tongs includes front hydraulic cylinder (12)
With the front binding clip (13) being arranged on front cylinder ends.
Turbine ejector the most according to claim 1, it is characterised in that described posterior fixation devices includes being arranged on main body
The rear fixing bar (10) of rear end on frame, the end fixing bar (10) afterwards is provided with forceps major bolt (14), is fixedly installed on aircraft carrier
Being provided with the rear hydraulic tongs corresponding with forceps major bolt on pillar on deck, rear hydraulic tongs includes rear hydraulic cylinder (16) and is arranged on
Rear cylinder ends and the rear binding clip (15) corresponding with forceps major bolt.
Turbine ejector the most according to claim 1, it is characterised in that described road wheel has two groups, is lift,
One of which is the driving wheel (8) used during main frame advance, the reset line travelling wheel that another group uses when returning for main frame
(11)。
Turbine ejector the most according to claim 1, it is characterised in that described turbogenerator (3) is symmetrical arranged
In main frame both sides 2.
Turbine ejector the most according to claim 1, it is characterised in that be provided with for refueling on described fuel tank (2)
Head of the trumpet (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610738820.XA CN106218913B (en) | 2016-08-22 | 2016-08-22 | Turbine ejector |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610738820.XA CN106218913B (en) | 2016-08-22 | 2016-08-22 | Turbine ejector |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106218913A true CN106218913A (en) | 2016-12-14 |
| CN106218913B CN106218913B (en) | 2018-03-30 |
Family
ID=57555696
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610738820.XA Active CN106218913B (en) | 2016-08-22 | 2016-08-22 | Turbine ejector |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106218913B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107444668A (en) * | 2017-08-02 | 2017-12-08 | 杨长云 | Air catapult |
| CN109178335A (en) * | 2018-08-16 | 2019-01-11 | 刘贵文 | A kind of fan gas operated boosting aircraft catapult |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE326214C (en) * | 1917-07-18 | 1920-10-12 | Mercur Flugzeugbau G M B H | Launching device for aircraft |
| US3963196A (en) * | 1974-06-12 | 1976-06-15 | The United States Of America As Represented By The Secretary Of The Air Force | Aircraft/spacecraft ground accelerator |
| RU2027642C1 (en) * | 1990-06-07 | 1995-01-27 | Борис Михайлович Климович | Assisted flight vehicle take-off unit |
| CN201385785Y (en) * | 2009-03-31 | 2010-01-20 | 王力丰 | Aircraft carrier launching device |
| CN205186553U (en) * | 2015-07-06 | 2016-04-27 | 王振川 | Carry is in cluster carrier rocket catapult of balladeur train dolly |
-
2016
- 2016-08-22 CN CN201610738820.XA patent/CN106218913B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE326214C (en) * | 1917-07-18 | 1920-10-12 | Mercur Flugzeugbau G M B H | Launching device for aircraft |
| US3963196A (en) * | 1974-06-12 | 1976-06-15 | The United States Of America As Represented By The Secretary Of The Air Force | Aircraft/spacecraft ground accelerator |
| RU2027642C1 (en) * | 1990-06-07 | 1995-01-27 | Борис Михайлович Климович | Assisted flight vehicle take-off unit |
| CN201385785Y (en) * | 2009-03-31 | 2010-01-20 | 王力丰 | Aircraft carrier launching device |
| CN205186553U (en) * | 2015-07-06 | 2016-04-27 | 王振川 | Carry is in cluster carrier rocket catapult of balladeur train dolly |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107444668A (en) * | 2017-08-02 | 2017-12-08 | 杨长云 | Air catapult |
| CN107444668B (en) * | 2017-08-02 | 2021-01-15 | 杨长云 | Air ejector |
| CN109178335A (en) * | 2018-08-16 | 2019-01-11 | 刘贵文 | A kind of fan gas operated boosting aircraft catapult |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106218913B (en) | 2018-03-30 |
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