CN102120495A - Ski jump carrier-based aircraft catapult and catapulting method thereof - Google Patents
Ski jump carrier-based aircraft catapult and catapulting method thereof Download PDFInfo
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- CN102120495A CN102120495A CN2010102851414A CN201010285141A CN102120495A CN 102120495 A CN102120495 A CN 102120495A CN 2010102851414 A CN2010102851414 A CN 2010102851414A CN 201010285141 A CN201010285141 A CN 201010285141A CN 102120495 A CN102120495 A CN 102120495A
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Abstract
The invention provides a ski jump carrier-based aircraft catapult and a catapulting method thereof. The ski jump carrier-based aircraft catapult consists of a power machine, clutches, a flywheel, a transmission shaft, a traction winch and a rope releasing winch, wherein the traction winch and the flywheel are arranged on the transmission shaft; 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 frame; 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 acceleration type carrier-based aircraft catapult has the characteristics of reasonable design, simple structure, safety, reliability, small volume, high automation degree, convenience of use, simple maintenance and the like, and has high promotion and application value.
Description
Technical field
The present invention relates to a kind of military equipment or aircraft carrier ejector, a kind of specifically cunning jump formula aircraft carrier 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 steam-type ejector to use on U.S. army's aircraft carrier, and this ejector uses steam to be used as power to drive hauling hook pulling aircraft by steam cylinder piston and quickens to take off.The steam catapult equipment volume is huge, occupies than large space, and steam boiler must be arranged, consumed energy is big, operating cost height, maintenance cost height, it is big to consume the fresh water amount in addition, straight news reporting is arranged, and the airplane catapult system of eaglet number or Mi Nizi whenever launches an airplane and consumes nearly 1 ton of fresh water, fresh water is heated into high temperature and high pressure steam, consume lot of energy, only the energy of ejector consumption accounts for 2096 of whole aircraft carrier energy, and huge fresh water consumption is a problem of can not ignore; The manufacturing process of steam catapult is quite complicated, having only the U.S., France and Britain to grasp at present has the technology of making steam catapult, the steam catapult of having grasped at present, its structure is that two parallel length are 90 meters, diameter is the cylinder that cracks of 457mm, also need 2 meters of supporting two huge diameters, length is 20 meters vapour storage tanks, about 600 cubic meters of cumulative volume, and volume is so huge, usually using on the nuclear aircraft carrier more than 70,000 tons, having only the U.S. that nuclear aircraft carrier is arranged at present.So-called steam catapult, actual is exactly that a steam launches big gun, and according to the pertinent data report, because initial velocity is crossed the stupor that conference produces moment, aircraft needs flight instrument automatic guidance automatically to the aviator when catapult-assisted take-off, waits the aviator to wake up the back in pilot steering.If chaufeur stupor overlong time, it also is unrare thing that aircraft falls into the sea.Big except volume, cost is high, power consumption is high, maintenance and also make service life U.S. army feel more headache, according to the report steam catapult use 500 times will overhaul, the cylinder life-span is 2000 times, promptly launches 2000 sorties, cylinder will be changed.So new ejector alternative is also being sought by U.S. army, and good result is not also arranged at present.
According to my analysis, the catapult technique of carrier-borne aircraft is not that to have only steam catapult be unique, selects steam why when the U.S. and launches, and reason has the following aspects,
1) abundant warship technology and the sufficient expenses of military expenditure made, the U.S. is in the military expenditure abundance and enrich the large-scale nuclear aircraft carrier of building under the marine technology support that is mostly, this is that micro state and developing country can't unrealistically compare, so utilize the huge function of steaming of nuclear reactor, the first-selected steam catapult that is used as power with steam also is understandable.
2) purposely make a mystery of simple things, threshold develops skill, in order to prevent shipbuilding capacity and the emergence of the development aircraft carrier country that has the ability, the technical threshold of building aircraft carrier is too high, also be a kind of mode of technical monopoly, so utilize the huge function of steaming of nuclear reactor, first-selection is used as power with steam, make two steam cylinders that crack of 98.5 meters that other countries can not make, although it feels also that this ejection mode is not handy itself, do not remove to propagate and research and develop simpler effectively other handy ejection modes yet, not so be that a country all can make aircraft carrier, all aircraft carrier has been arranged, the maritime hegemony status has not just been protected, this just and your satellite, others also has satellite, you have guided missile, others also has guided missile, and you have nuclear weapon, and others also has nuclear weapon the same, everybody has had, and just nothing can be put on airs:
By above-mentioned analysis; the economic advantages of the U.S. are along with the generation of world crisis loses gradually; technical advantage also can't be permanent losing under the prerequisite of economic advantages, is penetrated by people so do arcane truth party early, and simpler wholesale effectively safer carrier-based aircraft ejector must substitute steam catapult.
Second kind is cunning on the Russian aircraft carrier formula flight deck that jumps, be that aircraft leans on and self quickens above deck to realize that by the runway that is upturned the sliding formula that jumps flies from warship, 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, single engine opportunity of combat can't be used, so the machine of carrier-borne aircraft is received restriction.In addition, the sliding formula of the jumping mode of taking off is to take off by aircraft self power, so can not fully loaded takeoff, take-off weight only takes and carries 70% of take-off weight usually, to revive 33 is example, fully loaded is 33 tons, and present actual take-off weight has only 27 tons, does not take off at full capacity, lose 6 tons load, it is said, adopt any ejector to help to allow Soviet Union 33 on the sliding formula runway that jumps, fully loaded takeoff, fully loaded takeoff and just mean and improved fighting capacity and strengthened cruising radius.The ripe at present ejector that is using has only the steam formula ejector of the U.S., and the U.S. is to Russian blockade on new techniques, and Russia does not make yet, even the U.S. does not also adapt to the camber line steam cylinder of the sliding formula takeoff runway that jumps.
People's deficiency that two kinds of ejection modes exist in actual application is, 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, can do carrier-borne aircraft if solved any concentrated process transformation of sliding the launching of formula aircraft carrier that jump, Russia has also lost practical significance to prohibiting selling of China, so China's a kind of better carrier-based aircraft ejector of certain design is realized the aircraft carrier development dream of China.
Summary of the invention
Technical assignment of the present invention is to overcome above-mentioned shortcoming, provide a kind of simple in structure, reasonable in design, volume is little, easy to use, safely can adapt to the aircraft carrier ejector that various machines are made carrier-borne aircraft.
Technical scheme of the present invention realizes in the following manner: its structure is by the aircraft carrier cunning formula flight deck that jumps, the shuttle extension pulley, the extension pulley cableway, main traction winch, secondary traction winch and ejection sequence controller are formed, wherein, the extension pulley cableway is arranged on the jump centre of formula takeoff runway or horizontal takeoff runway of aircraft carrier cunning, the shuttle extension pulley is arranged among the extension pulley cableway, main traction winch and secondary traction winch are arranged among the cabin of takeoff runway below, and the cable wire of main traction winch and secondary traction winch is connected with the rear and front end of shuttle extension pulley respectively;
Leading bow I coaster cableway is made up of upper cover plate, chute, cable wire protection angle bar and Hanging roller, the top of chute is provided with flange, the bottom of flange and flight deck is fixed together, the I{j of upper cover plate asks to be provided with and cracks, both sides are parallel with flight deck and be fixed together with the flange on chute top, cable wire protection angle bar is arranged on the bottom of cracking, with crack parallel, Hanging roller is arranged on the bottom of chute, the two ends of chute are respectively arranged with electromagnetism or opto-electronic pickup and tachogenerator, for the ejection sequence controller provides switch controlling signal;
The shuttle extension pulley is by vehicle frame, roller, main pull line equalizer pulley, secondary pull line equalizer pulley and shuttle connecting panel are formed, main pull line equalizer pulley and secondary pull line equalizer pulley are fixed on the bottom of vehicle frame by head pulley axle bed and auxiliary pulley axle bed, vehicle frame is the I shape of horizontal positioned, by-level partly is the car crossbeam, the both sides vertical component is the roller adapter plate, roller divides on the adapter plate that two rows are arranged on the vehicle frame both sides, roll and join in two row's rollers on both sides, adapter plate top and upper cover plate bottom, roll and join in two row's rollers on both sides, adapter plate bottom and chute bottom, the shuttle connecting panel vertically is arranged on the centre of crossbeam, cracking upwards to expose with shuttle and be connected in the middle of the upper cover plate passed on its top, shuttle is connected with aircraft nose wheel, the bottom that is positioned at crossbeam is provided with main cable equalizer pulley and secondary pull line equalizer pulley, the residence cable wire pulley of neighing is connected with secondary traction winch with main traction winch with secondary pull line by main pull line respectively with secondary pull line equalizer pulley, main pull line and secondary pull line are walked among chute and Hanging roller, be connected with reverse pulley at the chute two ends, oppositely the main pull line after and secondary pull line are through among the Hanging roller of chute bottom:
Main traction winch, be by support, engine, power-transfer clutch, flywheel, transmission shaft, winch roller and brake gear are formed, wherein the winch roller is arranged on the transmission shaft, the transmission shaft two ends are fixed by bearing seat and support, wherein an end of transmission shaft passes bearing seat and is connected with power-transfer clutch, power-transfer clutch is connected with the flywheel of powered maneuver power output shaft end, the two ends of winch roller are provided with brake gear, engine and winch roller adopt the opposed mode of two covers to be arranged on the support, in the middle of two cover winch rollers are arranged on, engine is arranged on the both sides of support, use a main pull line on two winch rollers, the termination of main pull line and winch roller axle are fixed, and the centre of main pull line is connected with main pull line equalizer pulley on the shuttle extension pulley;
Secondary traction winch, be by auxiliary engine bed, electrical motor, side clutch, counter drive shaft, secondary winch roller and auxiliary brake device are formed, the counter drive shaft two ends of wherein secondary winch roller are fixed by countershaft bearing and auxiliary engine bed, the two ends of counter drive shaft are passed the countershaft bearing and are connected with side clutch, side clutch is connected with the motor power output shaft, the two ends of secondary winch roller are provided with the auxiliary brake device, electrical motor and secondary winch roller adopt the opposed mode of two covers to be arranged on the auxiliary engine bed, in the middle of the secondary winch roller of two covers is arranged on, electrical motor is arranged on the both sides of auxiliary engine bed, use a secondary pull line on two secondary winch rollers, termination and two secondary winch roller axles of secondary pull line are fixed, and the centre of secondary pull line is connected with secondary pull line equalizer pulley on the shuttle extension pulley.
The engine that main traction winch uses is meant adjustable frequency motor, diesel engine, spark ignition engine, steam turbine, turbo-machine and HM Hydraulic Motor.
The two ends master's pull line that is positioned at chute comes and goes the laser velocimeter, the opto-electronic pickup that are provided with on the passage of process and is connected with ejection controller by data line.
Main traction winch all is connected with ejection controller by data line with brake gear, power-transfer clutch and switch governor device on the good fortune traction winch.
The catapult technique of the sliding formula aircraft carrier ejector that jumps, be to be equipped with flywheel energy storage as propulsion source with engine, by the flywheel amount of holding, drawing under the winding reducing effect of cheese under the control of ejection sequence controller and at power-transfer clutch and pull line, the energy of flywheel and engine is gathered on 95 meters-130 meters takeoff runway to all kinds of carrier-borne aircrafts provide basic takeoff speed, and it is as follows to realize that step is specifically launched in the catapult-assisted take-off of all kinds of carrier-borne aircrafts on the sliding formula aircraft carrier takeoff runway that jumps:
1) by the setting of ejector controller take off kind, load and the takeoff speed of aircraft, ejector controller control engine drives flywheel and rotates synchronously, when the engine rotating speed reach set rotating speed after, stand-by;
2) the shuttle extension pulley is positioned at the starting point of takeoff runway, and the winch roller of main traction winch and secondary traction winch locks by drg, is connected with the aircraft nose wheel that is parked in the runway starting point with shuttle connecting panel bonded assembly shuttle, and carrier-borne aircraft is ready;
3) after the dispatcher assigns takeoff order, the flywheel that is connected with the powered maneuver power output shaft that the ejection sequence controller is controlled main traction winch passes through the flywheel clutch adhesive, drg discharges simultaneously, the power-transfer clutch and the drg of secondary traction winch all discharge, the engine of main traction winch drives the winch roller at full speed and rotates, cable wire extension pulley quick slip in chute when twining on the winch roller axle drives shuttle traction carrier-borne aircraft simultaneously and quickens to slide on takeoff runway, because the winch roller is at the rotation initial stage, cable wire is that minor diameter twines in the winding of winch roller axial region, haulage speed is slow, bashful tractive force is big, low velocity fire tractive force takeoff condition when just in time meeting the carrier-borne aircraft rate of onset and be zero, on winch roller axle, twine the increase of the number of turns along with cable wire, cooling diameter is increasing, thereby haulage speed is more and more faster, when carrier-borne aircraft arrives the takeoff runway terminal point, the diameter maximum that cable wire twines on winch roller axle, the speed of wrap of cable wire is exactly the basic takeoff speed of carrier-borne aircraft, at this moment shuttle separates with aircraft nose wheel, the carrier-borne aircraft lift-off;
4) when moment that shuttle separates with carrier-borne aircraft, the sensor-triggered of takeoff runway destination county, the power-transfer clutch that the ejection sequence controller is controlled on main traction winch and the secondary traction winch winch roller all discharges, drg on main traction winch and the secondary traction winch winch roller is braked simultaneously, and the shuttle extension pulley stops at the takeoff runway terminal point; Engine on the main traction winch is pressed tickover, and the electrical motor on the secondary traction winch remains in operation;
5) the ejection sequence controller is controlled main traction winch and the secondary drg that leads on the bow 1 winch winch roller discharges simultaneously, the power-transfer clutch of main traction winch winch roller discharges, power-transfer clutch adhesive on the secondary traction winch winch roller. secondary traction winch traction shuttle extension pulley returns the takeoff runway starting point, the ejection sequence controller is controlled the drg of winch roller on main traction winch and the secondary traction winch and is braked simultaneously, and shuttle stops at the takeoff runway starting point and awaits orders.
Excellent effect of the present invention is, volume is little, few with the space, takeoff runway is not subjected to distance limit, not limited by radian, not only can use on the sliding formula aircraft carrier that jumps, also can use on the common aircraft carrier in plane, 98.5 meters of why limiting of steam catapult mainly are the restrictions of processing length of cylinder of cracking.Chute length of the present invention is unrestricted, and sinuousness is unrestricted, thus can be that the sliding formula flight deck that jumps is arranged, more can the adaptation level flight deck.The range of choice of engine is wideer, can use any power on the aircraft carrier, comprise steam, electric power or combustion engine, ejector of the present invention is compared with steam catapult, excellent effect is, various high-power power machines have been prior aries, provide at engine under the situation of sufficient power, in the distance of takeoff runway 90-130 rice, aircraft is realized the even acceleration of 0-75 meter per second, promptly in the distance of 90-130 rice, aircraft is accelerated to the takeoff speed of 75-85 meter per second, this accelerated mode is by accelerating slowly, and the aviator adapts to and can not cause the aviator to go into a coma moment soon, and launching as steam is from fast to slow, reach 75 meter per seconds once starting to walk, reach at a high speed and can cause the aviator to go into a coma moment, when cylinder runs to the cylinder terminal point, reduce because of vapor tension on the contrary suddenly, cause thrust to descend. the drawback that takeoff speed descends, describe that with Chinese Proverbs the aircraft that launches out is as " an arrow at the end of its flight--a spent force ".
Description of drawings:
Fig. 1 is the sliding use structural representation of formula aircraft carrier ejector on the sliding formula aircraft carrier that jumps that jump:
Fig. 2 is the integral structure scheme drawing of the sliding formula aircraft carrier ejector that jumps
Fig. 3 is shuttle extension pulley structural representation in chute;
Fig. 4 is the section structure scheme drawing of chute;
Fig. 5 is the structural representation of looking up of shuttle extension pulley;
Fig. 6 is the plan structure scheme drawing of shuttle extension pulley;
Fig. 7 is the main TV structure scheme drawing of shuttle extension pulley.
Description of reference numerals: flight deck 1, upper cover plate 2, cable wire protection angle bar 3, chute 4, Hanging roller 5, main pull line 6, main pull line equalizer pulley 7, head pulley axle bed 8, vehicle frame 9, secondary pull line equalizer pulley 10, auxiliary pulley axle bed 11, roller 12, secondary pull line 13, shuttle connecting panel 14, engine 15 power-transfer clutchs 16, brake gear 17, winch roller 18, bearing seat 19, support 20, electrical motor 21, side clutch 22, secondary winch roller 23, secondary winch pull line 24, auxiliary brake device 25, tachogenerator 26, trigger switch 27, ejection controller 28, flywheel 29, transmission shaft 30, auxiliary engine bed 31, counter drive shaft 32, countershaft bearing 33.
The specific embodiment
With reference to accompanying drawing sliding formula aircraft carrier ejector and the catapult technique of jumping done following detailed explanation.
The cunning of the present invention formula aircraft carrier ejector that jumps, be by the aircraft carrier cunning formula flight deck that jumps, the shuttle extension pulley, the extension pulley cableway, main traction winch, secondary traction winch and ejection sequence controller are formed, wherein, the extension pulley cableway is arranged on the jump centre of formula takeoff runway or horizontal takeoff runway of aircraft carrier cunning, the shuttle extension pulley is arranged among the extension pulley cableway, main traction winch and secondary traction winch are arranged among the cabin of takeoff runway below, and the cable wire of main traction winch and secondary traction winch is connected with the rear and front end of shuttle extension pulley respectively;
The extension pulley cableway is by upper cover plate 2, chute 4, cable wire protection angle bar 3 and Hanging roller 5 are formed, the top of chute 4 is provided with flange, the bottom of flange and flight deck 1 is fixed together, the centre of upper cover plate 2 is provided with cracks, both sides and flight deck 1 are parallel and be fixed together with the flange on chute 4 tops, cable wire protection angle bar 3 is arranged on the bottom of cracking, with crack parallel, Hanging roller 5 is arranged on the bottom of chute 4, the two ends of chute 4 are respectively arranged with electromagnetism or opto-electronic pickup 27 and tachogenerator 26, for ejection sequence controller 28 provides switch controlling signal;
The shuttle extension pulley is by vehicle frame 9, roller 12, main pull line equalizer pulley 7, secondary pull line equalizer pulley 10 and shuttle connecting panel 14 are formed, main pull line equalizer pulley 7 and secondary pull line equalizer pulley 10 are fixed on the bottom of vehicle frame 9 by head pulley axle bed 8 and auxiliary pulley axle bed 11, vehicle frame 9 is the I shape of horizontal positioned, by-level partly is the car crossbeam, the both sides vertical component is the roller adapter plate, 12 fens two rows of roller are arranged on the adapter plate on vehicle frame 9 both sides, two row's rollers 12 on both sides, adapter plate top roll with upper cover plate 2 bottoms and join, two row's rollers 12 on both sides, adapter plate bottom roll with chute 9 bottoms and join, shuttle connecting panel 14 vertically is arranged on the centre of cross member of frame, cracking upwards to expose with shuttle and be connected in the middle of the upper cover plate 2 passed on its top, shuttle is connected with aircraft nose wheel, the bottom that is positioned at the vehicle frame crossbeam is not equipped with main cable equalizer pulley 7 and secondary pull line equalizer pulley 10, main cable equalizer pulley 7 is connected with secondary traction winch with main traction winch with secondary pull line 13 by main pull line 6 respectively with secondary pull line equalizer pulley 10, main pull line 6 and secondary pull line 13 are walked among chute 4 and Hanging roller 5, are connected with reverse pulley 25 at chute 4 two ends;
Main traction winch, be by support 20, engine 1t5, power-transfer clutch 16, flywheel 29, transmission shaft 30, winch roller 18 and brake gear 17 are formed, wherein winch roller 18 is arranged on the transmission shaft 30, transmission shaft 30 two ends are fixing with support 20 by bearing seat 19, wherein an end of transmission shaft 30 passes bearing seat 19 and is connected with power-transfer clutch 16, power-transfer clutch 16 is connected with the flywheel 29 of engine 15 takeoff output axle heads, the two ends of winch roller 18 are provided with brake gear 17, engine 15 and winch roller 18 adopt the opposed mode of two covers to be arranged on the support 20, in the middle of two cover winch rollers 18 are arranged on, engine 15 is arranged on the both sides of support 20, use a main pull line 6 on two winch rollers 18, the termination of main pull line 6 and winch roller axle are fixed, and the centre of main pull line 6 is connected with main pull line equalizer pulley 7 on the shuttle extension pulley;
Secondary traction winch, be by auxiliary engine bed 31, electrical motor 21, side clutch 22, counter drive shaft 32, secondary winch roller 23 and auxiliary brake device 25 are formed, counter drive shaft 32 two ends of wherein secondary winch roller 23 are fixing with auxiliary engine bed 31 by countershaft bearing 33, the two ends of counter drive shaft 32 are passed countershaft bearing 33 and are connected with side clutch 22, side clutch 22 is connected with the motor power output shaft, the two ends of secondary winch roller 23 are provided with the pair device 25 first of stopping, electrical motor and secondary winch roller 23 adopt the opposed mode of two covers to be arranged on the auxiliary engine bed 31, in the middle of the secondary winch roller 23 of two covers is arranged on, electrical motor is arranged on the both sides of auxiliary engine bed 31, use a secondary pull line 24 on two secondary winch rollers 23, termination and two secondary winch roller axles of secondary pull line 24 are fixed, and the centre of secondary pull line 24 is connected with secondary pull line equalizer pulley 10 on the shuttle extension pulley.
The engine 15 that main traction winch uses is meant adjustable frequency motor, diesel engine, spark ignition engine, steam turbine, turbo-machine and HM Hydraulic Motor.
The two ends master's pull line that is positioned at chute comes and goes the laser velocimeter 26, the opto-electronic pickup 27 that are provided with on the passage of process and is connected with ejection controller 28 by data line.
Main traction winch all is connected with ejection controller by data line with brake gear, power-transfer clutch and switch governor device on the good fortune traction winch.
The catapult technique of the sliding formula aircraft carrier ejector that jumps, be to be equipped with flywheel energy storage as propulsion source with engine, by the flywheel amount of holding, drawing under the winding reducing effect of cheese under the control of ejection sequence controller and at power-transfer clutch and pull line, the energy of flywheel and engine is gathered on 95 meters-130 meters takeoff runway to all kinds of carrier-borne aircrafts provide 75 meter per seconds basic takeoff speed, realize the catapult-assisted take-off of all kinds of carrier-borne aircrafts on the sliding formula aircraft carrier takeoff runway that jumps;
It is as follows specifically to launch step:
1) by the setting of ejector controller take off kind, load and the takeoff speed of aircraft, ejector controller control engine drives flywheel and rotates synchronously, when the engine rotating speed reach set rotating speed after, stand-by;
2) the shuttle extension pulley is positioned at the starting point of takeoff runway, and the winch roller of main traction winch and secondary traction winch locks by drg, is connected with the aircraft nose wheel that is parked in the runway starting point with shuttle connecting panel bonded assembly shuttle, and carrier-borne aircraft is ready;
3) after the dispatcher assigns takeoff order, the flywheel that is connected with the powered maneuver power output shaft that the ejection sequence controller is controlled main traction winch passes through the flywheel clutch adhesive, drg discharges simultaneously, the power-transfer clutch and the drg of secondary traction winch all discharge, the engine of main traction winch drives the winch roller at full speed and rotates, cable wire extension pulley quick slip in chute when twining on the winch roller axle drives shuttle traction carrier-borne aircraft simultaneously and quickens to slide on takeoff runway, because the winch roller is at the rotation initial stage, cable wire is that minor diameter twines in the winding of winch roller axial region, haulage speed is slow, but tractive force is big, low velocity fire tractive force takeoff condition when just in time meeting the carrier-borne aircraft rate of onset and be zero, on winch roller axle, twine the increase of the number of turns along with cable wire, cooling diameter is increasing, thereby haulage speed is more and more faster, when carrier-borne aircraft arrives the takeoff runway terminal point, the diameter maximum that cable wire twines on winch roller axle, the speed of wrap of cable wire is exactly the basic takeoff speed of carrier-borne aircraft, at this moment shuttle separates with aircraft nose wheel, the carrier-borne aircraft lift-off;
4) when moment that shuttle separates with carrier-borne aircraft, the sensor-triggered of takeoff runway destination county, the power-transfer clutch that the ejection sequence controller is controlled on main traction winch and the secondary traction winch all discharges, and drg is braked simultaneously, and the shuttle extension pulley stops at the takeoff runway terminal point:
5) drg controlled on main traction winch and the secondary traction winch of ejection sequence controller discharges simultaneously, the power-transfer clutch of main traction winch discharges, power-transfer clutch adhesive on the secondary traction winch, secondary traction winch traction shuttle extension pulley returns the takeoff runway starting point, the drg that the ejection sequence controller is controlled on main traction winch and the secondary traction winch is braked simultaneously, and shuttle stops at the takeoff runway starting point and awaits orders.
Embodiment
Control the liftoff moment takeoff speed of aircraft by the width of control winch roller and the cooling diameter of cable wire, computing formula is expressed from the next:
Carrier-borne aircraft must obtain 30m/s ' 2 on 100 meters runway acceleration/accel just can take off successfully, takes off speed and acceleration
It is as follows that the degree run duration is calculated formula:
V＝√(2aX)＝√(200×30)≈77.46m/s (1)
t＝√(2X/a)＝√(200/30)≈2.58s (2)
The length of the length=runway of cable wire, the length of cable wire=each layer rope length sum, the length of cable wire
L=(L1+L2+ ... LX)=length (3) of takeoff runway
The length computation formula of every layer of cable wire of winch roller:
Li＝3.14N(D+2dC) (4)
D is the diameter that is wrapped in winch roller axle,
N is the number of turns of every layer of cable wire;
The diameter of Di=winch roller axle;
The diameter of d=cable wire;
The number of plies of C=cable wire
The density that cable wire twines is ignored in length=100 of cable wire meter on the length of takeoff runway=winch roller, sets the diameter D axle of winch roller axle=0.3 meter; The diameter d of cable wire=0.02 meter; The number of turns N=2 of every layer of cable wire according to the length of formula (4) each layer cable wire is respectively:
The length of every layer of cable wire (rice) cumulative length (rice)
L1＝6.28(0.3+0.04*1)＝2.14 2.14
L2＝6.28(0.3+0.04*2)＝2.38 4.52
L3＝6.28(0.3+0.04*3)＝2.63 7.14
L4＝6.28(0.3+0.04*4)＝2.9 10.05
L5＝6.28(0.3+0.04*5)＝3.14 13.18
L6＝6.28(0.3+0.04*6)＝3.39 16.57
L7＝6.28(0.3+0.04*7)：3.64 20.21
L8＝6.28(0.3+0.04*8)＝3.89 24.10
L9＝6.28(0.3+0.04*9)＝4.14 28.24
LLO＝6.28(0.3+0.04*10)＝4.39 32.63
L11＝6.28(0.3+0.04*11)＝4.64 37.27
L12＝6.28(0.3+0.04*12)＝4.9 42.17
L13：6.28(0.3+0.04*13)＝5.15 47.32
L14＝6.28(0.3+0.04*14)＝5.4 52.57
L15＝6.28(0.3+0.04*15)＝5.65 58.37
Lt6＝6.28(0.3+0.04*16)＝5.9 64.27
L17＝6.28(0.3+0.04*17)＝6.15 70.42
L18＝6.28(0.3+0.04*18)＝6.4 76.82
L19：6.28(0.3+0.04*19)＝6.65 83.47
L20＝6.28(0.3+0.04*20)＝6.9 90.37
L21＝6.28(0.3+0.04*21)＝7.159 97.53
L22＝6.28(0.3+0.04*22)＝7.41 104.9
L23＝6.28(0.3+0.04*23)＝7.66 112.6
L24＝6.28(0.3+0.04*24)＝7.91 120.51
The length of the 22nd layer of cable wire is L=(LI+L2+ ... L21): 104.9 meters,
The length of the 24th layer of cable wire is L=(LI～L2+ ... L21): 120.51 meters,
Known aircraft quickens the departure time on 100 meters runways be 2.58 seconds, per second rope woolding 44/2.58 ≈ 17 circles, 17/2=8.53 layer/second, 2.58 second roller changes the 2.58*8.53=22 layer, cable wire is 105 meters at 22 layers cumulative length, if select for use diesel engine that power is provided, the standard revolving speed of diesel engine is 1500 rev/mins, the per second rotating speed is 25, is adjusted into 18 revolutions per seconds by speed change, can reach the takeoff speed of carrier-borne aircraft for the winch roller provides 18 revolutions per seconds rotating speed.
By aforementioned calculation as can be seen, the length of first second cable wire is 24.10 meters, the length of second second cable wire is 64.27 meters, quicken 40.17 meters, rope length was 120.51 meters in the 3rd second, and the acceleration between the 3rd second and second second is 56.24 meters, and 105 meters cable wires twine 44 circles altogether in the time of 2.58 seconds on roller, the very hommization of this kind accelerated mode can not cause damage to chaufeur and aircraft.The steel rope breaking strength of diameter 20mm is 67 tons, and the duplex type breaking strength is 134 tons, and the weight of hornet carrier-borne aircraft is 24 tons, selects for use the steel rope intensity of 20mm to satisfy.If satisfy early warning plane, launch the steel rope that can select the 30-40mm diameter for use.
When winch roller rotating speed one regularly, on roller, twine the increase of the number of plies by cable wire, for carrier-borne aircraft provides
Acceleration/accel and the takeoff speed of 77.46m/s.If diesel engine provides extra even acceleration by regulating throttle, the takeoff speed of carrier-borne aircraft can also improve 20-50%.
Under the certain situation of rotating speed, the diameter or the cable wire that suitably increase roller get the takeoff speed that diameter also increases carrier-borne aircraft.
Main traction winch adopts two configurations, is connected with extension pulley by pulley in the middle of the cable wire, can single engine during use, be used for launching of low speed shipboard early warning aircraft, and also can draw simultaneously by two-shipper, adapt to taking off of different carrier-borne aircrafts by controlling the engine rotating speed.
Be provided with micro controller system and memory device in the ejection controller, micro controller system belongs to industrial control technology, is known technology.
Use about flywheel can be used also and can not use according to actual conditions, depend on the engine selection, the selection of engine will be considered the size of aircraft carrier, if nuclear power source can consider to use steam engine or steam turbine, if medium-sized aircraft carrier then uses diesel engine or turbo-machine, various engines are mature technologys, have the range of choice of broad.Even select two high-power aero-engine for use, also little meeting takies much spaces, if the power of an aero-engine is the twice of carrier-borne aircraft driving engine, no matter carrier-borne aircraft of two aero-engine tractions with the power redundancy that has 1 times, is equipment manufacturing cost so, or use cost, all than calculating that steam catapult comes, technical risk is wanted little easy realization, and service life is also long than steam catapult.Because the whole sufficient modularizations of design of the present invention, no matter be processing and fabricating, install and use, it is all very simple and convenient still to save maintenance from damage.
Claims (5)
1. the sliding formula aircraft carrier ejector that jumps, it is characterized in that, comprise the aircraft carrier cunning formula flight deck that jumps, the shuttle extension pulley, the extension pulley cableway, main traction winch, secondary traction winch and ejection sequence controller, wherein, the extension pulley cableway is arranged on the jump centre of formula takeoff runway or horizontal takeoff runway of aircraft carrier cunning, the shuttle extension pulley is arranged among the extension pulley cableway, and main traction winch and secondary traction winch are arranged among the cabin of takeoff runway below, and the cable wire of main traction winch and secondary traction winch is connected with the rear and front end of shuttle extension pulley respectively;
The extension pulley cableway is made up of upper cover plate, chute, cable wire protection angle bar and Hanging roller, the top of chute is provided with flange, the bottom of flange and flight deck is fixed together, the centre of upper cover plate is provided with cracks, both sides are parallel with flight deck and be fixed together with the flange on chute top, cable wire protection angle bar is arranged on the bottom of cracking, with crack parallel, Hanging roller is arranged on the bottom of chute, the two ends of chute are respectively arranged with electromagnetism or opto-electronic pickup and tachogenerator, for the ejection sequence controller provides switch controlling signal;
The shuttle extension pulley is by vehicle frame, roller, main pull line equalizer pulley, secondary pull line equalizer pulley and shuttle connecting panel are formed, main pull line equalizer pulley and secondary pull line equalizer pulley are fixed on the bottom of vehicle frame by head pulley axle bed and auxiliary pulley axle bed, vehicle frame is the I shape of horizontal positioned, by-level partly is the car crossbeam, the both sides vertical component is the roller adapter plate, roller divides on the adapter plate that two rows are arranged on the vehicle frame both sides, roll and join in two row's rollers on both sides, adapter plate top and upper cover plate bottom, roll and join in two row's rollers on both sides, adapter plate bottom and chute bottom, the shuttle connecting panel vertically is arranged on the centre of crossbeam, cracking upwards to expose with shuttle and be connected in the middle of the upper cover plate passed on its top, shuttle is connected with aircraft nose wheel, the bottom that is positioned at crossbeam is provided with main cable equalizer pulley and secondary pull line equalizer pulley, the main cable equalizer pulley is connected with secondary traction winch with main traction winch with secondary pull line by main pull line respectively with secondary pull line equalizer pulley, main pull line and secondary pull line are walked among chute and Hanging roller, be connected with reverse pulley at the chute two ends, oppositely the main pull line after and secondary pull line are through among the Hanging roller of chute bottom;
Main traction winch, be by support, engine, power-transfer clutch, flywheel, transmission shaft, winch roller and brake gear are formed, wherein the winch roller is arranged on the transmission shaft, the transmission shaft two ends are fixed by bearing seat and support, wherein an end of transmission shaft passes bearing seat and is connected with power-transfer clutch, power-transfer clutch is connected with the flywheel of powered maneuver power output shaft end, the two ends of winch roller are provided with brake gear, engine and winch roller adopt the opposed mode of two covers to be arranged on the support, in the middle of two cover winch rollers are arranged on, engine is arranged on the both sides of support, use a main pull line on two winch rollers, the termination of main pull line and winch roller axle are fixed, and the centre of main pull line is connected with main pull line equalizer pulley on the shuttle extension pulley;
Secondary traction winch, be by auxiliary engine bed, electrical motor, side clutch, counter drive shaft, secondary winch roller and auxiliary brake device are formed, the counter drive shaft two ends of wherein secondary winch roller are fixed by countershaft bearing and auxiliary engine bed, the two ends of counter drive shaft are passed the countershaft bearing and are connected with side clutch, side clutch is connected with the motor power output shaft, the two ends of secondary winch roller are provided with the auxiliary brake device, electrical motor and secondary winch roller adopt the opposed mode of two covers to be arranged on the auxiliary engine bed, in the middle of the secondary winch roller of two covers is arranged on, electrical motor is arranged on the both sides of auxiliary engine bed, use a secondary pull line on two secondary winch rollers, termination and two secondary winch roller axles of secondary pull line are fixed, and the centre of secondary pull line is connected with secondary pull line equalizer pulley on the shuttle extension pulley.
2. according to the described cunning of the claim 1 formula aircraft carrier ejector that jumps, it is characterized in that the engine that main traction winch uses is meant adjustable frequency motor, diesel engine, spark ignition engine, steam turbine, turbo-machine and HM Hydraulic Motor.
3. according to the described cunning of the claim 1 formula aircraft carrier ejector that jumps, it is characterized in that the two ends master's pull line that is positioned at chute comes and goes the laser velocimeter, the opto-electronic pickup that are provided with on the passage of process and is connected with ejection controller by data line.
4. according to the described cunning of the claim 1 formula aircraft carrier ejector that jumps, it is characterized in that main traction winch all is connected with ejection controller by data line with brake gear, power-transfer clutch and switch governor device on the good fortune traction winch.
5. slide the catapult technique of the formula aircraft carrier ejector that jumps, it is characterized in that, be equipped with flywheel energy storage with engine as propulsion source, by the flywheel amount of holding, drawing under the winding reducing effect of cheese under the control of ejection sequence controller and at power-transfer clutch and pull line, the energy of flywheel and engine is gathered on 95 meters-130 meters takeoff runway to all kinds of carrier-borne aircrafts provide basic takeoff speed, realize the catapult-assisted take-off of all kinds of carrier-borne aircrafts on the sliding formula aircraft carrier takeoff runway that jumps; It is as follows specifically to launch step:
1) by the setting of ejector controller take off kind, load and the takeoff speed of aircraft, ejector controller control engine drives flywheel and rotates synchronously, when the engine rotating speed reach set rotating speed after, stand-by;
2) the shuttle extension pulley is positioned at the starting point of takeoff runway, and the winch roller of main traction winch and secondary traction winch locks by drg, is connected with the aircraft nose wheel that is parked in the runway starting point with shuttle connecting panel bonded assembly shuttle, and carrier-borne aircraft is ready;
3) after the dispatcher assigns takeoff order, the flywheel that is connected with the powered maneuver power output shaft that the ejection sequence controller is controlled main traction winch passes through the flywheel clutch adhesive, drg discharges simultaneously, the engine accelerated service, the power-transfer clutch and the drg of secondary traction winch all discharge, this moment, the engine of main traction winch drove the rotation of winch roller at full speed, cable wire extension pulley quick slip in chute when twining on the winch roller axle drives shuttle traction carrier-borne aircraft simultaneously and quickens to slide on takeoff runway, because the winch roller is at the rotation initial stage, cable wire is that minor diameter twines in the winding of winch roller axial region, haulage speed is slow, but tractive force is big, low velocity large traction takeoff condition when just in time meeting the carrier-borne aircraft rate of onset and be zero, on winch roller axle, twine the increase of the number of turns along with cable wire, cooling diameter is increasing, thereby haulage speed is more and more faster, when carrier-borne aircraft arrives the takeoff runway terminal point, the diameter maximum that cable wire twines on winch roller axle, the speed of wrap of cable wire is exactly the basic takeoff speed of carrier-borne aircraft, at this moment shuttle separates with aircraft nose wheel, the carrier-borne aircraft lift-off;
4) when moment that shuttle separates with carrier-borne aircraft, the sensor-triggered of takeoff runway destination county, the power-transfer clutch that the ejection sequence controller is controlled on main traction winch and the secondary traction winch winch roller all discharges, drg on main traction winch and the secondary traction winch winch roller is braked simultaneously, and the shuttle extension pulley stops at the takeoff runway terminal point; Engine on the main traction winch is pressed tickover, and the electrical motor on the secondary traction winch remains in operation;
5) drg controlled on main traction winch and the secondary traction winch winch roller of ejection sequence controller discharges simultaneously, the power-transfer clutch of main traction winch winch roller discharges, power-transfer clutch adhesive on the secondary traction winch winch roller, secondary traction winch traction shuttle extension pulley returns the takeoff runway starting point, the ejection sequence controller is controlled the drg of winch roller on main traction winch and the secondary traction winch and is braked simultaneously, and shuttle stops at the takeoff runway starting point and awaits orders.
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| Application Number | Priority Date | Filing Date | Title |
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| CN2010102851414A CN102120495A (en) | 2011-04-09 | 2011-04-09 | Ski jump carrier-based aircraft catapult and catapulting method thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2010102851414A CN102120495A (en) | 2011-04-09 | 2011-04-09 | Ski jump carrier-based aircraft catapult and catapulting method thereof |
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| CN102991687A (en) * | 2012-12-12 | 2013-03-27 | 魏伯卿 | Impeller ejector for carrier-based aircraft of aircraft carrier |
| CN103129745A (en) * | 2011-11-28 | 2013-06-05 | 丁陶生 | Method and device of whole course uniformly-accelerated mechanical traction high-speed take-off of shipboard aircraft |
| WO2014032295A1 (en) * | 2012-09-01 | 2014-03-06 | Zhao Tianshuo | Slope downward-sliding takeoff platform for carrier-based aircraft, application aircraft carrier and realization method |
| CN107023630A (en) * | 2016-02-01 | 2017-08-08 | 熵零技术逻辑工程院集团股份有限公司 | A kind of ejector |
| CN110589008A (en) * | 2018-06-12 | 2019-12-20 | 王善良 | Gas catapult |
| CN112829961A (en) * | 2021-02-19 | 2021-05-25 | 王运宏 | Aircraft carrier catapult |
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| WO2010113030A2 (en) * | 2009-03-31 | 2010-10-07 | Wang Lifeng | A carrier-borne aircraft takeoff/landing system and methods of using the same |
| CN102107737A (en) * | 2010-09-19 | 2011-06-29 | 朱惠芬 | Front-pull rear-push aircraft carrier ejector and ejection method |
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| WO2010113030A2 (en) * | 2009-03-31 | 2010-10-07 | Wang Lifeng | A carrier-borne aircraft takeoff/landing system and methods of using the same |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103129745A (en) * | 2011-11-28 | 2013-06-05 | 丁陶生 | Method and device of whole course uniformly-accelerated mechanical traction high-speed take-off of shipboard aircraft |
| CN103129745B (en) * | 2011-11-28 | 2016-08-03 | 丁陶生 | Carrier-borne aircraft omnidistance even acceleration mechanical traction high speed takeoff method and device |
| WO2014032295A1 (en) * | 2012-09-01 | 2014-03-06 | Zhao Tianshuo | Slope downward-sliding takeoff platform for carrier-based aircraft, application aircraft carrier and realization method |
| CN102991687A (en) * | 2012-12-12 | 2013-03-27 | 魏伯卿 | Impeller ejector for carrier-based aircraft of aircraft carrier |
| CN102991687B (en) * | 2012-12-12 | 2015-04-22 | 魏伯卿 | Impeller ejector for carrier-based aircraft of aircraft carrier |
| CN107023630A (en) * | 2016-02-01 | 2017-08-08 | 熵零技术逻辑工程院集团股份有限公司 | A kind of ejector |
| CN110589008A (en) * | 2018-06-12 | 2019-12-20 | 王善良 | Gas catapult |
| CN112829961A (en) * | 2021-02-19 | 2021-05-25 | 王运宏 | Aircraft carrier catapult |
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Application publication date: 20110713 |