CN101804866A - Flywheel energy storage accelerating carrier-based aircraft ejector and ejection method - Google Patents
Flywheel energy storage accelerating carrier-based aircraft ejector and ejection method Download PDFInfo
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- CN101804866A CN101804866A CN 201010110019 CN201010110019A CN101804866A CN 101804866 A CN101804866 A CN 101804866A CN 201010110019 CN201010110019 CN 201010110019 CN 201010110019 A CN201010110019 A CN 201010110019A CN 101804866 A CN101804866 A CN 101804866A
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Abstract
The invention provides a flywheel energy storage accelerating carrier-based aircraft ejector and an ejection method. The structure of the ejector is composed of a power machine, a clutch, a flywheel, a transmission shaft, a traction winch and a reel-off winch, wherein the traction winch and the flywheel are arranged on the transmission shaft, and the flywheel and the transmission shaft are fixed together; the traction winch is connected with the transmission shaft through a bearing; a flywheel clutch is arranged between the flywheel and the traction winch; the transmission shaft is fixed by a bearing bracket; and the end part of the transmission shaft is connected with the power machine through a motor clutch. Compared with the prior art, the flywheel energy storage accelerating carrier-based aircraft ejector has reasonable design, simple structure, safety, reliability, small volume, high automaticity, convenient use, easy maintenance and the like, and has favorable popularization and use value.
Description
Technical field
The present invention relates to a kind of ejector, a kind of specifically flywheel energy storage accelerating carrier-based aircraft ejector and catapult technique.
Background technology
At present, the carrier-borne aircraft mode of taking off on the aircraft carrier mainly contains two kinds, and a kind of is the steam-type ejector that uses on the state army aircraft carriers such as American and Britain, method, and this ejector uses steam to be used as power and quickens to take off by steam cylinder piston drive hauling hook pulling aircraft.Second kind is cunning on the Russian aircraft carrier formula that jumps, be that aircraft leans on and self quickens above deck to realize launching from warship flying by the runway that is upturned, the maximum deficiency that two kinds of ejection modes exist in actual application is, the steam catapult equipment volume is huge, occupy than large space, and steam boiler must be arranged, consumed energy is big, the operating cost height, the maintenance cost height, it is big to consume the fresh water amount in addition, straight news reporting is arranged, the airplane catapult system of eaglet number or Mi Nizi whenever launches an airplane and consumes nearly 1 ton of fresh water, and huge fresh water consumption is a problem of can not ignore; The deficiency that the sliding formula ejection mode that jumps exists is to build the sliding formula launching platform that jumps on the deck, must use the bi-motor aircraft of big thrust loading, so general middle-size and small-size aircraft carrier and single engine opportunity of combat can't be used.Owing to aspect the carrier-borne aircraft catapult technique China is carried out strict blockade on new techniques with western countries headed by the U.S., Muscovite carrier-borne aircraft with double engines prohibits selling to China, destroys the aircraft carrier of 10 serial single-shot opportunities of combat so Chinese can the taking off of a kind of realization of carrier-based aircraft ejector preferably is badly in need of in China.
Summary of the invention
Technical assignment of the present invention is to overcome above-mentioned shortcoming, and a kind of simple in structure, reasonable in design, flywheel energy storage accelerating carrier-based aircraft ejector that volume is little, easy to use, safe is provided.
Technical scheme of the present invention realizes in the following manner: its structure by engine, power-transfer clutch, flywheel, transmission shaft, traction winch and put the rope winch form, wherein traction winch and flywheel are arranged on the transmission shaft, flywheel and transmission shaft are fixed together, traction winch is connected with transmission shaft by bearing, between flywheel and the traction winch power-transfer clutch is set, transmission shaft is fixed by bearing frame, and the end of transmission shaft is connected with engine by power-transfer clutch.
Flywheel is provided with in the traction winch bilateral symmetry.
Engine is symmetrical arranged at the transmission shaft two ends.
The steel rope of putting the rope winch is connected with hauling hook, and hauling hook is connected with traction winch.
Hauling hook is provided with pulley, and two carrier-based aircraft ejector traction winches use a hauling rope, and the pulley on the middle hauling hook of hauling rope connects.
Engine is meant electrical motor, diesel engine, spark ignition engine, steam turbine, turbo-machine and HM Hydraulic Motor.
Adopt the beneficial effect in technology of the present invention garage to be, design science, simple in structure, volume is little, can use multiple propulsion source, flexible operation, accelerating ability are good, it is big to quicken horsepower, over-the-road expense is low, save characteristics such as the energy, long service life.
Description of drawings
Accompanying drawing 1 is the structural representation of flywheel energy storage accelerating carrier-based aircraft ejector main frame;
Accompanying drawing 2 is scheme drawings of flywheel energy storage accelerating carrier-based aircraft ejector complete machine;
Description of reference numerals: engine 1, electric motor clutch 2, bearing seat 3, flywheel 4, flywheel clutch 5, hauling rope 6, traction winch 7, transmission shaft 8, put rope winch 9, put rope winch clutch 10, put rope winch motor 11, hauling hook 12.
The specific embodiment:
Technical scheme of the present invention realizes in the following manner: as depicted in figs. 1 and 2, its structure by engine 1, power-transfer clutch, flywheel 4, transmission shaft 8, traction winch 7 and put the rope winch 9 form, wherein traction winch 7 and flywheel 4 are arranged on the transmission shaft 8, flywheel 4 is fixed together with transmission shaft 8, traction winch 7 is connected with transmission shaft 8 by bearing, between flywheel 4 and the traction winch 7 flywheel clutch 5 is set, transmission shaft is by bearing seat 3 support fixation, and the end of transmission shaft 8 is connected with engine 1 by electric motor clutch 2.
Flywheel 4 is in traction winch 7 bilateral symmetry settings.Engine 1 is symmetrical arranged at transmission shaft 8 two ends.
Put the rope winch 9 steel rope be connected with hauling hook 10, hauling hook 12 be connected with traction winch by steel rope.
Hauling hook 12 is provided with pulley, and two carrier-based aircraft ejector traction winches 7 use a hauling rope 6, and the centre of hauling rope 6 is connected with pulley on the hauling hook 12.
Put rope winch 9 by putting rope winch clutch 10 and putting the winch motor 11 of restricting and be connected.
The type selecting of engine is to decide according to the tonnage of aircraft carrier or classification, if nuclear aircraft carrier owing to carry steam boiler, can use steam engine or steam turbine that power is provided.If aircraft carrier powered by conventional energy can use electrical motor, turbo-machine, HM Hydraulic Motor or diesel engine to do power.Shown in accompanying drawing, the power take-off shaft of engine is connected the work of getting final product with the engine power-transfer clutch.
Ejector of the present invention can have multiple combination, can use an engine to drive such as traction winch, also can use two engine symmetries to connect drives, can also use in parallel use of traction winch of the double dynamical machine of two covers that large traction is provided, be used to launch early warning plane or other heavy bombers.Constructional drawing as shown in Figure 2.
Embodiment
Principle of work of the present invention is as follows: be equipped with flywheel energy storage with engine as propulsion source, by the flywheel amount of holding, under the cooperation of power-transfer clutch, the energy of flywheel and the energy of engine are gathered the tractive force that maximum is provided for opportunity of combat at short notice, opportunity of combat slides in the 5-10 rice, the whole adhesives of power-transfer clutch, engine is with regard to full load carrying out the full speed traction to opportunity of combat, in addition under the reducing effect of traction winch, for opportunity of combat provides extra acceleration, realize the short range catapult-assisted take-off of opportunity of combat; It is as follows specifically to launch step:
Engine provides turning effort, drives flywheel by electric motor clutch and transmission shaft and rotates, and is after the flywheel rotation reaches certain rotating speed, stand-by;
The hauling rope end of traction winch connects hauling hook, and hauling hook is connected with the carrier-borne aircraft front-wheel to the carrier-borne aircraft takeoff point by the rope traction of putting the rope winch awaits orders;
After the dispatcher assigns takeoff order, flywheel clutch adhesive between flywheel and the traction winch, engine continues full-load operation, traction winch is connected rapidly by flywheel clutch, and the driving traction winch rotates with flywheel, the hauling hook pulling opportunity of combat of traction end is quickened to move ahead, because traction winch is at the rotation initial stage, hauling rope is that minor diameter twines in the winding of traction winch axial region, and haulage speed is slow, but tractive force is big, along with the increase of twining the number of turns, cooling diameter is increasing, thereby haulage speed is more and more faster, before arriving ship side, opportunity of combat has reached takeoff speed, and at this moment hauling hook separates, the opportunity of combat lift-off;
Put the rope winch and be by putting rope clutch and putting the motor of restricting and be connected, when traction winch traction opportunity of combat begins to slide, putting the rope winch clutch discharges, the steel rope of putting the rope winch is pulled always and is pulled to the runway terminal point, after opportunity of combat flies away from the deck, put the power-transfer clutch adhesive of rope winch, flywheel clutch discharges, traction winch is no longer stressed, put the rope winch rotator inertia of traction winch is carried out damping, the traction winch stall, hauling hook is put the rope winch and is retracted the runway starting point then, put the rope winch clutch and discharge standby, second opportunity of combat enters takeoff point and is connected the next takeoff order of wait with hauling hook.
Adopt electrical motor that power is provided, the work of each power-transfer clutch all is relay or computer program automatic guidance, controls very simple and reliable.Such as, in starting point of launching runway and terminal point spacing relay is set respectively, program start when opportunity of combat is taken off is put the rope winch clutch and is discharged the flywheel clutch adhesive, when hauling hook traction opportunity of combat slides into the runway end on runway, the spacing relay of runway terminal point starts, and flywheel clutch discharges, and puts the adhesive of rope winch clutch, the inertia that stops traction winch to produce, it is standby that the traction hauling hook is got back to the runway starting point simultaneously.Adopting the advantage of electrical motor is the degree of automation height, and volume is little, safety good, and electric energy provides by the electric power system of naval vessels.
If adopting diesel engine, automotive gas turbine is example, when opportunity of combat is taken off, the program start throttle strengthens automatically, puts the rope winch clutch and discharges the flywheel clutch adhesive, hauling hook traction opportunity of combat slides into the runway terminal point, spacing relay starts, and flywheel clutch discharges, and puts the adhesive of rope winch clutch, the inertia that stops traction winch to produce, it is standby that the traction hauling hook is got back to the runway starting point simultaneously.Hauling hook is capable when the terminal point, and flywheel is accelerated to maximum speed simultaneously, and throttle automatic release, diesel engine are treated speed work, and flywheel is rotated further.The intermittent use of diesel oil can reduce consumption of fuel, prolongs the service life of equipment.
The designing requirement of the power of engine, single engine should can accelerate to takeoff speed with opportunity of combat in second at 5-15, the accumulation of energy of a flywheel should equal the energy output of an engine in unit time at least, adopt double dynamical machine and round trip flight wheel to be provided with like this, the amount of redundancy that three engines are just arranged can guarantee that fully the full speed safety of opportunity of combat is launched.If to launching of early warning plane or bomber, except selecting supporting engine and flywheel for use, can also the above device parallel connection of two covers use, as shown in Figure 2.Can also on power-transfer clutch, dispose toric transmission if necessary to adapt to the catapult-assisted take-off of different aircrafts.
If device of the present invention is designed to miniaturization, can also be used for launching of unmanned plane.
Claims (8)
1. flywheel energy storage accelerating carrier-based aircraft ejector, it is characterized in that comprising engine, power-transfer clutch, flywheel, transmission shaft, traction winch and put the rope winch, wherein traction winch and flywheel are arranged on the transmission shaft, flywheel and transmission shaft are fixed together, traction winch is connected with transmission shaft by bearing, between flywheel and the traction winch power-transfer clutch is set, transmission shaft is fixed by bearing frame, and the end of transmission shaft is connected with engine by power-transfer clutch.
2. centrifugal energy storage accelerating carrier-based aircraft ejector according to claim 1 is characterized in that flywheel is in the setting of traction winch bilateral symmetry.
3. according to the described centrifugal energy storage accelerating carrier-based aircraft ejector of claim 1, it is characterized in that engine is symmetrical arranged at the transmission shaft two ends.
4. according to the described centrifugal energy storage accelerating carrier-based aircraft ejector of claim 1, it is characterized in that the steel rope of putting the rope winch is connected with hauling hook, hauling hook is connected with traction winch.
5. according to the described centrifugal energy storage accelerating carrier-based aircraft ejector of claim 4, it is characterized in that hauling hook is provided with pulley, two carrier-based aircraft ejector traction winches use a hauling rope, and the pulley on the middle hauling hook of hauling rope connects.
6. according to the described centrifugal energy storage accelerating carrier-based aircraft ejector of claim 1, it is characterized in that engine is meant electrical motor, diesel engine, spark ignition engine, steam turbine, turbo-machine and HM Hydraulic Motor.
7. according to the described centrifugal energy storage accelerating carrier-based aircraft ejector of claim 1, it is characterized in that putting the rope winch by putting the rope winch clutch and putting the winch motor of restricting and be connected.
8. the catapult technique of a flywheel energy storage accelerating carrier-based aircraft ejector, it is characterized in that, be equipped with flywheel energy storage with engine as propulsion source, by the flywheel amount of holding, under the cooperation of power-transfer clutch, the energy of flywheel and the energy of engine are gathered the tractive force that maximum is provided for opportunity of combat at short notice, opportunity of combat slides in the 5-10 rice, the whole adhesives of power-transfer clutch, engine just can full load carry out the full speed traction to opportunity of combat, in addition under the reducing effect of traction winch, for opportunity of combat provides extra acceleration, realize the short range catapult-assisted take-off of opportunity of combat; It is as follows specifically to launch step:
Engine provides turning effort, drives flywheel by electric motor clutch and transmission shaft and rotates, and is after the flywheel rotation reaches certain rotating speed, stand-by;
The hauling rope end of traction winch connects hauling hook, and hauling hook is connected with the carrier-borne aircraft front-wheel to the carrier-borne aircraft takeoff point by the rope traction of putting the rope winch awaits orders;
After the dispatcher assigns takeoff order, flywheel clutch adhesive between flywheel and the traction winch, engine continues full-load operation, traction winch is connected rapidly by flywheel clutch, and the driving traction winch rotates with flywheel, the hauling hook pulling opportunity of combat of traction end is quickened to move ahead, because traction winch is at the rotation initial stage, hauling rope is that minor diameter twines in the winding of traction winch axial region, and haulage speed is slow, but tractive force is big, along with the increase of twining the number of turns, cooling diameter is increasing, thereby haulage speed is more and more faster, before arriving ship side, opportunity of combat has reached takeoff speed, and at this moment hauling hook separates, the opportunity of combat lift-off;
Put the rope winch and be by putting rope clutch and putting the motor of restricting and be connected, when traction winch traction opportunity of combat begins to slide, putting the rope winch clutch discharges, the steel rope of putting the rope winch is pulled always and is pulled to the runway terminal point, after opportunity of combat flies away from the deck, put the power-transfer clutch adhesive of rope winch, flywheel clutch discharges, traction winch is no longer stressed, put the rope winch rotator inertia of traction winch is carried out damping, the traction winch stall, hauling hook is put the rope winch and is retracted the runway starting point then, put the rope winch clutch and discharge standby, second opportunity of combat enters takeoff point and is connected the next takeoff order of wait with hauling hook.
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| CN201010110019.3A CN101804866B (en) | 2010-02-20 | 2010-02-20 | Flywheel energy storage accelerating carrier-based aircraft ejector |
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| CN201010110019.3A CN101804866B (en) | 2010-02-20 | 2010-02-20 | Flywheel energy storage accelerating carrier-based aircraft ejector |
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| CN101804866A true CN101804866A (en) | 2010-08-18 |
| CN101804866B CN101804866B (en) | 2014-01-29 |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102107737A (en) * | 2010-09-19 | 2011-06-29 | 朱惠芬 | Front-pull rear-push aircraft carrier ejector and ejection method |
| CN102555774A (en) * | 2010-12-28 | 2012-07-11 | 黄德固 | Inertial power engine with motor structure |
| CN102717895A (en) * | 2012-07-10 | 2012-10-10 | 马敏 | Continuous ejection ejector |
| CN102910294A (en) * | 2012-07-17 | 2013-02-06 | 朱惠芬 | Coaxial bidirectional winding accelerated shipboard aircraft catapult |
| CN102910295A (en) * | 2012-07-17 | 2013-02-06 | 朱惠芬 | Two-way driving winding speedup type ship-borne aircraft catapult |
| CN103121509A (en) * | 2012-12-23 | 2013-05-29 | 黄上立 | Spiral flywheel catapult and application thereof |
| CN103332297A (en) * | 2013-07-02 | 2013-10-02 | 济南环太机电技术有限公司 | Belt type carrier-based aircraft booster system and decentralized energy storage and concentrated random boosting working method |
| CN103482077A (en) * | 2012-06-12 | 2014-01-01 | 济南高达信息技术有限公司 | Variable-torque electromagnetic damping type carrier-based aircraft landing arrester |
| CN103507964A (en) * | 2012-06-16 | 2014-01-15 | 姜汝诚 | Aircraft catapult-assisted take-off device and aircraft landing stopping device |
| CN104097786A (en) * | 2014-07-09 | 2014-10-15 | 吴炳选 | Mechanical catapult for carrier-based aircraft |
| CN104760706A (en) * | 2014-05-12 | 2015-07-08 | 葛愉成 | Flywheel energy storage propelling device |
| CN106853872A (en) * | 2015-12-08 | 2017-06-16 | 熵零股份有限公司 | A kind of aircraft catapult method and its system |
| CN107128505A (en) * | 2016-02-26 | 2017-09-05 | 熵零技术逻辑工程院集团股份有限公司 | A kind of Electromagnetical ejector |
| CN108357691A (en) * | 2018-02-11 | 2018-08-03 | 济南环太机电技术有限公司 | A kind of energy gathering type carrier-based aircraft ejector system with generating function |
| CN110510140A (en) * | 2019-09-25 | 2019-11-29 | 孙茂林 | Aircraft is in airport security landing concept after undercarriage failure |
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| US2514406A (en) * | 1939-12-15 | 1950-07-11 | Lisle J Maxson | Snubbing means for catapult carriages |
| US2672306A (en) * | 1951-01-05 | 1954-03-16 | All American Eng Co | Flywheel type catapult launching means |
| US4094143A (en) * | 1976-12-13 | 1978-06-13 | All American Industries, Inc. | Variable torque hydraulic clutch |
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Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102107737B (en) * | 2010-09-19 | 2013-03-27 | 济南环太机电技术有限公司 | Front-pull rear-push aircraft carrier ejector and ejection method |
| CN102107737A (en) * | 2010-09-19 | 2011-06-29 | 朱惠芬 | Front-pull rear-push aircraft carrier ejector and ejection method |
| CN102555774A (en) * | 2010-12-28 | 2012-07-11 | 黄德固 | Inertial power engine with motor structure |
| CN103482077B (en) * | 2012-06-12 | 2016-01-06 | 济南高达信息技术有限公司 | Bending moment electromagnetic damping formula aircraft carrier warship stopping device |
| CN103482077A (en) * | 2012-06-12 | 2014-01-01 | 济南高达信息技术有限公司 | Variable-torque electromagnetic damping type carrier-based aircraft landing arrester |
| CN103507964B (en) * | 2012-06-16 | 2016-09-07 | 姜汝诚 | Airplane catapult launching apparatus and aircraft landing arrester |
| CN103507964A (en) * | 2012-06-16 | 2014-01-15 | 姜汝诚 | Aircraft catapult-assisted take-off device and aircraft landing stopping device |
| CN102717895A (en) * | 2012-07-10 | 2012-10-10 | 马敏 | Continuous ejection ejector |
| CN102717895B (en) * | 2012-07-10 | 2015-10-14 | 济南弘毅格致科贸有限公司 | A kind of ejection ejector continuously |
| CN102910295A (en) * | 2012-07-17 | 2013-02-06 | 朱惠芬 | Two-way driving winding speedup type ship-borne aircraft catapult |
| CN102910294A (en) * | 2012-07-17 | 2013-02-06 | 朱惠芬 | Coaxial bidirectional winding accelerated shipboard aircraft catapult |
| CN103121509B (en) * | 2012-12-23 | 2015-07-29 | 黄上立 | Spiral flywheel catapult and application thereof |
| CN103121509A (en) * | 2012-12-23 | 2013-05-29 | 黄上立 | Spiral flywheel catapult and application thereof |
| CN103332297A (en) * | 2013-07-02 | 2013-10-02 | 济南环太机电技术有限公司 | Belt type carrier-based aircraft booster system and decentralized energy storage and concentrated random boosting working method |
| CN104760706A (en) * | 2014-05-12 | 2015-07-08 | 葛愉成 | Flywheel energy storage propelling device |
| CN104097786A (en) * | 2014-07-09 | 2014-10-15 | 吴炳选 | Mechanical catapult for carrier-based aircraft |
| CN106853872A (en) * | 2015-12-08 | 2017-06-16 | 熵零股份有限公司 | A kind of aircraft catapult method and its system |
| CN107128505A (en) * | 2016-02-26 | 2017-09-05 | 熵零技术逻辑工程院集团股份有限公司 | A kind of Electromagnetical ejector |
| CN108357691A (en) * | 2018-02-11 | 2018-08-03 | 济南环太机电技术有限公司 | A kind of energy gathering type carrier-based aircraft ejector system with generating function |
| CN110510140A (en) * | 2019-09-25 | 2019-11-29 | 孙茂林 | Aircraft is in airport security landing concept after undercarriage failure |
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