CN106218913B - Turbine ejector - Google Patents
Turbine ejector Download PDFInfo
- Publication number
- CN106218913B CN106218913B CN201610738820.XA CN201610738820A CN106218913B CN 106218913 B CN106218913 B CN 106218913B CN 201610738820 A CN201610738820 A CN 201610738820A CN 106218913 B CN106218913 B CN 106218913B
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- CN
- China
- Prior art keywords
- main frame
- aircraft
- turbine
- ejector
- carrier
- 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.)
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Classifications
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- 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—Launching or towing gear
- B64F1/06—Launching or towing gear using catapults
Abstract
The present invention relates to turbine ejector,Can effectively solve the problems, such as carrier-based aircraft ejection,Technical scheme is,Including main frame the fuel tank on main frame,Turbogenerator,Power supply and controller,Main frame bottom is provided with road wheel,The preceding hydraulic tongs being connected with aircraft pintle is provided with main frame in front of main frame direction of travel,The posterior fixation devices for stationary body frame are provided with the main frame at direction of travel rear,The oil-out of fuel tank is connected by oil pipe with the oil inlet of turbogenerator,The present invention can be in the case where not changing the structure situation of existing aircraft carrier,It is rapidly assembled and disassembled,And it can be used with control,It is easy to maintenance,Take up an area small,Save big quantity space,Penetration ability is strong,Maintenance is convenient,Working environment is good,Work period is short,Quick requirement can be reached,It is and safe and reliable,Can more transducer set rapidly after damage,And can scene replacing,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 to have two kinds of steam ejector and Electromagnetical ejector, steam ejector leads to
Crossing use has multinomial technological difficulties, it is difficult to safeguards, be not suitable for the needs of modern aircraft carrier, electromagnetic launch is the production developed in recent years
Product, it is big to be integrated in technical difficulty on aircraft carrier, is launched better than steam, and but without under battle conditions, the big cost of difficulty is high-leveled and difficult in maintenance,
Specifically：
Steam catapult：Production is complicated, and technical requirements HTHP, difficulty is big, and working environment is poor, fragile maintenance difficulty
Greatly, equipment occupation space is big, each operating interval time length, does not reach the demand quickly gone up to the air, big part can not be changed；
Electromagnetical ejector：Reliable operation is single, quickly can continuously work, but frequency conversion rectifier difficulty is big, and power subsystem accounts for greatly
Space, and complex circuit, because power supply high temperature influences continuous work, maintenance difficulty is big, and it is inconvenient to change.
Therefore, its innovation is imperative.
The content of the invention
For the above situation, to overcome the defect of prior art, the purpose of the present invention is just to provide a kind of turbine ejector,
Can effectively solve the problems, such as carrier-based aircraft ejection.
The technical scheme that the present invention solves is a kind of turbine ejector, including fuel tank of the main frame on the main frame, whirlpool
Turbine, power supply and controller, main frame bottom are provided with road wheel, are set on the main frame in front of main frame direction of travel
There is the preceding hydraulic tongs being connected with aircraft pintle, the rear fixation for stationary body frame is provided with the main frame at direction of travel rear
Device, the oil-out of fuel tank are connected by oil pipe with the oil inlet of turbogenerator, and power supply is connected with controller, and controller is through control
Line processed is connected with turbogenerator, preceding hydraulic tongs and posterior fixation devices respectively, for the keying for controlling turbogenerator and preceding liquid
The connection status of pressing tongs, posterior fixation devices, in use, turbine ejector is placed on the deck of aircraft carrier, positioned at aircraft
Takeoff runway rear end, when aircraft needs catapult-assisted take-off, by the front end of controller operating main body frame by preceding hydraulic tongs with flying
Tail hook lock connects, and the rear end of stake body is locked by posterior fixation devices and the pillar being fixedly installed on aircraft-carrier-deck to be connected, and is opened
Turbogenerator and aircraft on dynamic main frame, when initial acceleration reaches 20m/s2, the posterior fixation devices solution of turbine ejector
Lock, turbine ejector are run forward together with aircraft, and turbine ejector accelerates after carrying out the forward 40-50 rice of aircraft, unclamps turbine bullet
The preceding hydraulic tongs of emitter front end, aircraft takes off under powerful inertia and aircraft itself dynamic action, and turbine ejector is simultaneously
Brake, hooked finally by the pintle being arranged on main frame after the resistance column rope on aircraft-carrier-deck slows down by samsara of walking
To original position, ejection next time is carried out.
Structure novel and unique of the present invention, advantages of simple can be in the case where not changing the structure situation of existing aircraft carrier, quick peace
Assembly and disassembly, it is suitable for aircraft carrier ejection fighter plane, transporter, unmanned plane, is increased and decreased according to ejection load, and can be with control
Use, easy to maintenance, occupation of land is small, saves big quantity space, and penetration ability is strong, and maintenance is convenient, and working environment is good, and the work period is short,
Quick requirement can be reached, and safe and reliable, after damage can more transducer set rapidly, and can scene change, can be according to aircraft
Take-off weight determines the turbine power of ejector, and easy to use as long as power reaches requirement, effect is good, is aircraft carrier
Innovation on aircraft ejection kit.
Brief description of the drawings
Fig. 1 is the stereogram of the present invention.
Embodiment
The embodiment of the present invention is described in further detail below in conjunction with accompanying drawing.
Provided by Fig. 1, the present invention includes fuel tank 2, turbogenerator 3, power supply 4 and control of the main frame 1 on main frame
Device 5 processed, main frame bottom are provided with road wheel, are provided with the main frame in front of main frame direction of travel and are connected with aircraft pintle
Preceding hydraulic tongs, be provided with the posterior fixation devices for stationary body frame on the main frame at direction of travel rear, fuel tank 2 it is fuel-displaced
Mouthful be connected by oil pipe 9 with the oil inlet of turbogenerator 3, power supply 4 is connected with controller, controller through control line respectively with whirlpool
Turbine 3, preceding hydraulic tongs are connected with posterior fixation devices, for controlling the keying and preceding hydraulic tongs, rear fixation of turbogenerator
The connection status of device, in use, turbine ejector is placed on the deck of aircraft carrier, after runway is taken off
End, when aircraft needs catapult-assisted take-off, connected by the front end of controller operating main body frame by preceding hydraulic tongs and airplane tail hook lock,
The rear end of stake body is locked by posterior fixation devices and the pillar being fixedly installed on aircraft-carrier-deck to be connected, and is started on main frame
Turbogenerator and aircraft, when initial acceleration reaches 20m/s2, the posterior fixation devices unblock of turbine ejector, turbine ejector
With being run forward together with aircraft, turbine ejector accelerates after carrying out the forward 40-50 rice of aircraft, unclamps the preceding liquid of turbine ejector front end
Pressing tongs, aircraft takes off under powerful inertia and aircraft itself dynamic action, and turbine ejector brakes simultaneously, finally by setting
Put and original position is returned to by road wheel after the resistance column rope that the pintle 6 on main frame is hooked on aircraft-carrier-deck slows down, carry out down
Ejection once.
To ensure using effect, described preceding hydraulic tongs includes preceding hydraulic cylinder 12 and is arranged on the preceding pincers of preceding cylinder ends
First 13；
Described posterior fixation devices include being arranged on the rear fix bar 10 of rear end on main frame, and the end of rear fix bar 10 is set
Forceps major bolt 14 is equipped with, is fixedly installed on and the rear hydraulic tongs corresponding with forceps major bolt is provided with the pillar on aircraft-carrier-deck,
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 afterwards
It is fixed in fixed seat 17, fixed seat is arranged on pillar；
Described road wheel has two groups, is lift, and one of which is the driving wheel 8 used when main frame advances, separately
One group is the reset road wheel 11 used when main frame returns, and the mode of lifting is routine techniques, and hydraulic control such as can be used, and is driven
Brake is set on driving wheel；
Described turbogenerator 3 has be symmetricly set on main frame both sides 2；
The head of the trumpet 7 for oiling is provided with described fuel tank 2；
Described controller through control line respectively with turbogenerator, preceding hydraulic cylinder and after hydraulic cylinder be connected, to its entirety
Work carry out comprehensively control, it is necessary to explanation, controller be commercially available prod (prior art) such as cyclelog, single-chip microcomputer control
Device 8051 processed etc., you can be controlled to the working condition of turbogenerator, preceding hydraulic cylinder and rear hydraulic cylinder, the technology is this
The usual technological means of art personnel, during actual use, it can also use Remote.
The present invention working condition be：Turbine ejector is placed on the deck of aircraft carrier, run positioned at taking off
Road rear end, when aircraft needs catapult-assisted take-off, preceding hydraulic tongs and aircraft pintle are passed through by the front end of controller operating main body frame
Lock connects, and makes aircraft and turbine ejector integral, walks together, while can discharge aircraft in walking process in time, allows aircraft
Free flight, the rear end of stake body is locked by posterior fixation devices and the pillar being fixedly installed on aircraft-carrier-deck to be connected, and is started
Turbogenerator and aircraft on main frame, when initial acceleration reaches 20m/s2, the posterior fixation devices unblock of turbine ejector,
Turbine ejector is run forward together with aircraft, and turbine ejector accelerates after carrying out the forward 40-50 rice of aircraft, unclamps turbine ejector
The preceding hydraulic tongs of front end, aircraft takes off under powerful inertia and aircraft itself dynamic action, and turbine ejector brakes simultaneously,
Hooked finally by the pintle 6 being arranged on main frame and original is returned to by road wheel after the resistance column rope on aircraft-carrier-deck slows down
Position, carries out ejection next time.Compared with prior art, structure novel and unique of the present invention, advantages of simple, can not change it is existing
Under the structure situation of aircraft carrier, it is rapidly assembled and disassembled, is suitable for aircraft carrier ejection fighter plane, transporter, unmanned plane, root
Increased and decreased according to ejection load, and can be used with control, easy to maintenance, occupation of land is small, saves big quantity space, and penetration ability is strong, maintenance
Convenient, working environment is good, and the work period is short, can reach quick requirement, and safe and reliable, can change one after damage rapidly
Set, and can scene change, the turbine power of ejector can be determined according to take-off weight, as long as power reaches requirement,
Easy to use, effect is good, is the innovation on carrier-based aircraft catapult-launching gear.
Applicant is not meant to limit this Shen it is noted that a kind of above-mentioned only embodiment pointed out of the application
Protection domain please, it is every to be made and technical scheme substantially identical technical side with equivalent or equivalent substitute means
Case belongs to the protection domain of the application.
Claims (4)
1. a kind of turbine ejector, it is characterised in that sent out including fuel tank (2), turbine of the main frame (1) on main frame
Motivation (3), power supply (4) and controller (5), main frame bottom are provided with road wheel, in front of main frame direction of travel
The preceding hydraulic tongs being connected with aircraft pintle is provided with main frame, is provided with the main frame at direction of travel rear for fixed master
The posterior fixation devices of body frame, the oil-out of fuel tank (2) are connected by oil pipe (9) with the oil inlet of turbogenerator (3),
Power supply (4) is connected with controller, controller through control line respectively with turbogenerator (3), preceding hydraulic tongs and after fixed fill
Put connected, in use, turbine ejector is placed on the deck of aircraft carrier, positioned at runway rear end is taken off, work as aircraft
When needing catapult-assisted take-off, connected by the front end of controller operating main body frame by preceding hydraulic tongs and airplane tail hook lock, stake body
Rear end is locked by posterior fixation devices and the pillar being fixedly installed on aircraft-carrier-deck to be connected, and starts the propeller for turboprop on main frame
Machine and aircraft, when initial acceleration reaches 20m/s2, the posterior fixation devices unblock of turbine ejector, turbine ejector and aircraft one
Rise and run forward, turbine ejector accelerates after carrying out the forward 40-50 rice of aircraft, unclamps the preceding hydraulic tongs of turbine ejector front end, flies
Machine takes off under powerful inertia and aircraft itself dynamic action, and turbine ejector brakes simultaneously, finally by being arranged on master
The resistance column rope that pintle (6) on body frame is hooked on aircraft-carrier-deck by road wheel returns to original position after slowing down, and carries out next
Secondary ejection；
The preceding binding clip (13) of cylinder ends before described preceding hydraulic tongs includes preceding hydraulic cylinder (12) and is arranged on；
Described posterior fixation devices include being arranged on the rear fix bar (10) of rear end on main frame, the end of rear fix bar (10)
Portion is provided with forceps major bolt (14), be fixedly installed on the pillar on aircraft-carrier-deck be provided with it is corresponding with forceps major bolt after
Hydraulic tongs, rear hydraulic tongs include rear hydraulic cylinder (16) and are arranged on rear cylinder ends and the rear binding clip corresponding with forceps major bolt
(15 )。
2. turbine ejector 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 when main frame advances, and another group is the reset road wheel used when main frame returns
(11 )。
3. turbine ejector according to claim 1, it is characterised in that described turbogenerator (3), which has, symmetrically to be set
Put 2 in main frame both sides.
4. turbine ejector according to claim 1, it is characterised in that be provided with described fuel tank (2) for adding
The head of the trumpet (7) of oil.
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 CN106218913A (en) | 2016-12-14 |
| CN106218913B true 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) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107444668B (en) * | 2017-08-02 | 2021-01-15 | 杨长云 | Air ejector |
| CN109178335B (en) * | 2018-08-16 | 2022-03-29 | 刘贵文 | Fan air guide type 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106218913A (en) | 2016-12-14 |
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