CN203143012U - Full-automatic intelligent aircraft carrier catapult - Google Patents
Full-automatic intelligent aircraft carrier catapult Download PDFInfo
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- CN203143012U CN203143012U CN 201320011180 CN201320011180U CN203143012U CN 203143012 U CN203143012 U CN 203143012U CN 201320011180 CN201320011180 CN 201320011180 CN 201320011180 U CN201320011180 U CN 201320011180U CN 203143012 U CN203143012 U CN 203143012U
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- aircraft carrier
- coaster
- spring assembly
- aircraft
- deck
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Abstract
The utility model discloses a full-automatic intelligent aircraft carrier catapult comprising an aircraft deck. A spring set support is vertically mounted on the aircraft carrier deck, a plurality of parallel spring barrels are arranged in the spring set support, elongated grooves are reserved between adjacent spring barrels, spring sets connected end to end are arranged in the spring barrels, the lower ends of the spring sets are connected with slide plates capable of sliding vertically in the elongated grooves in the spring set support, and an airplane catapulting pedal and a catapulting hoist are mounted on the aircraft carrier deck. All-weather taking off and war power of the aircraft carrier can be guaranteed without limit by severe weather. A fixed wing airborne early warning aircraft can take off, flight distance is greatly reduced, when a carrier-based aircraft takes off, flying weight is not needed to reduce, and bomb load and fuel load are reduced, so that the carrier-based aircraft can develop normal war power, and taking-off fuel of the carrier-based aircraft is saved. The aircraft carrier catapult is adjustable in size and speed and buffer force, high in safety coefficient and automation degree.
Description
Technical field
The utility model belongs to a kind of aircraft carrier technical field, specifically is a kind of fully-automatic intelligent aircraft carrier ejector.
Background technology
Present international aircraft carrier ejector mainly is divided into following several: the multiple power ejector of spring, potential energy ejecting device, combustion gas ejector, steam catapult, electromagnetic launch device, rocket-assisted ejection device, oblique angle ejector etc.And these several ejectors all exist certain inevitable shortcoming.Such as: the defective of steam catapult: (1) maintenance cost is big, and U-shaped sealing band is changed frequent and very bothered, and material is required high; (2) use the steam catapult cost big, efficient is low, and auxiliary facility is many, and system is loaded down with trivial details, and each link requires high; (3) need to consume a large amount of fresh water, the U.S. once considered vapour-condensing equipment for recovering for this reason, eventually because of low cancellation of the big efficient of volume.And the magnet coil ejector is different with common large flat type linear electric motors, and it not only has complicated pressure cooling system, and all inequality in the function of each section, so the electromagnetic launch device now only is in development phase.The rocket-assisted ejection device can produce a large amount of pollutantss in boosting, and cost height, can allow the not strong country of economy fear and stepping back with disposable boosting ejector, what be repeatedly used must join quick salvaging ship, inspection equipment, itself also will have position fixing system etc., the most important thing is that its safety is under suspicion always.The combustion gas ejector is in fact also just discussed and was analyzed, and the record of large-scale practice is not arranged.Potential energy ejecting device shortcoming be need build one very big domatic, the aircraft carrier air draught increases during operation, stealthy effect is bad, the more important thing is that the frequency of taking off is low, influence the miscellaneous equipment use, also needs supporting high-performance elevator etc.The multiple power ejector of spring then is to utilize linear electric motors or stored energy mechanism that spring is stretched to the energy storage position at present, utilize stop mechanism to keep energy not discharge, then utilize control system to disconnect stop mechanism during work, spring moving aircraft of pulling under multiple power accelerates, aircraft self driving engine and ejector make a concerted effort accelerate down, the initialization stroke generally has only 60 meters.But regrettably this ejector can not directly take off airplane catapult, and aircraft must slide one section and just can take off under the thrust of driving engine.And this ejector is that spring is placed in the slideway of opening (internal orifice band lubricating oil) in practical study, purpose be do not allow ejector when work not to around exert an influence, and this large power spring is to the material requirements strictness, just imagine that so high-performance spring do not change during one's term of military service at aircraft carrier, to material require be how to carve severe, even slideway, its precision also requires very high.This ejector cataplane number of times is not high, because it finishes energy storage by stored energy mechanism.Pulling force was very big when this ejector was initial, and the phenomenon of fainting in short-term can take place the aviator.Mechanism's intensity to aircraft also requires quite high.And the working distal tip pulling force is very little, and crucial moment can not accelerated take-off.
The utility model content
The purpose of this utility model is that simple in structure, ejection force is big for country provides a kind of fully-automatic intelligent aircraft carrier ejector, and ejection speed is fast, can launch aircraft carrier and take off.
Technical solutions of the utility model are as follows:
The fully-automatic intelligent aircraft carrier ejector, include the aircraft carrier deck, described aircraft carrier vertically is equipped with the spring assembly support on the deck, be provided with a plurality of parallel spring tubes in the described spring assembly support, be provided with the bar shaped fluting between the adjacent springs tube, be provided with end to end spring assembly in the described spring strut, described spring assembly lower end is connected with slide plate, upper and lower slip in the bar shaped fluting that described slide plate can be in described spring assembly support; The napex of described spring assembly support is equipped with pulley, the described spring assembly support next door that is positioned at below, aircraft carrier deck is equipped with the spring winch, after the slide plate wirerope being arranged and described slide plate being connected, walk around spring assembly and prop up the pulley of top of the trellis, be wound on the described winch, described winch is connected with motor driver by power-transfer clutch; Described aircraft carrier deck below also is equipped with winch and launches the coaster reel with shaft drive, front end below, deck also is equipped with front wheel, launch and be wound with the end to end coaster wirerope that launches on the coaster reel, described launch to be fixedly connected with on the coaster wirerope launch coaster, the described coaster reference position of launching is placed in the chute that has the slope on the aircraft carrier deck, launch coaster wirerope front end on front wheel, launch coaster reel rotating band and move and penetrate coaster and move ahead on the aircraft carrier deck; Be rotatablely equipped with the airplane catapult pedal on the described aircraft carrier deck of launching the coaster anterior position, the airplane catapult pedal upwarps along launching the coaster line of travel, airplane catapult pedal middle part has ammunition feed and penetrates the groove that the coaster wirerope passes through, described airplane catapult pedal lower end has turns pull bar, and the below, deck in airplane floor sheet the place ahead is equipped with the switch deflection sheave; On the described spring assembly support outer wall ejection switch mechanism is installed, described ejection switch mechanism includes to be equipped with and has the fixture block fluting on the outer wall of spring assembly support stage casing, the described fixture block fluting outside is equipped with support, described support upper fixed has turret, be rotatablely equipped with two sliding bars on the described turret, be set with towing plate on the described sliding bar, described sliding bar front end is installed with end plate, be with the fixture block spring on the sliding bar between described end plate and the towing plate, described towing plate two ends are rotatably connected to the switch fixture block, and described switch fixture block extend in the described fixture block fluting under the fixture block action of the spring; After having steel rope to be connected with to walk around deflection sheave group and switch deflection sheave behind the towing plate, be connected on the following pull bar that turns of airplane catapult pedal below.
Described spring assembly support is two, and parallel symmetry vertically is installed on the aircraft carrier deck at interval, and part extend into below, aircraft carrier deck, and described ejection switch mechanism is installed on the outer wall of spring assembly support stage casing.
The described coaster front end that launches is equipped with elastic buffering mechanism, and described elastic buffering mechanism pushing tow is taken off.
On the described turret servomotor is installed, described servomotor is controlled by PLC, and pulling brake Bands control brake disc can be controlled ejector speed.
Described spring assembly is formed by connecting by jointing by a plurality of springs.
The utility model principle of work:
After by the motor-driven winch slide plate wirerope being reeled, drive slide plate and be up to the spring assembly mid-stent, the switch fixture block by ejection switch mechanism snaps in the fixture block fluting on the spring assembly mid-stent outer wall, keeps off spacing above slide plate.At this moment, after the steel rope process deflection sheave group that connects on the towing plate of ejection switch mechanism and behind the switch deflection sheave, be connected on the following pull bar that turns of airplane catapult pedal below, make the airplane catapult pedal upwarp, be in this moment takes off readiness.When aircraft carrier slides, because launching coaster is arranged in the chute that has the slope on the aircraft carrier deck, aircraft can pass and launch coaster, when aircraft nose wheel is set foot on when launching pedal, press down and launch the pedal rotation, the tensioning steel rope drives towing plate and moves outward like this, and then drive switch fixture block breaks away from the fixture block fluting, slide plate is under the immense pressure and the effect of spring self gravitation of spring assembly, and is descending fast, at this moment, pass through electrical equipment control, power-transfer clutch between winch and the drive motor disconnects, winch under the drive of slide plate wirerope, twirl, because reel is coaxial with winch, therefore, reel is twirl also, and then is wound on and launches also twirl of coaster wirerope on the reel, and drive to launch in the chute that has the slope of coaster from the aircraft carrier deck and go out and slide, the elastic buffering mechanism by front end promotes to take off.Then, roll the slide plate wirerope by the motor-driven winch, towing plate can be got back to the initial position of withstanding the slide plate below under the elastic force effect of spring, can be used for the catapult-assisted take-off of next aircraft.The elastic force of spring assembly and group number etc. can calculate according to the airplane catapult required strength of taking off.
Advantage of the present utility model:
The utility model has been overcome material again and has been hard to buy by the operation of PLC programmed touch screen, the cost height, and the difficult processing of accessory, original personnel selection is many, and complicated operation makes trouble, and the multiple power working distal tip pulling force of spring very submissile is penetrated shortcoming.
Can ensure aircraft carrier all-weather depature fight capability, not limited by inclement weather; The fixed-wing early warning plane that can take off significantly reduces take off distance; When carrier-borne aircraft takes off, needn't alleviate take-off weight, and reduce bullet-loading capacity, fuel load, make carrier-borne aircraft give play to normal operational performance; Save the carrier-borne aircraft fuel that takes off.Aircraft carrier ejector ejection force adjustable size. adjustable-speed, cushion effect is adjustable, the safety factor height, the degree of automation height,
Spring assembly support height overall can be designed to 44 meters, stands upright on the clamping plate, and following 16 meters of clamping plate can 28 meters more than the clamping plate, can adjust the installation site according to actual conditions.The intelligence aircraft carrier ejector be with spring assembly as ejection force, adopt the electric reducer structure, spring is compressed to certain position, can produce 56 tons elastic force.56 tons of elastic force that produce add 46 tons of the deadweights of upper spring and spring assembly Kickboard Scooter, can produce 102 tons of ejection forces.Subtracting power by pulley is 51 tons, and catapulting distance is 45 meters.Launch no force phenomenon when launching extreme end before the intelligence aircraft carrier ejector has been avoided, the intelligence aircraft carrier ejector is from top to bottom to terminal, the strength of launching of starting point is 28 tons and launches strength and also can reach 16 tons to taking off back extreme end minimum, so also can guarantee enough ejection forces to terminal, also can be controlled to be constant speed by PLC.The most important is, aircraft carrier can run at full speed from the distance away from 10 meters of the ejectors and come, aircraft is in 10 meters distances far away 60-80 kilometer speed per hour that can raise speed, there has been such speed can reduce the sense of fainting to the bump sense of aircraft and aviator, front-wheel is pressed onto the airplane catapult pedal on the clamping plate, launch coaster and slide fast at deck level, elastic buffering mechanism tangles the aircraft nose wheel spindle carrier makes aircraft accelerate 80-100 meters of speed-controllable per seconds processed.Elastic buffering mechanism can allow aircraft not clash into sense, thereby has avoided the aviator that the phenomenon of fainting in short-term takes place, and aircraft takes off very easily like this, and the aviator can not faint yet.
Description of drawings
Fig. 1 is that the utility model is at aircraft carrier deck arrangement structure scheme drawing.
Fig. 2 is the utility model structural representation.
Fig. 3 is the utility model ejection switch structural scheme of mechanism.
Fig. 4 is the utility model winch mounting structure scheme drawing.
Fig. 5 is the utility model structural representation.
Fig. 6 the utility model skateboard scheme drawing.
Fig. 7 is the utility model spring assembly support top structure scheme drawing.
The specific embodiment
The fully-automatic intelligent aircraft carrier ejector, include aircraft carrier deck 1, the parallel interval symmetry vertically is equipped with two spring assembly supports 2 on the described aircraft carrier deck 1, be provided with a plurality of parallel spring tubes 3 in the described spring assembly support 2, be provided with bar shaped fluting 4 between the adjacent springs tube 3, be provided with end to end spring assembly 5 in the described spring strut 3, described spring assembly 5 lower ends are connected with slide plate 6, and described slide plate 6 can upper and lower slip in the bar shaped of described spring assembly support 2 fluting 4; The napex of described spring assembly support 2 is equipped with pulley 7, described spring assembly support 2 next doors that are positioned at 1 below, aircraft carrier deck are equipped with winch 8, after slide plate wirerope 9 being arranged and described slide plate 6 being connected, walk around the pulley 7 at spring assembly support 2 tops, be wound on the described winch 8, described winch 8 is connected with motor driver 11 by power-transfer clutch; 1 below, described aircraft carrier deck also is equipped with winch 8 and launches coaster reel 12 with shaft drive, 1 front end below, deck also is equipped with front wheel 13, launch and be wound with the end to end coaster wirerope 15 that launches on the coaster reel 12, described launch to be fixedly connected with on the coaster wirerope 15 launch coaster 14, described coaster 14 reference positions of launching are placed in the chute that has the slope on the aircraft carrier deck 1, launch on the coaster wirerope 15 front ends locks front wheel 13, launch coaster reel 12 rotating bands and move and penetrate coaster 14 and move ahead on aircraft carrier deck 1; Be rotatablely equipped with airplane catapult pedal 16 on the described aircraft carrier deck 1 of launching coaster 13 anterior position, airplane catapult pedal 16 upwarps along launching the coaster line of travel, airplane catapult pedal 16 middle parts have ammunition feed and penetrate the groove that coaster wirerope 15 passes through, described airplane catapult pedal 16 lower ends have turns pull bar 17, and 1 below, deck in airplane catapult pedal 16 the place aheads is equipped with switch deflection sheave 18; On described spring assembly support 2 outer walls ejection switch mechanism 19 is installed, described ejection switch mechanism 19 includes to be equipped with to have on the spring assembly support 2 stage casing outer walls among the fixture block fluting 20(figure and fails to show), described fixture block 20 outsides of slotting are equipped with support 21, described support 21 upper fixed have turret 22, be rotatablely equipped with two sliding bars 23 on the described turret 22, be set with towing plate 24 on the described sliding bar 23, described sliding bar 23 front ends are installed with end plate 25, be with fixture block spring 26 on the sliding bar 23 between described end plate 25 and the towing plate 24, described towing plate 24 two ends are rotatably connected to switch fixture block 27, and described switch fixture block 27 extend in the described fixture block fluting 20 under 26 effects of fixture block spring; After having steel rope 28 to be connected with to walk around deflection sheave group 10 and switch deflection sheave 18 behind the towing plate 24, be connected on the following pull bar that turns 17 of airplane catapult pedal below.
On the described turret 22 servomotor is installed, described servomotor turning cylinder is connected with towing plate 24 bolts, promotes towing plate 24 and slides up and down along sliding bar.Standby when being used for the inefficacy of airplane catapult pedal, can not establish.
Spring assembly is formed by connecting by jointing by a plurality of springs.The jointing two ends extend into respectively in the spring that two need connect and connect.
Claims (5)
1. fully-automatic intelligent aircraft carrier ejector, include the aircraft carrier deck, it is characterized in that, described aircraft carrier vertically is equipped with the spring assembly support on the deck, be provided with a plurality of parallel spring tubes in the described spring assembly support, be provided with the bar shaped fluting between the adjacent springs tube, be provided with end to end spring assembly in the described spring strut, described spring assembly lower end is connected with slide plate, upper and lower slip in the bar shaped fluting that described slide plate can be in described spring assembly support; The napex of described spring assembly support is equipped with pulley, the described spring assembly support next door that is positioned at below, aircraft carrier deck is equipped with the spring winch, after the slide plate wirerope being arranged and described slide plate being connected, walk around spring assembly and prop up the pulley of top of the trellis, be wound on the described winch, described winch is connected with motor driver by power-transfer clutch; Described aircraft carrier deck below also is equipped with winch and launches the coaster reel with shaft drive, front end below, deck also is equipped with front wheel, launch and be wound with the end to end coaster wirerope that launches on the coaster reel, described launch to be fixedly connected with on the coaster wirerope launch coaster, the described coaster reference position of launching is placed in the chute that has the slope on the aircraft carrier deck, launch coaster wirerope front end on front wheel, launch coaster reel rotating band and move and penetrate coaster and move ahead on the aircraft carrier deck; Be rotatablely equipped with the airplane catapult pedal on the described aircraft carrier deck of launching the coaster anterior position, the airplane catapult pedal upwarps along launching the coaster line of travel, airplane catapult pedal middle part has ammunition feed and penetrates the groove that the coaster wirerope passes through, described airplane catapult pedal lower end has turns pull bar, and the below, deck in airplane floor sheet the place ahead is equipped with the switch deflection sheave; On the described spring assembly support outer wall ejection switch mechanism is installed, described ejection switch mechanism includes to be equipped with and has the fixture block fluting on the outer wall of spring assembly support stage casing, the described fixture block fluting outside is equipped with support, described support upper fixed has turret, be rotatablely equipped with two sliding bars on the described turret, be set with towing plate on the described sliding bar, described sliding bar front end is installed with end plate, be with the fixture block spring on the sliding bar between described end plate and the towing plate, described towing plate two ends are rotatably connected to the switch fixture block, and described switch fixture block extend in the described fixture block fluting under the fixture block action of the spring; After having steel rope to be connected with to walk around deflection sheave group and switch deflection sheave behind the towing plate, be connected on the following pull bar that turns of airplane catapult pedal below.
2. fully-automatic intelligent aircraft carrier ejector according to claim 1, it is characterized in that described spring assembly support is two, parallel symmetry vertically is installed on the aircraft carrier deck at interval, and part extend into below, aircraft carrier deck, and described ejection switch mechanism is installed on the outer wall of spring assembly support stage casing.
3. fully-automatic intelligent aircraft carrier ejector according to claim 1 is characterized in that the described coaster front end that launches is equipped with elastic buffering mechanism, and described elastic buffering mechanism pushing tow is taken off.
4. fully-automatic intelligent aircraft carrier ejector according to claim 1 is characterized in that on the described turret servomotor being installed, and described servomotor is controlled by PLC, and pulling brake Bands control brake disc can be controlled ejector speed.
5. fully-automatic intelligent aircraft carrier ejector according to claim 1 is characterized in that described spring assembly is formed by connecting by jointing by a plurality of springs.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320011180 CN203143012U (en) | 2013-01-09 | 2013-01-09 | Full-automatic intelligent aircraft carrier catapult |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320011180 CN203143012U (en) | 2013-01-09 | 2013-01-09 | Full-automatic intelligent aircraft carrier catapult |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203143012U true CN203143012U (en) | 2013-08-21 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320011180 Expired - Lifetime CN203143012U (en) | 2013-01-09 | 2013-01-09 | Full-automatic intelligent aircraft carrier catapult |
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| CN (1) | CN203143012U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103043221A (en) * | 2013-01-09 | 2013-04-17 | 朱景超 | Full-automatic intelligent aircraft carrier catapult |
| CN110576946A (en) * | 2018-06-09 | 2019-12-17 | 天津大学（青岛）海洋工程研究院有限公司 | Water surface take-off and landing device of airplane |
-
2013
- 2013-01-09 CN CN 201320011180 patent/CN203143012U/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103043221A (en) * | 2013-01-09 | 2013-04-17 | 朱景超 | Full-automatic intelligent aircraft carrier catapult |
| CN103043221B (en) * | 2013-01-09 | 2015-04-15 | 朱景超 | Full-automatic intelligent aircraft carrier catapult |
| CN110576946A (en) * | 2018-06-09 | 2019-12-17 | 天津大学（青岛）海洋工程研究院有限公司 | Water surface take-off and landing device of airplane |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20130821 Effective date of abandoning: 20150415 |
|
| RGAV | Abandon patent right to avoid regrant |