CN101804866B - Flywheel energy storage accelerating carrier-based aircraft ejector - Google Patents
Flywheel energy storage accelerating carrier-based aircraft ejector Download PDFInfo
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- CN101804866B CN101804866B CN201010110019.3A CN201010110019A CN101804866B CN 101804866 B CN101804866 B CN 101804866B CN 201010110019 A CN201010110019 A CN 201010110019A CN 101804866 B CN101804866 B CN 101804866B
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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, specifically a kind of flywheel energy storage accelerating carrier-based aircraft ejector and catapult technique.
Background technology
At present, the carrier-borne aircraft mode of taking off on aircraft carrier mainly contains two kinds, and a kind of is the steam-type ejector using on American and Britain ,Fa Deng state army aircraft carrier, and this ejector use steam is used as power and drives hauling hook to pull aircraft to accelerate to take off by steam cylinder piston.The second is the formula that jumps of the cunning on Russian Aircraft Carrier, be that aircraft leans on and self accelerates above deck to realize launching from warship by the runway that is upturned to fly, the maximum deficiency that two kinds of ejection modes exist in actual application is, steam catapult equipment volume is huge, occupy larger space, and must there is steam boiler, consumed energy is large, operating cost is high, maintenance cost is high, consume in addition fresh water amount large, there is straight news reporting, the airplane catapult system of eaglet number or meter Ni Zi, often launch an airplane and consume nearly 1 ton of fresh water, huge fresh water consumption is a problem of can not ignore, the deficiency that the sliding formula ejection mode that jumps exists is on deck, to build the sliding formula launching platform that jumps, and 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 cannot be used.Owing to aspect carrier-borne aircraft catapult technique, China being carried out to strict blockade on new techniques with western countries headed by the U.S., Muscovite carrier-borne aircraft with double engines prohibits selling to China, so Chinese can the taking off of a kind of good carrier-based aircraft ejector realization is badly in need of in China, destroys the aircraft carrier of 10 serial single-shot opportunities of combat.
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 rope winch form, wherein traction winch and flywheel are arranged on transmission shaft, flywheel and transmission shaft are fixed together, traction winch is connected with transmission shaft by bearing, between flywheel and 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 arranges in traction winch bilateral symmetry.
Engine is symmetrical arranged at transmission shaft two ends.
The steel rope of putting rope winch is connected with hauling hook, and hauling hook is connected with traction winch.
On hauling hook, be 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.
Engine refers to 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, and flexible operation, accelerating ability are good, accelerates horsepower large, and over-the-road expense is low, save the features such as the energy, long service life.
Accompanying drawing explanation
Accompanying drawing 1 is the structural representation of flywheel energy storage accelerating carrier-based aircraft ejector main frame;
Accompanying drawing 2 is schematic diagrams 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 rope winch 9 form, wherein traction winch 7 and flywheel 4 are arranged on 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 traction winch 7, flywheel clutch 5 is set, transmission shaft supports fixing by bearing seat 3, 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 rope winch 9 steel rope be connected with hauling hook 10, hauling hook 12 with by steel rope, be connected with traction winch.
On hauling hook 12, be provided with pulley, two carrier-based aircraft ejector traction winches 7 use a hauling rope 6, and the centre of hauling rope 6 is connected with the pulley on 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 determine according to the tonnage of aircraft carrier or classification, if nuclear aircraft carrier, owing to carrying steam boiler, can be used 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 to the work of getting final product with engine power-transfer clutch.
Ejector of the present invention can have multiple combination, such as can using an engine, traction winch drives, also can use symmetrical connection of two engines to drive, can also use in parallel use of traction winch of the double dynamical machine of two covers that large traction is provided, for launching 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: the engine of usining is equipped with flywheel energy storage as propulsion source, by the flywheel amount of holding, under the cooperation of power-transfer clutch, the energy aggregation of the energy of flywheel and engine is got up at short notice for opportunity of combat provides maximum tractive force, opportunity of combat slides in 5-10 rice, the whole adhesives of power-transfer clutch, engine is with regard to full load carrying out 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; Specifically launch step as follows:
Engine provides turning effort, by electric motor clutch and transmission shaft, drives flywheel to rotate, and when flywheel rotates, reaches after certain rotating speed, stand-by;
The hauling rope end of traction winch connects hauling hook, and hauling hook is connected and awaits orders with carrier-borne aircraft front-wheel by putting rope traction to the carrier-borne aircraft takeoff point of rope winch;
When dispatcher assigns after takeoff order, flywheel clutch adhesive between flywheel and traction winch, engine continues full-load operation, traction winch is connected driving traction winch rapidly and rotates with flywheel by flywheel clutch, the hauling hook of traction end pulls opportunity of combat to accelerate to move ahead, because traction winch is at the rotation initial stage, hauling rope is that minor diameter is wound around in the winding of traction winch axial region, haulage speed is slow, but tractive force is large, along with being wound around the increase of 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, at this moment hauling hook is separated, opportunity of combat lift-off,
Put rope winch and be by putting rope clutch and putting the motor of restricting and be connected, when traction winch traction opportunity of combat starts to slide, putting rope winch clutch discharges, the steel rope of putting rope winch is pulled always and is pulled to runway terminal, when opportunity of combat flies away from behind deck, put the power-transfer clutch adhesive of rope winch, flywheel clutch discharges, traction winch is no longer stressed, put rope winch the rotator inertia of traction winch is carried out to damping, traction winch stall, then hauling hook is put rope winch and is retracted runway starting point, put 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 is all that relay or computer program are controlled automatically, controls very simple and reliable.Such as, at the starting point and the terminal that launch runway, limit relay is set respectively, when opportunity of combat is taken off, program starts, and puts rope winch clutch and discharges, flywheel clutch adhesive, when hauling hook traction opportunity of combat slides into the runway end on runway, the limit relay of runway terminal 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 traction hauling hook is got back to runway starting point simultaneously.Adopting the advantage of electrical motor is that degree of automation is high, 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, program starts throttle and automatically strengthens, and puts rope winch clutch and discharges, flywheel clutch adhesive, hauling hook traction opportunity of combat slides into runway terminal, limit 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 traction hauling hook is got back to runway starting point simultaneously.Hauling hook is capable when the terminal, and flywheel is accelerated to maximum speed simultaneously, and throttle discharges automatically, and diesel engine is treated speed work, and flywheel is rotated further.The intermittent use of diesel oil can reduce consumption of fuel, the service life of extension device.
The designing requirement of the power of engine, single-power machine should can accelerate to takeoff speed by opportunity of combat in second at 5-15, the accumulation of energy of a flywheel should at least equal the energy output of an engine within the unit time, adopt so double dynamical machine and free wheels setting, the amount of redundancy that just has three engines, can guarantee that the full speed of opportunity of combat is launched safely completely.If to launching of early warning plane or bomber, except selecting supporting engine and flywheel, can also the above device parallel connection of two covers use, as shown in Figure 2.Can also on power-transfer clutch, configure if necessary toric transmission to adapt to the catapult-assisted take-off of different aircrafts.
If device of the present invention is designed to miniaturization, can also launching for unmanned plane.
Claims (2)
1. a flywheel energy storage accelerating carrier-based aircraft ejector, it is characterized in that carrier-based aircraft ejector structure comprises: engine, power-transfer clutch, flywheel, transmission shaft, traction winch and put rope winch, wherein traction winch and flywheel are arranged on transmission shaft, flywheel and transmission shaft are fixed together, traction winch is connected with transmission shaft by bearing, between flywheel and traction winch, power-transfer clutch is set, and transmission shaft is fixed by bearing frame, the end of transmission shaft is connected with engine by power-transfer clutch, wherein:
Flywheel arranges in traction winch bilateral symmetry, engine is symmetrical arranged at transmission shaft two ends, the steel rope of putting rope winch is connected with hauling hook, hauling hook is connected with traction winch, on hauling hook, be 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; Put rope winch by putting rope winch clutch and putting the winch motor of restricting and be connected.
2. according to centrifugal energy storage accelerating carrier-based aircraft ejector claimed in claim 1, it is characterized in that engine refers to electrical motor, diesel engine, spark ignition engine, steam turbine, turbo-machine and HM Hydraulic Motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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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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| Application Number | Priority Date | Filing Date | Title |
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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 CN101804866A (en) | 2010-08-18 |
| CN101804866B true CN101804866B (en) | 2014-01-29 |
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Families Citing this family (16)
| 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 |
| 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 |
| CN103507964B (en) * | 2012-06-16 | 2016-09-07 | 姜汝诚 | Airplane catapult launching apparatus and aircraft landing arrester |
| 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 |
| 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 |
| CN103121509B (en) * | 2012-12-23 | 2015-07-29 | 黄上立 | Spiral flywheel catapult and application thereof |
| CN103332297B (en) * | 2013-07-02 | 2016-04-20 | 济南环太机电技术有限公司 | Random boosting work method is concentrated in a kind of belt carrier-borne aircraft booster system and dispersion accumulation of energy |
| CN104760706B (en) * | 2014-05-12 | 2017-03-15 | 葛愉成 | A kind of flywheel energy storage propulsion plant |
| 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 |
| CN114537693B (en) * | 2021-11-17 | 2024-09-24 | 王泽民 | Traction device for taking off carrier-based aircraft |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN1419508A (en) * | 2000-02-24 | 2003-05-21 | 弗雷德里克·让-皮埃尔·德莫勒 | An acceleration system |
-
2010
- 2010-02-20 CN CN201010110019.3A patent/CN101804866B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN1419508A (en) * | 2000-02-24 | 2003-05-21 | 弗雷德里克·让-皮埃尔·德莫勒 | An acceleration system |
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| CN101804866A (en) | 2010-08-18 |
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Effective date of registration: 20140714 Address after: 226236 Nanhai Road, Binhai Industrial Park, Nantong, Jiangsu, Qidong Patentee after: Qidong Sanjiang Construction Machinery Co., Ltd. Address before: 250014 Shandong Province, Lixia District of Ji'nan City Kiln Road No. 2-43 Patentee before: Jiang Ming |