CN102107737B - Front-pull rear-push aircraft carrier ejector and ejection method - Google Patents
Front-pull rear-push aircraft carrier ejector and ejection method Download PDFInfo
- Publication number
- CN102107737B CN102107737B CN 201010286055 CN201010286055A CN102107737B CN 102107737 B CN102107737 B CN 102107737B CN 201010286055 CN201010286055 CN 201010286055 CN 201010286055 A CN201010286055 A CN 201010286055A CN 102107737 B CN102107737 B CN 102107737B
- Authority
- CN
- China
- Prior art keywords
- main
- winch
- roller
- shuttle
- pull line
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Control Of Turbines (AREA)
Abstract
The invention provides a front-pull rear-push aircraft carrier ejector and an ejection method. The structure of the ejector consists of a power machine, a clutch, a flywheel, a transmission shaft, a traction winch and a reel-off winch, wherein the traction winch and the flywheel are arranged on the transmission shaft; the flywheel is fixed together with the transmission shaft; the traction winch is connected with the transmission shaft through a bearing; the flywheel cutch is arranged between the flywheel and the traction winch; the transmission shaft is fixed through a bearing bracket; and the end of the transmission shaft is connected with the power machine through a motor clutch. Compared with the prior art, the flywheel energy storage accelerating aircraft carrier ejector has the characteristics of reasonable design, simple structure, safety, reliability, small volume, high automation degree and the like, is convenient to use and easy to maintain, and has good popularization and usage value.
Description
Technical field
The present invention relates to a kind of military equipment or aircraft carrier ejector, specifically a kind of front-pull rear-push aircraft carrier ejector and catapult technique thereof.
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 and accelerates to take off by the cylinder frigid zone moving hauling hook pulling aircraft of living.The steam catapult equipment volume is huge, occupies than large space, and steam boiler must be arranged, consumed energy is large, and operating cost is high, and maintenance cost is high, consume in addition the fresh water amount large, 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 a large amount of energy, only the energy of ejector consumption accounts for 20% of whole aircraft carrier energy, and huge fresh water consumption is a problem of can not ignore; The manufacturing process very complex of steam catapult, only having at present the U.S., France and Britain to grasp has the technology of making steam catapult, the steam catapult of having grasped at present, its structure is that two parallel length are more than 90 meter, diameter is the cylinder that cracks of .457mm, also need 2 meters of supporting two huge diameters, length is 20 meters vapour storage tanks, and cumulative volume is 600 cubic meters approximately, and volume is so huge, usually use at nuclear aircraft carrier more than 90,000 tons, only have at present the U.S. that nuclear aircraft carrier is arranged.So-called steam catapult, actual is exactly a steam ejection big gun, report according to pertinent data, the aviator crosses the stupor that conference produces moment because of initial velocity when catapult-assisted take-off, aircraft needs automatic flight instrument automatically to control, wake up rear in pilot steering Deng the aviator, the power of steam ejection is from vapour storage tank, launch initiation pressure large, terminal pressure reduces, so be 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, thrust descends, takeoff speed descends, and describes the aircraft that launches out with Chinese Proverbs as " an arrow at the end of its flight--a spent force ", and therefore aircraft falls into the sea also is unrare thing.The steam catapult of at present U.S. army's use, large except volume, cost is high, high, maintenance and use life-span of power consumption also makes U.S. army feel more headache, according to the report steam catapult use 500 times will overhaul, the cylinder life-span is 2000 times, namely launch 2000 sorties, cylinder will be changed.So new ejector alternative is also being sought by U.S. army, good result is not also arranged at present.
The time sliding formula takeoff runway that jumps that uses on the Russian Aircraft Carrier, be that aircraft leans on and self accelerates 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 the 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 as example, fully loaded is 33 tons, and present actual take-off weight only has 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 fully loaded takeoff at the sliding formula runway that jumps, fully loaded takeoff and just mean and improved fighting capacity and strengthened cruising radius.The ripe ejector that is using only has the steam type ejector of the U.S. at present, 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.
The maximum deficiency that two kinds of known 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 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, safe, can adapt to the aircraft carrier ejector that various machines are made carrier-borne aircraft what each tonnage used.
Technical scheme of the present invention realizes in the following manner: its structure is by the aircraft carrier cunning formula takeoff runway that jumps, the shuttle extension pulley, the extension pulley cableway, main traction winch, secondary traction winch, before push away cylinder and ejection sequence controller and form, 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, main traction winch be connected the cable wire of traction winch and be connected with the rear and front end of shuttle extension pulley respectively, frontly push away the bottom that cylinder is arranged on the starting point place extension pulley cableway that is positioned at takeoff runway;
The extension pulley cableway is comprised of upper cover plate, chute, the top of chute is provided with flange, the bottom of flange and takeoff runway is fixed together, the centre of upper cover plate is provided with cracks, on the both sides of cracking parallel with takeoff runway and be fixed together with the flange on chute top, middle being provided with down in bottom that is positioned at the forebody chute of takeoff runway cracked: lower cracking equates with the extension elongation that front pushes away steam cylinder piston, the two ends of chute are respectively arranged with stroke sensor and tachogenerator, for the ejection sequence controller provides switch controlling signal;
The shuttle extension pulley, mainly by vehicle frame, roller, main pull line equalizer pulley, secondary pull line equalizer pulley and shuttle connecting panel form, vehicle frame is the I shape of horizontal positioned, by-level partly is cross member of frame, main pull line equalizer pulley and secondary pull line equalizer pulley are fixed on the bottom of cross member of frame by head pulley axle bed and auxiliary pulley axle bed, vehicle frame both sides vertical component is the roller adapter plate, roller divides on the roller adapter plate that two rows are arranged on the vehicle frame both sides, roll and join in two row's rollers on both sides, roller adapter plate top and upper cover plate bottom, roll and join in two row's rollers on both sides, roller adapter plate bottom and chute bottom, the shuttle connecting panel vertically is arranged on the centre of cross member of frame, its top pass in the middle of the upper cover plate on crack upwards to expose with shuttle and be connected, shuttle is connected with aircraft nose wheel, main pull line equalizer pulley be connected the pull line equalizer pulley respectively by main pull line be connected pull line and main traction winch be connected traction winch and be connected, the centre, rear portion of shuttle extension pulley vehicle frame is provided with baffle plate;
Main traction winch, by main engine bed, main bearing seat, engine, master clutch, flywheel, main driving axle, main winch roller and main brake installation composition, wherein the main winch roller is arranged on the main driving axle, the main driving axle two ends are fixed by main bearing seat and main engine bed, one end of main driving axle passes main bearing seat and is connected with master clutch, master clutch is connected with the flywheel of powered maneuver power output shaft end, the two ends of main winch roller are provided with the main brake device, engine and main winch roller adopt the opposed mode of two covers to be arranged on the main engine bed, in the middle of two cover main winch rollers are arranged on, engine is arranged on the both sides of main engine bed, use a main pull line on two main winch rollers, the termination of main pull line and main winch roller shaft 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, by auxiliary engine bed, the countershaft bearing, electrical motor, side clutch, counter drive shaft, secondary winch roller and auxiliary brake form, wherein the counter drive shaft two ends of 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 auxiliary brake, 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 shafts 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 refers to adjustable frequency motor, diesel engine, spark ignition engine, steam turbine, turbo-machine and HM Hydraulic Motor.
It is opto-electronic pickup that the two ends master's pull line that is positioned at chute comes and goes the stroke sensor that arranges on the passage of process, and tachogenerator is laser velocimeter, and stroke sensor is connected data line and is connected with the ejection sequence controller with tachogenerator.
Main traction winch all is connected with the ejection sequence controller by data line with brake gear, power-transfer clutch on being connected traction winch.
Before push away cylinder and adopt twin-tub to be arranged side by side, the end of piston by connecting rod with push away hook and be connected, the front cylinder that pushes away is connected with vapour storage tank by pipeline, is provided with electromagnetic valve between the pipeline, vapour storage tank also is connected with steam boiler by pipeline.
Before to push away cylinder be air cylinder, be connected with storage tank by pipeline, storage tank is connected with Air compressor by pipeline.
The catapult technique of front-pull rear-push aircraft carrier ejector is as follows:
In 0 to 50 meter distance of aircraft carrier takeoff runway, provide acceleration/accel by front pushing away cylinder for carrier-borne aircraft, when front pushing away the cylinder startup, be equipped with flywheel energy storage with engine as propulsion source, by the flywheel amount of holding, leading under the winding reducing effect of drawing on the roller under the control of ejection sequence controller and at power-transfer clutch and main pull line, the energy aggregation of flywheel and engine is got up on the takeoff runway of 0-130 rice for carrier-borne aircraft provides basic takeoff speed, realize the catapult-assisted take-off of all kinds of carrier-borne aircrafts on the aircraft carrier takeoff runway; Specifically launch step as follows:
1) by the setting of ejection sequence controller take off kind, load and the takeoff speed of aircraft, ejection sequence controller control engine flywheel driven 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, the shuttle that is connected with the shuttle connecting panel is connected with the aircraft nose wheel that is parked in the runway starting point, the winch roller of main traction winch and secondary traction winch locks by drg, before push away the steam cylinder piston end push away hook and shuttle extension pulley rear portion overlap joint, carrier-borne aircraft is ready;
3) after the dispatcher assigns takeoff order, ejection sequence controller control electromagnetic valve is opened, vapour storage tank pushes away forward cylinder and injects high pressure steam, piston actuated shuttle extension pulley moves, the flywheel that is connected with the powered maneuver power output shaft of main traction winch is by the flywheel clutch adhesive simultaneously, the drg of main traction winch discharges, the engine accelerated service, 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, extension pulley quick sliding in chute when main pull line twines on the winch roller shaft, drive simultaneously shuttle and drawing carrier-borne aircraft accelerated slip on takeoff runway, because the winch roller is at the rotation initial stage, main pull line is that minor diameter twines in the winding of winch roller axial region, haulage speed is slow, but tractive force is large, low velocity large traction takeoff condition when just in time meeting the carrier-borne aircraft rate of onset and be zero, twine the increase of the number of turns at the winch roller shaft along with main pull line, cooling diameter is increasing, thereby haulage speed is more and more faster, when carrier-borne aircraft arrives the takeoff runway terminal point, main pull line is maximum at the diameter that the winch roller shaft twines, the speed of wrap of main pull line 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 stroke sensor of takeoff runway destination county triggers, 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, power-transfer clutch on the 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, before push away cylinder and oppositely fill vapour, piston is pulled back in the indentation cylinder barrel, 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, and is few with the space, and takeoff runway is not subjected to distance limit, not limited by radian, not only can use at the sliding formula aircraft carrier that jumps, and also can use by common aircraft carrier on the plane, is not subjected to the restriction of landing airdrome length.Chute length of the present invention is unrestricted, and sinuousness is unrestricted, thus can adapt to the sliding formula takeoff runway that jumps, more can the adaptation level takeoff runway.The range of choice of engine is wider, 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 mature technologys, in the situation that engine provides sufficient power, in the distance of takeoff runway 90-130 rice, aircraft is realized the even acceleration of 0-75 meter per second, and namely in the interior takeoff speed that aircraft is accelerated to the 75-85 meter per second of the distance of 90-130 rice, this accelerated mode is by accelerating slowly, the aviator adapts to soon, can not cause the aviator to go into a coma moment.
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 schematic diagram 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 schematic diagram of chute;
Fig. 5 is the structural representation of looking up of shuttle extension pulley;
Fig. 6 is the plan structure schematic diagram of shuttle extension pulley;
Fig. 7 is the main TV structure schematic diagram of shuttle extension pulley;
Fig. 8 is the local structure for amplifying schematic diagram of Fig. 1.
Description of reference numerals: takeoff runway 1, upper cover plate 2, cable wire protection angle bar 3, chute 4, baffle plate 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, master clutch 16, main brake device 17, main winch roller 18, main bearing seat 19, main engine bed 20, electrical motor 21, side clutch 22, secondary winch roller 23, secondary winch pull line 24, auxiliary brake 25, tachogenerator 26, stroke sensor 27, ejection sequence controller 28, flywheel 29, main driving axle 30, auxiliary engine bed 31, counter drive shaft 32, countershaft bearing 33, before push away cylinder 34, connecting rod 35, push away hook 36, support wheel 37, vapour storage tank 38, on crack 39, under crack 40.
The specific embodiment
With reference to accompanying drawing front-pull rear-push aircraft carrier ejector and catapult technique thereof are done following detailed explanation.
Such as accompanying drawing 1,2, shown in 8, front-pull rear-push aircraft carrier ejector of the present invention, its structure is by the aircraft carrier cunning formula takeoff runway that jumps, the shuttle extension pulley, the extension pulley cableway, main traction winch, secondary traction winch, before push away cylinder and ejection sequence controller and form, 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, main traction winch be connected the cable wire of traction winch and be connected with the rear and front end of shuttle extension pulley respectively, frontly push away the bottom that cylinder is arranged on the starting point place extension pulley cableway that is positioned at takeoff runway;
Such as accompanying drawing 3, shown in 4, the extension pulley cableway is by upper cover plate 2, chute 4, cable wire protection angle bar 3 forms, the top of chute 4 is provided with flange, the bottom of flange and takeoff runway 1 is fixed together, the centre of upper cover plate 2 is provided with cracks 39, on crack 39 both sides and takeoff runway 1 parallel and be fixed together with the flange on chute 4 tops, chute 4 bottoms that are positioned at takeoff runway 1 starting point have down cracks 40, cracking down 40 equates with the extension elongation that before pushes away cylinder 34 pistons, and the two ends of chute 4 are respectively arranged with stroke sensor 27 and tachogenerator 26 provides switch controlling signal for ejection sequence controller 28;
Such as accompanying drawing 5,6, shown in 7, 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 form, vehicle frame 9 is the I shape of horizontal positioned, by-level partly is cross member of frame, main pull line equalizer pulley 7 and secondary pull line equalizer pulley 10 are fixed on the bottom of cross member of frame by head pulley axle bed 8 and auxiliary pulley axle bed 11, vehicle frame both sides vertical component is the roller adapter plate, 12 minutes two rows of roller are arranged on the roller adapter plate on vehicle frame 9 both sides, two row's rollers 12 on both sides, roller adapter plate top roll with upper cover plate 2 bottoms and join, two row's rollers 12 on both sides, roller adapter plate bottom roll with chute 9 bottoms and join, be provided with baffle plate 5 in the middle of the rear portion of cross member of frame, shuttle connecting panel 14 vertically is arranged on the centre of cross member of frame, its top pass in the middle of the upper cover plate 2 on crack upwards to expose with shuttle and be connected, shuttle is connected with aircraft nose wheel, main cable equalizer pulley 7 be connected pull line equalizer pulley 10 respectively by main pull line 6 be connected pull line 13 and main traction winch be connected traction winch and be connected, main pull line 6 be connected pull line 13 and be connected with reverse pulley at chute 4 two ends;
Shown in accompanying drawing 1,2,3,8, before push away cylinder 34 piston nose section be connected with connecting rod 35, the other end of connecting rod 35 is connected with and pushes away hook 36, pushes away the rear end that pushes away cylinder 34 before hook 36 oppositely extends, be upward through the lower of chute 4 bottoms and crack 40, join with the baffle plate 5 at the rear portion of shuttle extension pulley; The both sides that push away hook 36 are provided with support wheel 37 and are connected with chute 4 rollings;
Before push away cylinder 34 and adopt twin-tubs to be arranged side by side, the end of piston by connecting rod 35 with push away hook 36 and be connected, the front cylinder 34 that pushes away is connected with vapour storage tank 38 by pipeline, is provided with electromagnetic valve between the pipeline, vapour storage tank 38 also is connected with steam boiler by pipeline.
Before push away cylinder 34 air cylinders and replace, air cylinder is connected with storage tank by pipeline, storage tank is connected with Air compressor by pipeline.
As shown in Figure 2, main traction winch, by main engine bed 20, main bearing seat 19, engine 15, master clutch 16, flywheel 29, main driving axle 30, main winch roller 18, main pull line 6 and main brake device 17 form, wherein main winch roller 18 is arranged on the main driving axle 30, main driving axle 30 two ends are fixing with main engine bed 20 by main bearing seat 19, wherein an end of main driving axle 30 passes main bearing seat 19 and is connected with master clutch 16, master clutch 16 is connected with the flywheel 29 of engine 15 power take-off shaft ends, the two ends of main winch roller 18 are provided with main brake device 17, engine 15 and main winch roller 18 adopt the opposed mode of two covers to be arranged on the main engine bed 20, in the middle of two cover main winch rollers 18 are arranged on, engine 15 is arranged on the both sides of main engine bed 20, use a main pull line 6 on two main winch rollers 18, the termination of main pull line 6 and main winch roller shaft 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, by auxiliary engine bed 31, countershaft bearing 33, electrical motor 21, side clutch 22, counter drive shaft 32, secondary winch roller letter 23, secondary pull line 24 and auxiliary brake 25 form, wherein counter drive shaft 32 two ends of 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 electrical motor 21 power take-off shafts, the two ends of secondary winch roller 23 are provided with auxiliary brake 25, 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 21 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 shafts 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 refers to adjustable frequency motor, diesel engine, spark ignition engine, steam turbine, turbo-machine and HM Hydraulic Motor.
The two ends master's pull line 6 that is positioned at chute comes and goes the stroke sensor 27 that arranges on the passage of process and is opto-electronic pickup, and tachogenerator 26 is laser velocimeter, and opto-electronic pickup is connected data line and is connected with the ejection sequence controller with laser velocimeter.
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 arrange on the passage of process and is connected with ejection sequence controller 28 by data line.
Main traction winch is connected with the ejection sequence controller by data line with brake gear, the power-transfer clutch of being connected on the traction winch.
In 0 to 50 meter distance of aircraft carrier takeoff runway, provide acceleration/accel by front pushing away cylinder for carrier-borne aircraft, when front pushing away the cylinder startup, be equipped with flywheel energy storage with engine as propulsion source, by the flywheel amount of holding, leading under the winding reducing effect of drawing on the roller under the control of ejection sequence controller and at power-transfer clutch and main pull line, the energy aggregation of flywheel and engine is got up on the takeoff runway of 0-130 rice for carrier-borne aircraft provides basic takeoff speed, realize the catapult-assisted take-off of all kinds of carrier-borne aircrafts on the aircraft carrier takeoff runway; Specifically launch step as follows:
1) by the setting of ejection sequence controller take off kind, load and the takeoff speed of aircraft, ejection sequence controller control engine flywheel driven 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, the shuttle that is connected with the shuttle connecting panel is connected with the aircraft nose wheel that is parked in the runway starting point, the winch roller of main traction winch and secondary traction winch locks by drg, before push away the steam cylinder piston end push away hook and shuttle extension pulley rear portion overlap joint, carrier-borne aircraft is ready;
3) after the dispatcher assigns takeoff order, ejection sequence controller control electromagnetic valve is opened, vapour storage tank pushes away forward cylinder and injects high pressure steam, piston actuated shuttle extension pulley moves, the flywheel that is connected with the powered maneuver power output shaft of main traction winch is by the flywheel clutch adhesive simultaneously, the drg of main traction winch discharges, the engine accelerated service, 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, extension pulley quick sliding in chute when main pull line twines on the winch roller shaft, drive simultaneously shuttle and drawing carrier-borne aircraft accelerated slip on takeoff runway, because the winch roller is at the rotation initial stage, main pull line is that minor diameter twines in the winding of winch roller axial region, haulage speed is slow, but tractive force is large, low velocity large traction takeoff condition when just in time meeting the carrier-borne aircraft rate of onset and be zero, twine the increase of the number of turns at the winch roller shaft along with main pull line, cooling diameter is increasing, thereby haulage speed is more and more faster, when carrier-borne aircraft arrives the takeoff runway terminal point, main pull line is maximum at the diameter that the winch roller shaft twines, the speed of wrap of main pull line 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 stroke sensor of takeoff runway destination county triggers, 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, power-transfer clutch on the 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, before push away cylinder and oppositely fill vapour, piston is pulled back in the indentation cylinder barrel, 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.
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 ˇ 2 on 100 meters runway acceleration/accel just can take off successfully, takes off speed and acceleration movement Time Calculation formula is as follows:
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 the winch roller shaft,
N is the number of turns of every layer of cable wire;
The diameter of Di=winch roller shaft;
The diameter of d=cable wire;
The number of plies of C=cable wire
The length of cable wire on the length of takeoff runway=winch roller=100 meters is ignored the density that cable wire twines, the diameter D axle of setting winch roller shaft=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
LL0＝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 1 12.6
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,
It is 2.58 seconds that known aircraft accelerates the departure time at 100 meters runways, per second rope woolding 44/2.58 ≈ 17 circles, 17/2=8.53 layer/second, 2.58 a second roller turns the 2.58*8.53=22 layer, cable wire is 105 meters at 22 layers cumulative length, if select 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.
Can find out by above-mentioned calculating, the length of first second cable wire is 24.10 meters, the length of second second cable wire is 64.27 meters, accelerate 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.Before push away the first half term that cylinder is arranged on takeoff runway, the speed of taking off is started from scratch, the kinetic energy that need to take off is large, thereby provide initial velocity with before pushing away cylinder, and aircraft rises when going to the second half, and engine has been realized rotating at full speed, add the self power of boarding a plane, the takeoff speed that aircraft is easy to accelerate.When one timing of winch roller rotating speed, twine the increase of the number of plies at roller by cable wire, the takeoff speed of acceleration/accel and the 77.46m/s of 30m/s ˇ 2 is provided for carrier-borne aircraft.If diesel engine provides extra even acceleration by regulating throttle, the takeoff speed of carrier-borne aircraft can also improve 20-50%.
In the situation that rotating speed is certain, 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, for launching of low speed shipboard early warning aircraft, also can draw simultaneously by two-shipper, and 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.
About front pushing away the processing of cylinder, cylinder length is selected 1/2nd of takeoff runway, be not only the difficulty of processing that reduces cylinder, mainly be to adopt closed cylinder, except energy savings, cylinder operation pressure can be improved, especially adopt air cylinder, under Same Efficieney, can reduce the diameter of cylinder, reduce the sky of hold facility and ask, improve the service life of equipment.The selection of engine will be considered the size of aircraft carrier, if nuclear power source can be considered 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 wider range of choice.Even select two high-power aero-engine, can not take much spaces yet, if the power of an aero-engine is the twice of carrier-borne aircraft driving engine, carrier-borne aircraft of two aero-engine tractions is redundant with the power that has 4 times so.The pistons end thrust Design if do not consider above factor, can be adopted in the space of the length that oppositely is connected main consideration cylinder with coaster of steam cylinder piston and minimizing clamping plate below.
No matter carrier-based aircraft ejector of the present invention is equipment manufacturing cost, or use cost, all wants the calculating of steam catapult of ratio open cylinder, and technical risk is wanted little easy realization, and service life, also ratio open cylinder steam catapult will be grown.Because design of the present invention all is modularization, no matter be processing and fabricating, install and use, still save maintenance from damage all very simple and convenient.China is badly in need of at present aircraft carrier and safeguards our 3,800,000 square kilometres ocean, wishes that state knows that office contacts with the Chinese military as early as possible, recommends technical scheme of the present invention or for their reference, realizes as early as possible the aircraft carrier dream of China to them.
Claims (7)
1. front-pull rear-push aircraft carrier ejector, it is characterized in that, comprise takeoff runway, the shuttle extension pulley, the extension pulley cableway, main traction winch, secondary traction winch, before push away cylinder 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, and 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, main traction winch be connected the cable wire of traction winch and be connected with the rear and front end of shuttle extension pulley respectively, frontly push away the bottom that cylinder is arranged on the starting point place extension pulley cableway that is positioned at takeoff runway;
The extension pulley cableway is comprised of upper cover plate, chute, the top of chute is provided with flange, the bottom of flange and takeoff runway is fixed together, the centre of upper cover plate is provided with cracks, on the both sides of cracking parallel with takeoff runway and be fixed together with the flange on chute top, middle being provided with down in bottom that is positioned at the forebody chute of takeoff runway cracked, crack down and equate with the extension elongation that front pushes away steam cylinder piston, the two ends of chute are respectively arranged with stroke sensor and tachogenerator, for the ejection sequence controller provides switch controlling signal;
The shuttle extension pulley, mainly by vehicle frame, roller, main pull line equalizer pulley, secondary pull line equalizer pulley and shuttle connecting panel form, vehicle frame is the I shape of horizontal positioned, by-level partly is cross member of frame, main pull line equalizer pulley and secondary pull line equalizer pulley are fixed on the bottom of cross member of frame by head pulley axle bed and auxiliary pulley axle bed, vehicle frame both sides vertical component is the roller adapter plate, roller divides on the roller adapter plate that two rows are arranged on the vehicle frame both sides, roll and join in two row's rollers on both sides, roller adapter plate top and upper cover plate bottom, roll and join in two row's rollers on both sides, roller adapter plate bottom and chute bottom, the shuttle connecting panel vertically is arranged on the centre of cross member of frame, its top pass in the middle of the upper cover plate on crack upwards to expose with shuttle and be connected, shuttle is connected with aircraft nose wheel, main pull line equalizer pulley be connected the pull line equalizer pulley respectively by main pull line be connected pull line and main traction winch be connected traction winch and be connected, the centre, rear portion of shuttle extension pulley vehicle frame is provided with baffle plate;
Before push away cylinder piston nose section be connected with connecting rod, the other end of connecting rod is connected with and pushes away hook, pushes away the rear end that pushes away cylinder before hook oppositely extends, and is upward through the lower of chute bottom
OpenSeam joins with the rear portion baffle plate of shuttle extension pulley vehicle frame; The both sides that push away hook are provided with support wheel and are connected with the chute rolling;
Main traction winch, by main engine bed, main bearing seat, engine, master clutch, flywheel, main driving axle, main winch roller and main brake installation composition, wherein the main winch roller is arranged on the main driving axle, the main driving axle two ends are fixed by main bearing seat and main engine bed, one end of main driving axle passes main bearing seat and is connected with master clutch, master clutch is connected with the flywheel of powered maneuver power output shaft end, the two ends of main winch roller are provided with the main brake device, engine and main winch roller adopt the opposed mode of two covers to be arranged on the main engine bed, in the middle of two cover main winch rollers are arranged on, engine is arranged on the both sides of main engine bed, use a main pull line on two main winch rollers, the termination of main pull line and main winch roller shaft 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, by auxiliary engine bed, the countershaft bearing, electrical motor, side clutch, counter drive shaft, secondary winch roller and auxiliary brake form, wherein the counter drive shaft two ends of 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 auxiliary brake, 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 shafts 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 aircraft carrier ejector claimed in claim 1, it is characterized in that the engine that main traction winch uses refers to adjustable frequency motor, diesel engine, spark ignition engine, steam turbine, turbo-machine and HM Hydraulic Motor.
3. according to aircraft carrier ejector claimed in claim 1, it is characterized in that, it is opto-electronic pickup that the two ends master's pull line that is positioned at chute comes and goes the stroke sensor that arranges on the passage of process, tachogenerator is laser velocimeter, and opto-electronic pickup is connected data line and is connected with the ejection sequence controller with laser velocimeter.
4. according to aircraft carrier ejector claimed in claim 1, it is characterized in that, main traction winch all is connected with the ejection sequence controller by data line with brake gear, the power-transfer clutch of being connected on the traction winch.
5. according to aircraft carrier ejector claimed in claim 1, it is characterized in that, before push away cylinder and adopt twin-tub to be arranged side by side, the end of piston by connecting rod with push away hook and be connected, before push away cylinder and be connected with vapour storage tank by pipeline, be provided with electromagnetic valve between the pipeline, vapour storage tank also is connected with steam boiler by pipeline.
6. according to aircraft carrier ejector claimed in claim 1, it is characterized in that, the front cylinder that pushes away is air cylinder, is connected with storage tank by pipeline, and storage tank is connected with Air compressor by pipeline.
7. the catapult technique of front-pull rear-push aircraft carrier ejector, it is characterized in that, in 0 to 50 meter distance of aircraft carrier takeoff runway, provide acceleration/accel by front pushing away cylinder for carrier-borne aircraft, when front pushing away the cylinder startup, be equipped with flywheel energy storage with engine as propulsion source, by the flywheel amount of holding, under the control of ejection sequence controller and at power-transfer clutch and main pull line under the winding reducing effect on the main winch roller, the energy aggregation of flywheel and engine is got up on the takeoff runway of 0-130 rice for carrier-borne aircraft provides basic takeoff speed, realize the catapult-assisted take-off of all kinds of carrier-borne aircrafts on the aircraft carrier takeoff runway; Specifically launch step as follows:
1) by the setting of ejection sequence controller take off kind, load and the takeoff speed of aircraft, ejection sequence controller control engine flywheel driven 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, the shuttle that is connected with the shuttle connecting panel is connected with the aircraft nose wheel that is parked in the runway starting point, the winch roller of main traction winch and secondary traction winch locks by drg, before push away the hook that pushes away of steam cylinder piston end, with shuttle extension pulley rear portion overlap joint, carrier-borne aircraft is ready;
3) after the dispatcher assigns takeoff order, ejection sequence controller control electromagnetic valve is opened, vapour storage tank pushes away forward cylinder and injects high pressure steam, piston actuated shuttle extension pulley moves, the flywheel that is connected with the powered maneuver power output shaft of main traction winch is by the flywheel clutch adhesive simultaneously, the drg of main traction winch discharges, the engine accelerated service, 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, extension pulley quick sliding in chute when main pull line twines on the winch roller shaft, drive simultaneously shuttle and drawing carrier-borne aircraft accelerated slip on takeoff runway, because the winch roller is at the rotation initial stage, main pull line is that minor diameter twines in the winding of winch roller axial region, haulage speed is slow, but tractive force is large, low velocity large traction takeoff condition when just in time meeting the carrier-borne aircraft rate of onset and be zero, twine the increase of the number of turns at the winch roller shaft along with main pull line, cooling diameter is increasing, thereby haulage speed is more and more faster, when carrier-borne aircraft arrives the takeoff runway terminal point, main pull line is maximum at the diameter that the winch roller shaft twines, the speed of wrap of main pull line 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 stroke sensor of takeoff runway destination county triggers, 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, power-transfer clutch on the 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, before push away cylinder and oppositely fill vapour, piston is pulled back in the indentation cylinder barrel, 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010286055 CN102107737B (en) | 2010-09-19 | 2010-09-19 | Front-pull rear-push aircraft carrier ejector and ejection method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010286055 CN102107737B (en) | 2010-09-19 | 2010-09-19 | Front-pull rear-push aircraft carrier ejector and ejection method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102107737A CN102107737A (en) | 2011-06-29 |
| CN102107737B true CN102107737B (en) | 2013-03-27 |
Family
ID=44172048
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010286055 Active CN102107737B (en) | 2010-09-19 | 2010-09-19 | Front-pull rear-push aircraft carrier ejector and ejection method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102107737B (en) |
Families Citing this family (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102120495A (en) * | 2011-04-09 | 2011-07-13 | 朱惠芬 | Ski jump carrier-based aircraft catapult and catapulting method thereof |
| CN102862684A (en) * | 2011-07-05 | 2013-01-09 | 王长存 | Novel aircraft carrier flying-off deck |
| CN102951297B (en) * | 2011-08-19 | 2015-04-22 | 丁陶生 | Device for realizing high-speed take-off of shipboard aircraft by spring combination mechanical ejection |
| CN102910294A (en) * | 2012-07-17 | 2013-02-06 | 朱惠芬 | Coaxial bidirectional winding accelerated shipboard aircraft catapult |
| CN102910295A (en) * | 2012-07-17 | 2013-02-06 | 朱惠芬 | Two-way driving winding speedup type ship-borne aircraft catapult |
| CN102826233B (en) * | 2012-08-24 | 2015-02-25 | 朱惠芬 | Combined multipurpose aircraft carrier land-based catapult-assisted take-off training device |
| CN102874415B (en) * | 2012-09-28 | 2016-01-20 | 王洪才 | Explosive aircraft catapult on a kind of aircraft carrier |
| CN103332297B (en) * | 2013-07-02 | 2016-04-20 | 济南环太机电技术有限公司 | Random boosting work method is concentrated in a kind of belt carrier-borne aircraft booster system and dispersion accumulation of energy |
| CN105314123A (en) * | 2014-06-20 | 2016-02-10 | 徐延明 | Control valve of aircraft carrier ejector |
| CN104192315A (en) * | 2014-09-15 | 2014-12-10 | 罗国沛 | Novel technique for catapulting aircraft to take off by cannon catapult |
| CN106956783A (en) * | 2016-01-11 | 2017-07-18 | 熵零技术逻辑工程院集团股份有限公司 | A kind of catapult technique |
| CN109229411A (en) * | 2017-07-11 | 2019-01-18 | 余华阳 | Vehicle type carrier-borne aircraft catapult launcher |
| CN107554811A (en) * | 2017-09-13 | 2018-01-09 | 荆门创佳机械科技有限公司 | Aircraft carrier electromagnetic launch device with tilt function |
| CN107572004A (en) * | 2017-10-06 | 2018-01-12 | 李克强 | A kind of ejector of aircraft carrier shipboard aircraft |
| CN108583923A (en) * | 2017-11-29 | 2018-09-28 | 北京航天试验技术研究所 | A kind of high-strength light slide trolley |
| CN110498056A (en) * | 2018-05-18 | 2019-11-26 | 田春生 | Two one, column cylinder seal tape type steam catapults |
| CN110731255B (en) * | 2018-07-18 | 2022-10-04 | 刘化云 | Deep root fertilizing equipment for rice |
| CN109080845A (en) * | 2018-08-30 | 2018-12-25 | 安徽理工大学 | A kind of multistage electromagnetism acceleration ejection system |
| RU2712407C1 (en) * | 2019-04-10 | 2020-01-28 | Федеральное государственное унитарное предприятие "Крыловский государственный научный центр" | Accelerating device for takeoff of shipborne aircraft |
| CN113018881B (en) * | 2021-04-25 | 2022-04-29 | 航天创客（北京）科技有限公司 | Aerospace science popularization model self-adaptive ejection device |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2726533A1 (en) * | 1994-11-04 | 1996-05-10 | Giat Ind Sa | Aircraft or projectile launching ramp for ship etc. |
| CN2866334Y (en) * | 2005-06-17 | 2007-02-07 | 廖志明 | Efficient aircraft carrier projectile device |
| CN200960980Y (en) * | 2006-06-02 | 2007-10-17 | 珠海星宇模型实业有限公司 | Ejecting system applied to unmanned machine transmission system |
| CN201089521Y (en) * | 2007-08-10 | 2008-07-23 | 霍方华 | Aircraft carrier shipboard aircraft steam catapult |
| CN101804866A (en) * | 2010-02-20 | 2010-08-18 | 姜明 | Flywheel energy storage accelerating carrier-based aircraft ejector and ejection method |
-
2010
- 2010-09-19 CN CN 201010286055 patent/CN102107737B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2726533A1 (en) * | 1994-11-04 | 1996-05-10 | Giat Ind Sa | Aircraft or projectile launching ramp for ship etc. |
| CN2866334Y (en) * | 2005-06-17 | 2007-02-07 | 廖志明 | Efficient aircraft carrier projectile device |
| CN200960980Y (en) * | 2006-06-02 | 2007-10-17 | 珠海星宇模型实业有限公司 | Ejecting system applied to unmanned machine transmission system |
| CN201089521Y (en) * | 2007-08-10 | 2008-07-23 | 霍方华 | Aircraft carrier shipboard aircraft steam catapult |
| CN101804866A (en) * | 2010-02-20 | 2010-08-18 | 姜明 | Flywheel energy storage accelerating carrier-based aircraft ejector and ejection method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102107737A (en) | 2011-06-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102107737B (en) | Front-pull rear-push aircraft carrier ejector and ejection method | |
| CN101804866B (en) | Flywheel energy storage accelerating carrier-based aircraft ejector | |
| CN102120495A (en) | Ski jump carrier-based aircraft catapult and catapulting method thereof | |
| CN102198865A (en) | Steam catapult for carrier-borne aircraft and catapulting method thereof | |
| CN101244764B (en) | Cascade connection type hybrid power ejection propulsion vehicle for takeoff of airplane | |
| CN102015452B (en) | Ground-based device for aircraft takeoff, landing and run-off processes | |
| CN102826233B (en) | Combined multipurpose aircraft carrier land-based catapult-assisted take-off training device | |
| CN103183132B (en) | Launch by power source unit body and aircraft carrier combustion and steam ejector and catapult technique | |
| CN101513936A (en) | Taking off device and taking off method for carrier-based aircraft | |
| CN102152856A (en) | Large-thrust multiple acceleration type pneumatic ejector for carrier-based airplanes of airplane carrier | |
| CN102145750A (en) | Electric ejector serving as departure power assisting device for carrier aircraft | |
| CN103332297A (en) | Belt type carrier-based aircraft booster system and decentralized energy storage and concentrated random boosting working method | |
| CN104760706A (en) | Flywheel energy storage propelling device | |
| CN106864765A (en) | flywheel ejector | |
| CN201089521Y (en) | Aircraft carrier shipboard aircraft steam catapult | |
| CN101519124B (en) | Take-off device and take-off method for carrier-based aircraft of aircraft carrier | |
| CN102910294A (en) | Coaxial bidirectional winding accelerated shipboard aircraft catapult | |
| CN2855904Y (en) | Steam ejection means for aircraft carrier | |
| CN201385785Y (en) | Aircraft carrier launching device | |
| CN202244097U (en) | Steam ejector | |
| CN103183133B (en) | Ejector of aircraft carrier shipboard aircraft | |
| CN102862684A (en) | Novel aircraft carrier flying-off deck | |
| CN102910295A (en) | Two-way driving winding speedup type ship-borne aircraft catapult | |
| CN204264463U (en) | Vacuum power accumulating formula fixed wing aircraft launching catapult | |
| CN102849223A (en) | Novel spring catapult for aircraft carrier |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| ASS | Succession or assignment of patent right |
Owner name: JINAN HUANTAI ELECTROMECHANICAL TECHNOLOGY CO., LT Free format text: FORMER OWNER: ZHU HUIFEN Effective date: 20130207 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20130207 Address after: 701 room 2755, No. 250014, Sau Sau Road, Ji'nan hi tech Zone, Shandong, China Applicant after: Jinan Huantai Electromechanical Technology Co., Ltd. Address before: No. 80 Design Institute of chemical industry of Shandong province 250014 dormitory Lixia District of Ji'nan city Min Zi Qian Lu Applicant before: Zhu Huifen |
|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| ASS | Succession or assignment of patent right |
Owner name: QIDONG SANJIANG CONSTRUCTION MACHINERY CO., LTD. Free format text: FORMER OWNER: JINAN HUANTAI ELECTROMECHANICAL TECHNOLOGY CO., LTD. Effective date: 20140716 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| COR | Change of bibliographic data |
Free format text: CORRECT: ADDRESS; FROM: 250014 JINAN, SHANDONG PROVINCE TO: 226236 NANTONG, JIANGSU PROVINCE |
|
| TR01 | Transfer of patent right |
Effective date of registration: 20140716 Address after: 226236 Nanhai Road, Binhai Industrial Park, Nantong, Jiangsu, Qidong Patentee after: Qidong Sanjiang Construction Machinery Co., Ltd. Address before: 701 room 2755, No. 250014, Sau Sau Road, Ji'nan hi tech Zone, Shandong, China Patentee before: Jinan Huantai Electromechanical Technology Co., Ltd. |