CN103332297A - Belt type carrier-based aircraft booster system and decentralized energy storage and concentrated random boosting working method - Google Patents
Belt type carrier-based aircraft booster system and decentralized energy storage and concentrated random boosting working method Download PDFInfo
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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
- B64F1/08—Launching or towing gear using winches
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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 invention provides a belt type carrier-based aircraft booster system and a decentralized energy storage and concentrated random boosting working method. The system comprises a boosting module assembly, a return module assembly, a runway module, a slide shuttle module and a controller module, wherein the boosting module assembly consists of more than one boosting module which is arranged below the runway module; the boosting module comprises a T-shaped box body, motors, a transmission shaft, a clutch, a brake and a pedestal; the bottom of the T-shaped box body is fixed to the middle part of the pedestal; the motors are fixedly arranged on the pedestal and are positioned on the two sides of the T-shaped box body; the transmission shaft penetrates through the middle part of the T-shaped box body through a bearing pedestal; the two ends of the transmission shaft are provided with the clutch and the brake respectively; a driven part of the clutch and the brake are fixed to the transmission shaft; a driving part of the clutch is connected with the belt pulley; the belt pulley is connected with the transmission shaft through a bearing; the outer circle of the belt pulley is connected with the belt pulley at the motor shaft end through the belt; and the two ends of the folded transmission belt are fixed on the transmission shaft in the middle of the T-shaped box body through belt pressing plates. The system has the characteristics of simple structure, easiness in machining, transportation, mounting, debugging and maintenance, high modularization and the like, and is a piece of optimal equipment for an aircraft carrier.
Description
Technical field
The present invention relates to a kind of military equipment technical field, boosting work method is at random concentrated in a kind of belt carrier-borne aircraft booster system and dispersion accumulation of energy specifically.
Background technology
At present, the carrier-based aircraft ejector of the use on the aircraft carrier mainly contains two kinds, and a kind of is the steam catapult that uses with on U.S. army's aircraft carrier, and this booster uses steam to be used as power and accelerates to take off by piston drive hauling hook pulling aircraft in the open cylinder.The steam catapult equipment volume is huge, occupies than large space complex manufacturing technology, also will consume a large amount of fresh water, be the cylinder that cracks because the steam catapult of the U.S. adopts, thereby steam leakage is big, energy consumption is big, cylinder packing spare is short service life, and the maintenance cost height is in severe cold area or winter, the steam that leaks can freeze above deck, have a strong impact on taking off or landing of carrier-borne aircraft, this also be U.S.'s aircraft carrier in the winter time action radius reduce, or dare not arrive the basic reason of arctic scope activity at all.Because technology is externally maintained secrecy, so have only U.S. army to be equipped with steam catapult at 11 aircraft carriers at present.
The shortcoming that steam catapult exists is as follows:
1) weight is big, volume is big, and nearly 1000 tons of steam power booster total weight can be divided into by function: 1. take-off system 2. steam units 3. playback systems 4. hydraulic efficiency pressure systems, 5. pre-power system 6. lubricating systems, 7. control system.These systems can be decomposed into more mini system again; Roughly be 1.6 *, 1.8=2.88 sq ms for laying the groove sectional area that cylinder reserves on the flight deck, consider again booster nearly 100 meters length, then the volume of this part taps into 300 cubic meters.The volume of two jars also more than 200 cubic meters, is added the place that devices such as gas pipeline occupy, and cumulative volume has been arrived 600 cubic meters, the cumulative volume of 4 cover boosters is 2400 cubic meters, as for weight, a cover booster has 1000 tons at least, and 4 covers just have 4000 tons;
2) very high to material, technological requirement.Now except the U.S., comprise that the big national capitals of naval such as Great Britain and France can not make, buy to the U.S.;
3) efficient is low, and is wasteful.One time boosting will consume 800-1000 kilograms of fresh water.Producing these steam earlier will be with sea water desalination, and the water with desalination is heated into high temperature and high pressure steam in boiler again.And with these steam-reformings become boosting power have only 4 % to 6 %! If carry out boosting with the minimum interval, need to consume the steam of aircraft carrier boiler 20%;
4) system complex, operating personal is numerous, and a booster needs operating personal and about 120 people of reform personnel.The Operation and maintenance personnel that portion's booster needs reach more than 500, complete account for about 10% of warship establishment, maintenance capacity is big, and whenever launching 400 to 500 sorties just need be by the maintenance of carrying out 1-2 days with the warship personnel;
5) be that to launch power big, ejector to the requirement of launching carrier-borne aircraft be requirement in a short period of time, the power of consume significant launches takeoff speed to the heavy carrier-borne aircraft of 35-60 ton with what break out formula in the distance of 90-100 rice.The power of maximum steam catapult is ten thousand kilowatts of 4.75-6.3333 now! And working application time has only .2.6 second! The nuclear reactor gross horsepower of the atomic aircraft of U.S.'s maximum is 280,000 horsepowers, amounts to about 200,000 kilowatts! And the power of a steam catapult will how 60,000 4 thousand watt! If not the large-scale storage tank help accumulation of energy by 2 100 cubic meters, in any case this nuclear reactor of 200,000 kilowatts also can not supply the 4th booster;
6) cost height, production technology is highly confidential, and steam catapult of the U.S. of known active service is 8,000 ten thousand dollars of prices at least, have only the U.S. to grasp production technology at present, and selling range of use is the U.S. and ally thereof.
Second kind is the electromagnetic type ejector, in view of the many disadvantages that steam catapult exists, 28 years consuming time of United States Navy, expensive 3,200,000,000 dollars, succeeded in developing the electromagnetic type ejector, though in the land success of the test, because bulky, power consumption is huge, structure is too complicated, stability is very unreliable, and can't adapt to marine humidity and the harsh environment of salt fog, so yet be in conceptual phase till now, aircraft carrier also dare not formally be equipped so far by U.S. army.
In sum, do not have carrier-based aircraft ejector, no matter the aircraft carrier size all can not form fighting capacity, the principle of steam catapult is exactly a big and long steam engine! The characteristics of steam engine are long work, rather than break out the work of formula, so, the mode of operation of his inborn incompatibility booster.The principle of electromagnetic type ejector is exactly a linear motor.His work characteristics is the same with steam engine, only is adapted to long work, and can not break out the work of formula.No matter steam catapult still is the electromagnetic type ejector, the huge energy of abrupt release all is to realize by accumulation of energy, consumption of power all is 6.4 ten thousand kilowatts, and steam catapult is that the steam storage tank by 2 100 cubic meters comes accumulation of energy, converts high pressure steam to mechanical kinetic energy by open cylinder; And the electromagnetic type ejector is to realize by the mode of forcing storage station, the so-called storage station that forces, exactly the electric energy in traditional power station being driven 8 8000 kilowatts of dual-purpose motors respectively rotates and carries out accumulation of energy, when the electromagnetic type ejector needs big electric current to do work, 8 electrical motors convert 8 electrical generators immediately to, to rotate potential energy converting and energy and become electric energy, electric energy is concentrated in the linear electric motors of electromagnetic launch device and convert magnetic energy to, drive the mover high-speed mobile by magnetic energy and convert kinetic energy to, energy will consume 30-50% in the multiple conversions process, since steam catapult and electromagnetic type ejector be during by steam pressure can and magnetic field potential energy carry out moment and do work, need zero energy big, so energy dissipation is huge, according to pertinent data, be actually used in the energy shortage 10% on the carrier-borne aircraft, be least economical two kinds and launch pattern.As taking off shown in the curve of Fig. 6, carrier-borne aircraft is initially just accepted huge tractive force taking off, so speed is fast, and along with the consumption of energy, the reducing of potential energy, speed descends gradually, the shadow representation energy consumption of curve below;
As shown in Figure 7, the carrier-borne aircraft rate of onset is low, but along with the increase of the release force of inertia of energy, speed is just more and more faster, the gesture that rises to appears in curve, takeoff speed curve when this boosting curve and carrier-borne aircraft are unloaded matches, the energy consumption of comparison diagram 6 curves below, and the shade under Fig. 7 curve is significantly less than Fig. 6, this is the principle of boosting at random advance of the present invention just, energy consumption is more little, for carrier-based aircraft ejector, just means to have more good exploitativeness.
Summary of the invention
Technical assignment of the present invention is to overcome above-mentioned shortcoming, provide a kind of simple in structure, design is ingenious, scientific and reasonable, volume is little, easy to use, safe, long service life, the saving energy, energy utilization rate height, can adapt to various carrier-borne aircraft accelerated take-offs belt carrier-borne aircraft booster system and disperse accumulation of energy to concentrate boosting work method at random.
Technical scheme of the present invention realizes in the following manner: system comprises boosting module assembly, playback module assembly, runway module, shuttle module and controller module, wherein:
The boosting module assembly is listed in runway module below by an above boosting module row and forms, the boosting module comprises T shape casing, driving band, motor, transmission shaft, power-transfer clutch, drg and base, wherein T shape bottom half and base center fixed, motor is fixed on the both sides that are positioned at T shape casing on the base, transmission shaft is applied in centre at T shape casing by bearing seat, the two ends of transmission shaft are respectively arranged with power-transfer clutch and drg, the passive part of power-transfer clutch and drg and transmission shaft are fixed, the A end of power-transfer clutch is connected with belt pulley, belt pulley is connected with transmission shaft by bearing, the cylindrical of belt pulley is connected with the belt pulley of motor shaft end by belt, driving band two ends after the doubling are fixed on by the belt pressing plate and are positioned on the middle transmission shaft of T shape casing, driving band centre portion after the doubling is connected with the shuttle assembly, the top of T shape casing is provided with guiding roller, is connected with meter counter on the guiding roller
,Driving band passes in the middle of guiding roller and meter counter, and the two ends on T shape casing top are connected with the runway module, and the top of T shape casing is provided with the grooved track, and the grooved track is connected in series with the grooved track at runway module top;
The playback module assembly is listed in runway module below by playback module row more than and forms, the playback module comprises T shape casing driving band, motor, transmission shaft, power-transfer clutch, drg and base, wherein T shape bottom half and base center fixed, motor is fixed on the both sides that are positioned at T shape casing on the base, transmission shaft is applied in centre at T shape casing by bearing seat, the two ends of transmission shaft are respectively arranged with power-transfer clutch and drg, the passive part of power-transfer clutch and drg and transmission shaft are fixed, the A end of power-transfer clutch is connected with belt pulley, belt pulley is connected with transmission shaft by bearing, the cylindrical of belt pulley is connected with the belt pulley of motor shaft end by belt, driving band two ends after the doubling are fixed on by the belt pressing plate and are positioned on the middle transmission shaft of T shape casing, driving band centre portion after the doubling is connected with the shuttle assembly, the top of T shape casing is provided with guiding roller, is connected with meter counter on the guiding roller
,Driving band passes in the middle of guiding roller and meter counter, and the two ends on T shape casing top are connected with the runway module, and the top of T shape casing is provided with the grooved track, and the grooved track is connected in series with the grooved track at runway module top;
The runway module is made up of runway carriage, reverse rollers, middle carrying roller and grooved track, the runway carriage is connected between boosting module and the playback module and two ends, for the shuttle module is formed the linear slide track, the end that reverse rollers is arranged on the runway module provides the transmission guiding for driving band, and middle carrying roller is arranged on the centre of runway module and lifts holder for driving band provides guiding;
The shuttle module is arranged among the grooved track, its structure is by shuttle, shuttle vehicle frame, roller and be with roller and balance roller is formed, and the band roller is arranged on the outside at shuttle vehicle frame two ends, balance roller is arranged on and is with between the roller, and be with roller and balance roller to be formed by roll shaft and axle sleeve, it is protruding that two downward flange of shuttle vehicle frame are run through at the two ends of roll shaft, the two ends that roller is arranged on roll shaft are connected with the both sides groove rolling of grooved track, and axle sleeve is arranged on the centre of roll shaft between two downward flange of shuttle vehicle frame; Be connected the midway location of the doubling driving band on the boosting module transmission shaft, the middle carrying roller in the middle of the runway module, end reverse rollers and and pass on the axle sleeve that is socketed in balance roller with the top of roller; Be connected the midway location of the doubling driving band on the playback module transmission shaft, middle carrying roller, end reverse rollers and the shuttle vehicle frame end in the middle of the runway module and pass on the axle sleeve that is socketed in balance roller with the top of roller;
Controller module is made up of heavy-current control switch, light current master cock and meter counter, the heavy-current control switch only carries out switch control to the motor of boosting module and the motor of playback module, the light current master cock is only carried out switch control to power-transfer clutch and drg, be arranged on the meter counter on boosting module and the playback module guiding roller, the miles of relative movement that accurately detects driving band provides accurate on-off signal for the light current master cock.
The propelled method at random that does work is concentrated in the dispersion accumulation of energy of belt carrier-borne aircraft booster system, maximum boosting carrier-borne aircraft tonnage according to the design of boosting module assembly, below the runway module, arrange more than one boosting module, transmission shaft two ends on each boosting module connect a motor by power-transfer clutch at least, start the excessive electric net overload problem that causes of the total load that brings simultaneously in order to solve all motors of booster, the heavy-current control switch starts one by one to all motors makes its unloaded rotation disperse accumulation of energy, the normal transfer part component of rotation that also drives belt pulley and magnetic clutch behind the electric motor starting simultaneously disperses accumulation of energy, the motor in all booster modules all changes into electric energy kinetic energy and disperses to store in the system in unloaded rotation process like this, because the transmission shaft of all boosting modules all is to be connected with the shuttle module by driving band, the shuttle module is connected with carrier-borne aircraft again, when booster system need be carried out the boosting traction to carrier-borne aircraft, the light current master cock while is sent to the magnetic clutch on all boosting module transmission shafts, the power-transfer clutch adhesive, transmission shaft merged the kinetic energy of the rating horsepower of all boosting module motors and idle running storage to absorb by power-transfer clutch moment comes, finish concentrated acting at random on the shuttle module by concentrated being applied to of driving band, acting is exactly that boosting speed and the carrier-borne aircraft of shuttle assembly are bound from the takeoff speed on takeoff runway at random, also because transmission shaft is radix with the transmission shaft diameter when the coiling driving band begins, so driving band is with the low rotation speed large torque transferring power, because the increase along with the coiling number of plies, the winding speed of driving band increases sharply, and realizes boosting at random so the boosting acceleration/accel that driving band produces in winding process just in time matches with the acceleration/accel that takes off of carrier-borne aircraft;
Setting the length of boosting runway and the equal in length of driving band coiling is 100 meters, as long as the time set that the driving band that will equate with landing airdrome length is wound on the transmission shaft is 2.6 seconds, carrier-borne aircraft just can be run through 100 meters boosting runways in 2.6 second time, carrier-borne aircraft just can take off from the boosting runway smoothly, and computing formula is as follows:
Carrier-borne aircraft must obtain 30m/s on 100 meters runway
2Acceleration/accel just can take off, take off speed and acceleration movement Time Calculation formula is as follows:
V=√(2aL)=√(200×30)≈77.46m／s (1)
t=√(2L／a)=√(200／30)≈2.58s (2)
The length of the length=runway of driving band, L=is wrapped in each layer driving band length sum on the transmission shaft, the length of driving band
L=(L1+L2+ ... meter LN)=100=length (3) of boosting runway
Be wrapped in the length computation formula of every layer of driving band on the transmission shaft: Li=3.14(D+2dn) i=1,2,3 ... n (4)
D is the diameter of transmission shaft; The thickness of d=driving band; The number of plies of n=driving band
L=100=3.14[（D+2d1）+（D+2d2）+（D+2d3）+...（D+2dn）] （5）
The length of the length=driving band of known boosting runway=100 meter, ignore the density that driving band twines, the diameter D of transmission shaft, the numerical value substitution formula (4) of the thickness d of driving band calculates the length of every layer of driving band, length with each layer driving band is accumulated near 100 meters then, the number of plies of last one deck is set at twines the 100 meters needed axle of driving bands revolutions, because transmission shaft whenever turns around, driving band just twines one deck, so the accumulative total number of plies=axle revolution;
Known aircraft accelerates about 2.6 seconds of the departure time at 100 meters runways, accumulative total axle revolution/2.6 second=design rotations/sec, the cumulative length of driving band under accumulative total axle revolution is 100 meters, the rated revolution of selecting motor for use is X revolutions per second, being adjusted into the design revolution by strap speed varying is Y revolutions per second, converter speed ratio=X commentaries on classics/Y changes, as long as motor provides Y revolutions per second rotating speed for transmission shaft by belt pulley, the boosting module just can accelerate to carrier-borne aircraft the takeoff speed of 80 meter per seconds at 100 meters runway in 2.6 seconds.
Excellent effect of the present invention is,
1) design science is reasonable, the accelerated mode of booster by speed time curve as can be seen, speed is by accelerating slowly, the even change accelerates, if aircraft departure time on 100 meters runways is 2.6 seconds, the takeoff speed at first second end is no more than 30 meters, the takeoff speed at second second end can reach the takeoff speed requirement of 80 meter per seconds, because energy is not to break out formula to discharge, so, capacity usage ratio can reach more than 98%, because booster of the present invention is the ingenious pure theory of machines of having used, comprises speed, time, use power and mechanical strength, all data parameters all are to design and to calculate, state-of-art according to present comprise propulsion source, electronic controller and driving band can both satisfy the requirement of the at present known various carrier-borne aircrafts of booster boosting;
2) height hommization, the boosting process of booster of the present invention has the powerful tractive force of slower initial velocity, whole accelerator and the aircraft accelerating performance on the airport matches, accelerating ability is hommization very, the aviator is fast to the overload reactive adaptation in the accelerated take-off process, can not use constant boosting speed as traditional booster, the moment that occurs when causing aviator's accelerated take-off goes into a coma;
3) volume is little, and is simple in structure, occupies little space, the boosting landing airdrome length is unrestricted, not limited by radian, not only can use on the sliding formula aircraft carrier deck that jumps, can use on aircraft carrier deck, plane yet, the groove depth of boosting runway on flight deck is no more than 50 centimeters, width is no more than 100 centimeters, and sectional area is no more than 0.5 square meter, can save a large amount of usage spaces for aircraft carrier, main frame takies the cabin area and is no more than 30 square meters, 30 tons of total weight less thaies;
4) save the energy, the propulsion source range of choice is wide, selects for use electrical motor or the diesel engine of 500-1000 kilowatt of 6-12 platform to do power, and gross horsepower horsepower input 6000KW gets final product, and energy consumption is more few, and exploitativeness is more high;
5) control simply, operation realizes an intelligent key control, can be by manual control or remote manipulation, realize the automatic boosting of shuttle and return automatically, boosting speed has multiple choices, if motor adopts frequency converter or governor control, can adapt to the boosting needs that various carrier-borne aircrafts comprise unmanned plane;
6) simple in structure, high modularization has characteristics such as easy processing, easily transportation, easily installation, easily debugging, easy care;
7) capacity usage ratio height, significantly do not rub and resistance in the total system of the present invention, the little in light weight and operation in the grooved track of sliding lock assembly volume is in the rolling condition of low resistance all the time, driving band from boosting move back module to the playback module migration also be to roll in commutation, low-resistance rolling contact condition on guiding roller and the middle carrying roller, and all adopt the low-resistance bearing in the above-mentioned roller, especially the module that playbacks is not needing to provide under the situation of any energy for the shuttle assembly, the most scientific and reasonable reverse traction damping is provided, so can be reduced to power consumption minimum, because system is partly switched with accumulation of energy the acting part by power-transfer clutch, accumulation of energy partly refers to the A end that motor pulley and power-transfer clutch are formed, the acting part refers to transmission shaft, the passive part that driving band and shuttle assembly are formed, after the acting part is finished merit, power-transfer clutch discharges, the accumulation of energy part enters energy accumulating state immediately again, so total system is in the maximum energy-saving state all the time, so the capacity usage ratio of system of the present invention is more than 98%.
Description of drawings:
Fig. 1 is the booster system structural representation that single boosting module and single playback module are formed;
Fig. 2 is the structural representation that many boostings module and single playback module are formed booster system;
Fig. 3 is the section structure scheme drawing of boosting module or playback module;
The structure scheme drawing that Fig. 4 list boosting module and single playback module transmission shaft are connected with the shuttle assembly by driving band;
Fig. 5 is many boostings module transmission shaft and single playback module transmission shaft and shuttle assembly connection structure scheme drawing;
Fig. 6 is the speed/time curve of steam catapult or electromagnetic type ejector, and the interview of curve below is the consumption of power scheme drawing;
Fig. 7 is the speed time curve of belt carrier-borne aircraft booster system, and the area of curve below is consumption of power situation scheme drawing.
Description of reference numerals: base 1, T shape casing 2, power-transfer clutch 3, belt pulley 4, drg 5, driving band pressing plate 6, grooved track 7 also are with roller 8, axle sleeve 9, shuttle 10, shuttle vehicle frame 11, roller 12, transmission shaft 13, motor l4, driving band 15, guiding roller 16, meter counter 17, runway carriage 18, middle carrying roller 19, balance roller 20.
The specific embodiment
Concentrate work method to do following detailed explanation with reference to accompanying drawing to belt carrier-borne aircraft booster system and dispersion accumulation of energy.
Shown in Fig. 1-7, booster system comprises boosting module assembly, playback module assembly, runway module, shuttle module and controller module, wherein:
The boosting module assembly is listed in runway module below by an above boosting module row and forms, the boosting module comprises T shape casing, driving band 15, motor, transmission shaft, power-transfer clutch, drg and base, wherein T shape casing 2 bottoms and base 1 center fixed, motor 14 is fixed on the both sides that are positioned at T shape casing 2 on the base 1, transmission shaft 13 is applied in centre at T shape casing 2 by bearing seat, the two ends of transmission shaft 13 are respectively arranged with power-transfer clutch 3 and drg 5, the passive part of power-transfer clutch 3 and drg 5 are fixed with transmission shaft, the A end of power-transfer clutch 3 is connected with belt pulley 4, belt pulley 4 is connected with transmission shaft 13 by bearing, the cylindrical of belt pulley 4 is connected by the belt pulley of belt with motor 14 axle heads, driving band 15 two ends after the doubling are fixed on the transmission shaft 13 that is positioned at T shape casing 2 centres by belt pressing plate 6, driving band 15 centre portions after the doubling are connected with the shuttle assembly, the top of T shape casing 2 is provided with guiding roller 16, be connected with meter counter 17 on the guiding roller 16, driving band 15 passes in the middle of guiding roller 16 and meter counter 17, the two ends on T shape casing 2 tops are connected with the runway module, the top of T shape casing 2 is provided with grooved track 7, and grooved track 7 is connected in series with the grooved track at runway module top;
The playback module assembly is listed in runway module below by playback module row more than and forms, structure is identical with the boosting module, the playback module comprises T shape casing 2, driving band 15 motors 14, transmission shaft 13, power-transfer clutch 3, drg 5 and base 1, wherein T shape casing 2 bottoms and base 1 center fixed, motor 14 is fixed on the both sides that are positioned at T shape casing 2 on the base 1, transmission shaft 13 is applied in centre at T shape casing 2 by bearing seat, the two ends of transmission shaft 13 are respectively arranged with power-transfer clutch 3 and drg 5, the passive part of power-transfer clutch 3 and drg 5 are fixing with transmission shaft 13, the A end of power-transfer clutch 3 is connected with belt pulley 4, belt pulley 4 is connected with transmission shaft 13 by bearing, the cylindrical of belt pulley 4 is connected by the belt pulley of belt with motor 14 axle heads, driving band 15 two ends after the doubling are fixed on the transmission shaft 13 that is positioned at T shape casing 2 centres by driving band pressing plate 20, driving band 15 centre portions after the doubling are connected with the shuttle assembly, the top of T shape casing 2 is provided with guiding roller 16, be connected with meter counter 17 on the guiding roller 16, driving band 15 passes in the middle of guiding roller 16 and meter counter 17, the two ends on T shape casing 2 tops are connected with the runway module, the top of T shape casing 2 is provided with grooved track 7, and grooved track 7 is connected in series with the grooved track at runway module top;
The runway module is made up of runway carriage 18, reverse rollers 14, middle carrying roller 22 and grooved track 7, runway carriage 18 is connected between boosting module and the playback module and two ends, for the shuttle module is formed the linear slide runway, the end that reverse rollers 14 is arranged on the runway module provides the transmission guiding for driving band 15, and middle carrying roller 22 is arranged on the centre of runway module and lifts holder for driving band 15 provides guiding;
The shuttle module is arranged among the grooved track 7, its structure is by shuttle 10, shuttle vehicle frame 11, roller 12 and be with roller 8 and balance roller 20 is formed, and band roller 8 is arranged on the outside at shuttle vehicle frame 11 two ends, balance roller 20 is arranged on and is with between the roller 8, and be with roller 8 and balance roller 20 to be formed by roll shaft and axle sleeve 9, it is protruding that two downward flange of shuttle vehicle frame 11 are run through at the two ends of roll shaft, the two ends that roller 12 is arranged on roll shaft are connected with the both sides groove rolling of grooved track 7, and axle sleeve 9 is arranged on the centre of roll shaft between two downward flange of shuttle vehicle frame 11; Be connected the midway location of the doubling driving band 15 on the boosting module transmission shaft 13, the middle carrying roller 19 in the middle of the runway module, end reverse rollers 14 and and pass on the axle sleeve 9 that is socketed in balance roller 20 with the top of roller 8; The midway location that connects the doubling driving band 15 on the playback module transmission shaft 13, middle carrying roller 22, end reverse rollers 14 and shuttle vehicle frame 11 ends in the middle of the runway module and pass on the axle sleeve 9 that is socketed in balance roller 20 with the top of roller 8;
Controller module is made up of heavy-current control switch, light current master cock and meter counter 17, and the heavy-current control switch is only to the boosting mould
The motor 14 of the motor 14 of piece and playback module carries out switch control, the light current master cock is only carried out switch control to power-transfer clutch 3 and drg 5, be arranged on the meter counter 17 on boosting module and the playback module guiding roller 16, the miles of relative movement that accurately detects driving band 15 provides accurate on-off signal for the light current master cock.
Motor, power-transfer clutch, drg, heavy-current control switch, light current master cock and meter counter be commercially available general-purpose machinery and electrical applicances, and power-transfer clutch and drg comprise electromagnetic mode or start-up mode.
Setting the length of boosting runway and the equal in length of driving band coiling is 100 meters, as long as the time set that the driving band that will equate with landing airdrome length is wound on the transmission shaft is 2.6 seconds, carrier-borne aircraft just can be run through 100 meters boosting runways in 2.6 second time, carrier-borne aircraft just can take off from the boosting runway smoothly, and computing formula is as follows:
Carrier-borne aircraft must obtain 30m/s on 100 meters runway
2Acceleration/accel just can take off, take off speed and acceleration movement Time Calculation formula is as follows:
V=√(2aL)=√(200×30)≈77.46m／s (1)
t=√(2L／a)=√(200／30)≈2.58s (2)
The length of the length=runway of driving band, L=is wrapped in each layer driving band length sum on the transmission shaft, the length of driving band
L=(L1+L2+ ... meter LN)=100=length (3) of boosting runway
Be wrapped in the length computation formula of every layer of driving band on the transmission shaft: Li=3.14(D+2dn) i=1,2,3 ... n (4)
D is the diameter of transmission shaft; The thickness of d=driving band; The number of plies of n=driving band
L=100=3.14[（D+2d1）+（D+2d2）+（D+2d3）+...（D+2dn）] （5）
The length of the length=driving band of known boosting runway=100 meter, ignore the density that driving band twines, the diameter D of transmission shaft, the numerical value substitution formula (4) of the thickness d of driving band calculates the length of every layer of driving band, length with each layer driving band is accumulated near 100 meters then, the number of plies of last one deck is set at twines the 100 meters needed axle of driving bands revolutions, because transmission shaft whenever turns around, driving band just twines one deck, so the accumulative total number of plies=axle revolution;
Known aircraft accelerates about 2.6 seconds of the departure time at 100 meters runways, accumulative total axle revolution/2.6 second=design rotations/sec, the cumulative length of driving band under accumulative total axle revolution is 100 meters, the rated revolution of selecting motor for use is X revolutions per second, being adjusted into the design revolution by strap speed varying is Y revolutions per second, converter speed ratio=X commentaries on classics/Y changes, as long as motor provides Y revolutions per second rotating speed for transmission shaft by belt pulley, the boosting module just can accelerate to carrier-borne aircraft the takeoff speed of 80 meter per seconds at 100 meters runway in 2.6 seconds.
The calculating of boosting module assembly power, the calculating of the calculating boosting module assembly power of driving band breaking strength, comprise that reverse predication method and test predication method calculate, wherein oppositely predication method is: the power according to disclosed power steam catapult the biggest in the world is 6.4 ten thousand kilowatts, its the effective merit that is actually used in the traction carrier-borne aircraft has only 4%, 64000 kilowatts * 4%=2560 kilowatt, be radix for 3000 kilowatts with the effective merit of reality, each boosting module is by two electric machine design, every power of motor is 500 kilowatts, amount to 1000 kilowatts, three boosting module gross horsepowers are 3000 kilowatts, known antisubmarine plane or early warning plane tonnage are 60 tons, every kilowatt boosting quality is 60000 kilograms/3000 kilowatts=20 kilograms, and namely every kilowatt motor can accelerate to 20 kilograms object the takeoff speed of 80 meter per seconds in 2.6 seconds on 100 meters runways; Because the employed power of system of the present invention can increase by the power that increases motor or the quantity that increases the boosting module, so have good alerting ability;
Because existing various boosting modes comprise the various parameters of carrier-borne aircraft, it all is military secrecy, very difficult acquisition among the people, intelligence obtains by test, and method is miniature belt type carrier-borne aircraft booster system of design, long 100 meters of design runway, select 1 kilowatt of power of motor for use, running through the quality that boosting is gone out behind 100 meters runways in 2.6 seconds is radix, radix=kilogram/kilowatt, 60000 kilograms/radix=design horse power;
Verify feasibility of the present invention according to the method for making up the difference, known 15 the gr.wt. of destroying is 33 tons, light mass is 27 tons, destroying 15 can take off at the sliding formula runway that jumps under no-load condition, fly and can not glide to jumping up in full load conditions, carrying out boosting by assist system of the present invention makes up the difference, the boosting power that the object of 6 tons of quality is accelerated to 80 meter per second speed imposes on destroys 15, destroying 15 can fully loaded takeoff, according to top radix=kilogram/kilowatt formula, calculate one of 6000 kilograms/radix=boosting and be fully loaded with 15 desired power of destroying that meet.
Embodiment
Design procedure is as follows:
Carrier-borne aircraft must obtain 30m/s on 100 meters runway
2Acceleration/accel just can take off, take off speed and acceleration movement Time Calculation formula is as follows:
V=√(2aL)=√(200×30)≈77.46m／s (1)
t=√(2L／a)=√(200／30)≈2.58s (2)
The length of the length=runway of driving band, L=is wrapped in each layer driving band length sum on the transmission shaft, the length of driving band
L=(L1+L2+ ... meter LN)=100=length (3) of boosting runway
The length computation formula of every layer of driving band of transmission shaft: Li=3.14(D+2dn) (4)
D is the diameter of transmission shaft,
The thickness of d=driving band;
The number of plies of n=driving band
L=100=3.14[（D+2d1）+（D+2d2）+（D+2d3）+...（D+2dn）] （5）
The density that driving band twines is ignored in the length of the length=driving band of known boosting runway=100 meter, sets the diameter D axle of transmission shaft=0.3 meter; The thickness d of driving band=0.02 meter; The coiling length of every layer of driving band (rice) Li=3.14(D+2dn)
The length of calculating each layer driving band according to formula (4) is respectively:
L1=3.14(0.3+0.04*1)=3.14*0.34=1.676 1.676
L2=3.14(0.3+0.04*2)=3.14*0.38=1.1932 2.8692
L3=3.14(0.3+0.04*3)=3.14*0.42= 1.3188 4.188
L4=3.14(0.3+0.04*4)=3.14*0.46= 1.4444 5.6324
L5=3.14(0.3+0.04*5)=3.14 *0.5= 1.57 7.2024
L6=3.14(0.3+0.04*6)=3.14*0.54=1.6956 8.898
L7=3.14(0.3+0.04*7)=3.14*0.58=1.8212 10.7192
L8=3.14(0.3+0.04*8)= 3.14*0.72= 2.2608 12.98
L9=3.14(0.3+0.04*9)=3.14 *0.66 =2.0724 15.0524
L1O=3.14(0.3+0.04*1 0)=3.14*0.7= 2.198 17.2504
L11=3.14(0.3+0.04*11)=3.14*0.74= 2.3236 19.574
L12=3.14(0.3+0.04*12)= 3.14*0.78=2.4492 22.0232
L13：3.14(0.3+0.04*13)= 3.14* 0.82=2.5748 24.6016
L14=3.14(0.3+0.04*14)= 3.14*0.86=2.7 27.3016
L15=3.14(0.3+0.04*15)= 3.14*0.9= 2.826 30.2532
L16=3.14(0.3+0.04*16)= 3.14* 0.94=2.9516 33.2048
L17=3.14(0.3+0.04*17)= 3.14*0.98=3.0772 36.282
L18=3.14(0.3+0.04*18)= 3.14* 1.02= 3.2028 39.4848
L19：3.14(0.3+0.04*19)= 3.14* 1.06=3.3284 42.8132
L20=3.14(0.3+0.04*20)= 3.14* 1.1=3.454 46.2672
L21=3.14(0.3+0.04*21)= 3.14*1.14=3.5796 49.8468
L22=3.14(0.3+0.04*22)= 3.14* 1.18=3.7052 53.552
L23=3.14(0.3+0.04*23)= 3.14*1.22=3.8308 57.3828
L24=3.14(0.3+0.04*24)=3.14*1.26=3.9564 61.3392
L25=3.14(0.3+0.04*25)=3.14*1.3=4.082 65.4212
L26=3.14(0.3+0.04*26)=3.14*1.34=4.2076 69.6288
L27=3.14(0.3+0.04*27)=3.14*1.38=4.3332 73.962
L28=3.14(0.3+0.04*28)=3.14*1.42=4.458 78.42
L29=3.14(0.3+0.04*29)=3.14*1.46=4.5844 83.0044
L30=3.14(0.3+0.04*30)= 3.14*1.5= 4.71 87.754
L31=3.14(0.3+0.04*31)= 3.14* 1.54= 4.8356 92.5896
L32=3.14(0.3+0.04*32)= 3.14*1.58=4.9612 97.5508
L33=3.14(0.3+0.04*33)=3.14*1.6= 5.0868 102.6376
The length of each layer driving band is placed in the speed time curve coordinate, makes speed time curve, as shown in Figure 7;
According to calculating: the total length of the 33rd layer of driving band is L=(LI+L2+ ... meter L21)=102.6, outmost turns driving band diameter is 1.6 meters, calculates the maximum gauge of tep reel and selects 2 meters for use, and the width of tep reel is decided on the width of driving band.
Known aircraft accelerates about 2.5 seconds of the departure time at 100 meters runways, per second rope woolding 33/2.5 ≈ 13 circles, driving band is 102 meters at 33 layers cumulative length, if select for use motor that power is provided, the rated speed of rotation of motor is 1500 rev/mins, and the per second rotating speed is 25 commentaries on classics, is adjusted into 13 revolutions per seconds by speed change, converter speed ratio 25/13 can reach the takeoff speed of carrier-borne aircraft for transmission shaft provides 13 revolutions per seconds rotating speed.
By above-mentioned calculating as can be seen, air speed was about 24 meters in first second, the aircraft stroke was about 70 meters in second second, 2.5 flight is 102 meters during second, driving band twines 44 circles altogether on transmission shaft, aircraft was run through runway whole process in 2.5 seconds, and accelerated mode and driving band the speed of wrap on tep reel of aircraft on the boosting runway is synchronous fully, and accelerated mode is hommization very, can not cause damage to chaufeur and aircraft.
Selecting for use of driving band, select the nylon6 chips base band for use, gross thickness 6-10cm, width 50-100cm, tensile strength are the 100-200 tons, if select the carbon fiber composite sheet base band of identical basal area for use, breaking strength can reach the 250-300 ton, and it is 33 tons that Soviet Union 33 is fully loaded with, and 3-10 times of above safety factor arranged, the boosting runway has only 0.6-1.2 rice at the deck groove width, and the degree of depth gets final product for 0.30-0.50 rice.
If power is selected diesel engine for use, diesel engine provides extra even acceleration by regulating throttle, the takeoff speed of carrier-borne aircraft can also be up and down 20 one 50% float.
Carrier-borne aircraft boosting step is as follows:
1) shuttle is positioned at the runway starting point, is connected with the carrier-borne aircraft nose-gear by hanging device, and aero-engine refuels, and waits for takeoff order;
2) takeoff order is assigned, the adhesive of boosting module power-transfer clutch, the whole energy of motor pass to transmission shaft by power-transfer clutch, transmission shaft rotates driving band is twined, and driving band passes to shuttle with shp, the starting of shuttle traction carrier-borne aircraft, along with driving band increases in the number of plies that transmission shaft twines, haulage speed is more and more faster, and shuttle moves to the runway terminal point, and carrier-borne aircraft reaches takeoff speed and takes off smoothly;
When 3) shuttle is about to arrive the runway terminal point, the movable length of meter counter accurate measurement driving band, the equal in length of meter counter pre-set length and runway, when equal in length that meter counter preseting length and driving band move, meter counter sends speed-slackening signal to control module, power-transfer clutch on the control module control boosting module discharges, stop to transmit power, drg on boosting module and the playback module is braked simultaneously, transmission shaft stops operating simultaneously on boosting module and the playback module, and shuttle accurately is positioned at the runway terminal point;
4) shuttle is after the runway terminal point stops, delay time 1-3 second, drg on boosting module and the playback module discharges simultaneously, power-transfer clutch adhesive on the playback module, the driving band that is wrapped on the boosting module transmission shaft oppositely twines on playback module transmission shaft, shuttle is moved to the runway starting point by the runway terminal point, meter counter measures the driving band transfer length again, after the driving band transfer length reaches setting value, meter counter sends speed-slackening signal to control module, and the power-transfer clutch on the control module control playback module discharges, and the drg on boosting module and the playback module is braked simultaneously, shuttle accurately is positioned on the runway starting point, prepares next sortie carrier-borne aircraft accelerated take-off.
Claims (3)
1. a belt carrier-borne aircraft booster system is characterized in that, system comprises boosting module assembly, playback module assembly, runway module, shuttle module and controller module, wherein:
The boosting module assembly is listed in runway module below by an above boosting module row and forms, the boosting module comprises T shape casing, motor, transmission shaft, power-transfer clutch, drg and base, wherein T shape bottom half and base center fixed, motor is fixed on the both sides that are positioned at T shape casing on the base, transmission shaft is applied in centre at T shape casing by bearing seat, the two ends of transmission shaft are respectively arranged with power-transfer clutch and drg, the passive part of power-transfer clutch and drg and transmission shaft are fixed, the A end of power-transfer clutch is connected with belt pulley, belt pulley is connected with transmission shaft by bearing, the cylindrical of belt pulley is connected with the belt pulley of motor shaft end by belt, driving band two ends after the doubling are fixed on by the belt pressing plate and are positioned on the middle transmission shaft of T shape casing, driving band centre portion after the doubling is connected with the shuttle assembly, the top of T shape casing is provided with guiding roller, is connected with meter counter on the guiding roller
,Driving band passes in the middle of guiding roller and meter counter, and the two ends on T shape casing top are connected with the runway module, and the top of T shape casing is provided with the grooved track, and the grooved track is connected in series with the grooved track at runway module top;
The playback module assembly is listed in runway module below by playback module row more than and forms, the playback module comprises T shape casing, motor, transmission shaft, power-transfer clutch, drg and base, wherein T shape bottom half and base center fixed, motor is fixed on the both sides that are positioned at T shape casing on the base, transmission shaft is applied in centre at T shape casing by bearing seat, the two ends of transmission shaft are respectively arranged with power-transfer clutch and drg, the passive part of power-transfer clutch and drg and transmission shaft are fixed, the A end of power-transfer clutch is connected with belt pulley, belt pulley is connected with transmission shaft by bearing, the cylindrical of belt pulley is connected with the belt pulley of motor shaft end by belt, driving band two ends after the doubling are fixed on by the belt pressing plate and are positioned on the middle transmission shaft of T shape casing, driving band centre portion after the doubling is connected with the shuttle assembly, the top of T shape casing is provided with guiding roller, is connected with meter counter on the guiding roller
,Driving band passes in the middle of guiding roller and meter counter, and the two ends on T shape casing top are connected with the runway module, and the top of T shape casing is provided with the grooved track, and the grooved track is connected in series with the grooved track at runway module top;
The runway module is made up of runway carriage, reverse rollers, middle carrying roller and grooved track, the runway carriage is connected between boosting module and the playback module and two ends, for the shuttle module is formed the linear slide track, the end that reverse rollers is arranged on the runway module provides the transmission guiding for driving band, and middle carrying roller is arranged on the centre of runway module and lifts holder for driving band provides guiding;
The shuttle module is arranged among the grooved track, its structure is by shuttle, shuttle vehicle frame, roller and be with roller and balance roller is formed, and the band roller is arranged on the outside at shuttle vehicle frame two ends, balance roller is arranged on and is with between the roller, and be with roller and balance roller to be formed by roll shaft and axle sleeve, it is protruding that two downward flange of shuttle vehicle frame are run through at the two ends of roll shaft, the two ends that roller is arranged on roll shaft are connected with the both sides groove rolling of grooved track, and axle sleeve is arranged on the centre of roll shaft between two downward flange of shuttle vehicle frame; Be connected the midway location of the doubling driving band on the boosting module transmission shaft, the middle carrying roller in the middle of the runway module, end reverse rollers and and pass on the axle sleeve that is socketed in balance roller with the top of roller; Be connected the midway location of the doubling driving band on the playback module transmission shaft, middle carrying roller, end reverse rollers and the shuttle vehicle frame end in the middle of the runway module and pass on the axle sleeve that is socketed in balance roller with the top of roller;
Controller module is made up of heavy-current control switch, light current master cock and meter counter, the heavy-current control switch only carries out switch control to the motor of boosting module and the motor of playback module, the light current master cock is only carried out switch control to power-transfer clutch and drg, be arranged on the meter counter on boosting module and the playback module guiding roller, the miles of relative movement that can accurately detect driving band is the light current master cock
Accurate on-off signal is provided.
2. boosting work method is at random concentrated in the dispersion accumulation of energy of belt carrier-borne aircraft booster system, it is characterized in that, every carrier-based aircraft ejector must have powerful energy-storage system, maximum carrier-borne aircraft tonnage according to boosting module assembly design boosting, below the runway module, arrange more than one boosting module, transmission shaft two ends on each boosting module connect a motor by power-transfer clutch at least, start the excessive electric net overload problem that causes of the total load that brings simultaneously in order to solve all motors of booster, the heavy-current control switch starts one by one to all motors makes its unloaded rotation disperse accumulation of energy, the normal transfer part component of rotation that also drives belt pulley and magnetic clutch behind the electric motor starting simultaneously disperses accumulation of energy, motor in the system in all booster modules all changes into kinetic energy with electric energy in unloaded rotation process disperses to store, because the transmission shaft of all boosting modules all is to be connected with the shuttle module by driving band, the shuttle module is connected with carrier-borne aircraft again, when booster system is accelerated the huge kinetic energy of boosting moment needs to carrier-borne aircraft, the light current master cock while is sent to the magnetic clutch on all boosting module transmission shafts, the power-transfer clutch adhesive, transmission shaft merged the kinetic energy of the rating horsepower of all boosting module motors and idle running storage to absorb by power-transfer clutch moment comes, finish concentrated acting at random on the shuttle module by concentrated being applied to of driving band, acting is exactly that boosting speed and the carrier-borne aircraft of shuttle assembly are bound from the takeoff speed on takeoff runway at random, also because transmission shaft is radix with the transmission shaft diameter when the coiling driving band begins, so driving band is with the low rotation speed large torque transferring power, because the increase along with the coiling number of plies, the winding speed of driving band increases sharply, and realizes boosting at random so the boosting acceleration/accel that driving band produces in winding process just in time matches with the acceleration/accel that takes off of carrier-borne aircraft; The boosting speed designs is as follows:
Setting the length of boosting runway and the equal in length of driving band coiling is 100 meters, as long as the time set that the driving band that will equate with landing airdrome length is wound on the transmission shaft is 2.6 seconds, carrier-borne aircraft just can be run through 100 meters boosting runways in 2.6 second time, carrier-borne aircraft just can take off from the boosting runway smoothly, and computing formula is as follows:
Carrier-borne aircraft must obtain 30m/s on 100 meters runway
2Acceleration/accel just can take off, take off speed and acceleration movement Time Calculation formula is as follows:
V=√(2aL)=√(200×30)≈77.46m／s (1)
t=√(2L／a)=√(200／30)≈2.58s (2)
The length of the length=runway of driving band, L=is wrapped in each layer driving band length sum on the transmission shaft, the length of driving band
L=(L1+L2+ ... meter LN)=100=length (3) of boosting runway
Be wrapped in the length computation formula of every layer of driving band on the transmission shaft: Li=3.14(D+2dn) i=1,2,3 ... n (4)
D is the diameter of transmission shaft; The thickness of d=driving band; The number of plies of n=driving band
L=100=3.14[（D+2d1）+（D+2d2）+（D+2d3）+...（D+2dn）] （5）
The length of the length=driving band of known boosting runway=100 meter, ignore the density that driving band twines, the diameter D of transmission shaft, the numerical value substitution formula (4) of the thickness d of driving band calculates the length of every layer of driving band, length with each layer driving band is accumulated near 100 meters then, the number of plies of last one deck is set at twines the 100 meters needed axle of driving bands revolutions, because transmission shaft whenever turns around, driving band just twines one deck, so the accumulative total number of plies=axle revolution;
Known aircraft accelerates about 2.6 seconds of the departure time at 100 meters runways, accumulative total axle revolution/2.6 second=design rotations/sec, the cumulative length of driving band under accumulative total axle revolution is 100 meters, the rated revolution of selecting motor for use is X revolutions per second, being adjusted into the design revolution by strap speed varying is Y revolutions per second, converter speed ratio=X commentaries on classics/Y changes, as long as motor provides Y revolutions per second rotating speed for transmission shaft by belt pulley, the boosting module just can accelerate to carrier-borne aircraft boosting on 100 meters runway the takeoff speed of 80 meter per seconds in 2.6 seconds.
3. the shuttle terminal point of belt carrier-borne aircraft booster system oppositely draws damping method, it is characterized in that the driving band at sliding lock assembly two ends is connected on the transmission shaft of boosting module and playback module, the length of boosting module driving band that transmission shafts twines and speed equate, adopt meter counter to make the movable length that sensor accurately detects driving band, the miles of relative movement of accurate Calculation sliding lock assembly, after accurately detecting the sliding lock assembly miles of relative movement that sets when meter counter, by control module the drg on the playback module transmission shaft is accurately controlled, and when the sliding lock assembly moves to runway module terminal point, be wrapped in the cooling diameter minimum of driving band on the playback module transmission shaft, so lock torque maximum, utilize driving band to make the plugging medium, the sliding lock assembly that moves to runway module terminal point is not had power consumption and oppositely traction most effectively, realize that the shuttle assembly is in the pinpoint braking of runway terminal point terminal point.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310272662.XA CN103332297B (en) | 2013-07-02 | 2013-07-02 | Random boosting work method is concentrated in a kind of belt carrier-borne aircraft booster system and dispersion accumulation of energy |
| PCT/CN2014/081448 WO2015000407A1 (en) | 2013-07-02 | 2014-07-02 | Belt-type carrier-based aircraft booster system, and method of working with centralized and random boosting with distributed energy storage |
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| CN201310272662.XA CN103332297B (en) | 2013-07-02 | 2013-07-02 | Random boosting work method is concentrated in a kind of belt carrier-borne aircraft booster system and dispersion accumulation of energy |
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| CN104002983A (en) * | 2014-05-30 | 2014-08-27 | 陈亮 | Aircraft take-off and landing device |
| WO2015000407A1 (en) * | 2013-07-02 | 2015-01-08 | 济南环太机电技术有限公司 | Belt-type carrier-based aircraft booster system, and method of working with centralized and random boosting with distributed energy storage |
| CN104890893A (en) * | 2014-03-09 | 2015-09-09 | 徐延明 | Aircraft carrier catapult |
| CN106314816A (en) * | 2016-08-23 | 2017-01-11 | 济南环太机电技术有限公司 | Mechanical and electronic integration dynamic energy-storage type shipboard aircraft catapult system |
| CN106477063A (en) * | 2016-08-23 | 2017-03-08 | 济南环太机电技术有限公司 | Multipurpose dynamic energy storage type carrier-based aircraft ejector system and its using method |
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| 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 |
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| CN106314816A (en) * | 2016-08-23 | 2017-01-11 | 济南环太机电技术有限公司 | Mechanical and electronic integration dynamic energy-storage type shipboard aircraft catapult system |
| CN106477063A (en) * | 2016-08-23 | 2017-03-08 | 济南环太机电技术有限公司 | Multipurpose dynamic energy storage type carrier-based aircraft ejector system and its using method |
| CN106477063B (en) * | 2016-08-23 | 2019-02-26 | 济南环太机电技术有限公司 | Multipurpose dynamic energy storage type carrier-based aircraft ejector system and its application method |
| ES2657050A1 (en) * | 2016-08-30 | 2018-03-01 | Fco. Javier Porras Vila | Train gear-cone in the engine launches-aircraft of an aircraft carrier (Machine-translation by Google Translate, not legally binding) |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2015000407A1 (en) | 2015-01-08 |
| CN103332297B (en) | 2016-04-20 |
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