CN103192995B - Rotary-piston type spring catapult - Google Patents
Rotary-piston type spring catapult Download PDFInfo
- Publication number
- CN103192995B CN103192995B CN201210587367.9A CN201210587367A CN103192995B CN 103192995 B CN103192995 B CN 103192995B CN 201210587367 A CN201210587367 A CN 201210587367A CN 103192995 B CN103192995 B CN 103192995B
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- China
- Prior art keywords
- piston
- aircraft
- ejector
- gear
- push rod
- 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.)
- Expired - Fee Related
Links
- 239000010721 machine oil Substances 0.000 claims abstract description 9
- 239000003921 oil Substances 0.000 claims description 16
- 230000006835 compression Effects 0.000 claims description 8
- 238000007906 compression Methods 0.000 claims description 8
- 239000010705 motor oil Substances 0.000 claims description 7
- 230000000694 effects Effects 0.000 claims description 6
- 239000000446 fuel Substances 0.000 claims description 6
- 239000000945 filler Substances 0.000 claims description 4
- 238000012423 maintenance Methods 0.000 abstract description 2
- 238000009434 installation Methods 0.000 abstract 1
- 238000000034 method Methods 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 2
- 239000004519 grease Substances 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- IWEDIXLBFLAXBO-UHFFFAOYSA-N dicamba Chemical compound COC1=C(Cl)C=CC(Cl)=C1C(O)=O IWEDIXLBFLAXBO-UHFFFAOYSA-N 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
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Abstract
The invention provides a kind of aircraft carrier catapult, especially a kind of rotary-piston type spring catapult, it is that carrier ship-board aircraft is when taking off, a kind of boost installation of carrier-borne aircraft takeoff speed can be improved, it is characterized in that: before taking off, after filling machine oil in cylinder sleeve, according to model and the size of aircraft, adjust gear, in take-off process, the semicircle piston of two panels is rotated and overlap gradually, machine oil before piston is discharged backward, make piston and spring assembly drag reduction forward, and expand rapidly when controlled, aircraft is driven to take off fast, energy-conserving and environment-protective of the present invention, structure is simple, maintenance is convenient, life-span is long, cost is low, occupy little space, it is current optimal carrier-based aircraft ejector in the world.
Description
Technical field
The invention provides a kind of aircraft carrier ejector, especially a kind of rotary-piston type spring catapult, belong to military domain.
Background technology
At present, have the majority state of aircraft carrier in the world, generally all adopt steam-type ejector, it is because maintaining enough steam for a long time, and slattern a large amount of fuel, its cylinder, piston must have higher sealing property, otherwise can make ejector under power, make safety when taking off can not get basic assurance.Present a few countries is studied, Electromagnetical ejector on probation is technical very strong, is difficult to grasp in the short time.Therefore, use in China's inconvenience.In decades, a lot of country, to spring loaded ereisma, has all carried out conscientiously studying, all because initial velocity is high, easily aviator and aircraft are caused damage, simultaneously again because acceleration/accel is low, make the speed that aircraft out of reach takes off, up to the present go back neither one country and really grasp or use this technology.
Summary of the invention
For above-mentioned deficiency, need to develop a kind of novel aircraft carrier ejector, make its economize energy, reduce costs, in view of this, present invention employs a kind of state-of-the-art rotary-piston type spring catapult, in order to the tension force of controlling spring group, it fills machine oil by before cylinder sleeve inner carrier, two panels piston is rotated gradually and overlap, machine oil is discharged backward, whole spring assembly is when reducing resistance, rapid expansion, aircraft is driven steadily to take off safely, advantage of the present invention is: energy-conserving and environment-protective, structure is simple, maintenance is convenient, long service life, occupy little space, it is a kind of optimal carrier-based aircraft ejector.
The present invention includes: oil is stopped device, push-rod piston, engine oil compression room, ejector sleeve rotating piston, hauling block, push rod, ejector sleeve, tractor, ejector shell, Push Rod Rack, fuel transfer pump, hauling rope, traction sheave, main shaft drive gear, motor gear, there is forward and reverse electrical motor, push rod driven wheel, spring back seat, sliding wheel, filler port, oil cabinet shell, store grease chamber, more piece spring assembly, front end transport pipe, brake wheel, main shaft, rear end transport pipe, ejector sleeve skewed slot etc., gear gim peg, gear hold down groove.
Accompanying drawing explanation
Below in conjunction with accompanying drawing, the present invention is described in detail
Figure <1> is the schematic diagram of existing rotating piston spring catapult
Figure <2> is the schematic diagram of ejector sleeve skewed slot
Figure <3> is the schematic diagram of push-rod piston
Figure <4> is the schematic diagram of pipe rotating piston
Figure <5> is the schematic diagram of gear hold down groove
Mark in accompanying drawing represents respectively: oil is stopped device (1), push-rod piston (2), engine oil compression room (3), ejector sleeve rotating piston (4), hauling block (5), push rod (6), ejector sleeve (7), tractor (8), ejector shell (9), Push Rod Rack (10), fuel transfer pump (11), hauling rope (12), traction sheave (13), main shaft drive gear (14), motor gear (16), there is forward and reverse electrical motor (15), push rod driven wheel (17), spring back seat (18), sliding wheel (19), filler port (20), oil cabinet shell (21), store grease chamber (22), more piece spring assembly (23), front end transport pipe (24), brake wheel (25), main shaft (26), rear end transport pipe (27), ejector sleeve skewed slot (28), gear gim peg (29), gear hold down groove (30), gear permanent seat (31).
Detailed description of the invention
<1> is first by ejector shell (9) with reference to the accompanying drawings, be arranged on below type aircraft carrier deck, ejector and aircraft carrier warship body keeping parallelism, push-rod piston (2) and push rod (6) are reinforced, push rod (6) other end establishes gear gim peg (29), then ejector shell (9) is put into, again ejector sleeve rotating piston (4) and ejector sleeve (7) are reinforced, then be enclosed within push rod (6), more piece spring assembly (23) is enclosed within ejector sleeve (7), by push rod driven wheel (17) and main shaft (26), ejector shell (9) rear end is fixed on bearing, by traction sheave (13) and main shaft drive gear (14), be fixed on one end of main shaft (26), brake wheel (25) is fixed on the other end of main shaft (26), motor gear (16), meshing with main shaft drive gear (14), hauling rope (12) one end connects traction sheave (13), the other end is connected by hauling block (5) and aircraft and tractor (8) and aircraft.Then mounting spring back seat (18), spring back seat (18) and oil cabinet shell (21) are reinforced, oil cabinet shell (21) upper end is established in filler port (20), oil cabinet shell (21), installs fixing multiple sliding wheel (19).Gear gim peg (29) is placed in gear hold down groove (30), gear permanent seat (31) and oil cabinet shell (21) are reinforced, establish fuel transfer pump (11) in front end transport pipe (24) and rear end transport pipe (27), two ends are respectively connected with ejector shell (9) and oil cabinet shell (21).
Machine oil is poured into by ejector after all parts install, then actuating motor makes it rotate forward at a slow speed, multistage spring assembly is compressed, piston is under the effect of ejector sleeve skewed slot, form positive round state gradually, at this moment machine oil enters engine oil compression room immediately, and hauling rope extends, and then starts brake gear and makes ejector be in arm-to-arm.When aircraft starts to take off, starting fuel transfer pump makes compression chamber inner engine oil fill, and adjust gear according to aircraft size, then turn-on reversal power supply, electrical motor is reversed, loosen brake gear simultaneously, make spring slow expansion, force push rod and ejector sleeve reach, ejector sleeve skewed slot is under the effect of push rod driven wheel, start to drive ejector sleeve and piston rotation, piston is made to form breach also overlapping gradually, at this moment the machine oil of engine oil compression room is altered immediately afterwards, the anterior pressure of piston gradually reduces, spring assembly is expanded gradually, the rotating speed of electrical motor is progressively accelerated, aircraft safety is taken off, piston oil stop device effect under stop moving ahead.
Claims (1)
1. a rotary-piston type spring catapult, it is characterized in that: by ejector shell (9), be arranged on below type aircraft carrier deck, ejector and aircraft carrier warship body keeping parallelism, push-rod piston (2) and push rod (6) are reinforced, push rod (6) other end establishes gear gim peg (29), then ejector shell (9) is put into, ejector sleeve rotating piston (4) and ejector sleeve (7) are reinforced, then be enclosed within push rod (6), more piece spring assembly (23) is enclosed within ejector sleeve (7), by push rod driven wheel (17) and main shaft (26), ejector shell (9) rear end is fixed on bearing, by traction sheave (13) and main shaft drive gear (14), be fixed on one end of main shaft (26), brake wheel (25) is fixed on the other end of main shaft (26), motor gear (16), meshing with main shaft drive gear (14), hauling rope (12) one end connects traction sheave (13), the other end is connected by hauling block (5) and aircraft and tractor (8) and aircraft, then mounting spring back seat (18), spring back seat (18) and oil cabinet shell (21) are reinforced, filler port (20) is established in oil cabinet shell (21) upper end, in oil cabinet shell (21), fixing multiple sliding wheel (19) is installed, gear gim peg (29) is placed in gear hold down groove (30), gear permanent seat (31) and oil cabinet shell (21) are reinforced, fuel transfer pump (11) is established in front end transport pipe (24) and rear end transport pipe (27), two ends are respectively connected with ejector shell (9) and oil cabinet shell (21), when electrical motor rotates forward, multistage spring assembly compression, piston is under the effect of ejector sleeve skewed slot, form positive round state gradually, at this moment machine oil enters engine oil compression room immediately, during electrical motor reversion, spring slow expansion, force push rod and ejector sleeve reach, ejector sleeve skewed slot is under the effect of push rod driven wheel, start to drive ejector sleeve and piston rotation, piston is made to form breach also overlapping gradually, at this moment the machine oil of engine oil compression room is altered immediately afterwards, the anterior pressure of piston gradually reduces, spring assembly is expanded gradually, the rotating speed of electrical motor is progressively accelerated, aircraft safety is taken off, piston oil stop device effect under stop moving ahead.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210587367.9A CN103192995B (en) | 2012-12-30 | 2012-12-30 | Rotary-piston type spring catapult |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210587367.9A CN103192995B (en) | 2012-12-30 | 2012-12-30 | Rotary-piston type spring catapult |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103192995A CN103192995A (en) | 2013-07-10 |
| CN103192995B true CN103192995B (en) | 2015-08-26 |
Family
ID=48715852
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210587367.9A Expired - Fee Related CN103192995B (en) | 2012-12-30 | 2012-12-30 | Rotary-piston type spring catapult |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103192995B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105730708A (en) * | 2016-02-20 | 2016-07-06 | 银世德 | Rotary cylinder type fuel gas ejector |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3968947A (en) * | 1975-01-14 | 1976-07-13 | All American Industries, Inc. | Launching apparatus for flying device |
| GB2173745A (en) * | 1985-04-18 | 1986-10-22 | Secr Defence | Launcher for unmanned aircraft |
| US5961069A (en) * | 1995-10-18 | 1999-10-05 | Dassault Aviation | Catapult exit shock absorber |
| CN102267571A (en) * | 2011-06-03 | 2011-12-07 | 清华大学 | Spring-pulley combined unmanned aerial vehicle ejector |
| CN202320800U (en) * | 2011-11-29 | 2012-07-11 | 北京思凯飞翔科技有限公司 | Ejection device for unmanned aircraft |
| CN102700721A (en) * | 2012-05-04 | 2012-10-03 | 银世德 | Combined catapult for aircraft carrier |
-
2012
- 2012-12-30 CN CN201210587367.9A patent/CN103192995B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3968947A (en) * | 1975-01-14 | 1976-07-13 | All American Industries, Inc. | Launching apparatus for flying device |
| GB2173745A (en) * | 1985-04-18 | 1986-10-22 | Secr Defence | Launcher for unmanned aircraft |
| US5961069A (en) * | 1995-10-18 | 1999-10-05 | Dassault Aviation | Catapult exit shock absorber |
| CN102267571A (en) * | 2011-06-03 | 2011-12-07 | 清华大学 | Spring-pulley combined unmanned aerial vehicle ejector |
| CN202320800U (en) * | 2011-11-29 | 2012-07-11 | 北京思凯飞翔科技有限公司 | Ejection device for unmanned aircraft |
| CN102700721A (en) * | 2012-05-04 | 2012-10-03 | 银世德 | Combined catapult for aircraft carrier |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103192995A (en) | 2013-07-10 |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150826 Termination date: 20151230 |
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| EXPY | Termination of patent right or utility model |