CN102826233A - Combined multipurpose aircraft carrier land-based catapult-assisted take-off training device - Google Patents
Combined multipurpose aircraft carrier land-based catapult-assisted take-off training device Download PDFInfo
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- CN102826233A CN102826233A CN2012103024155A CN201210302415A CN102826233A CN 102826233 A CN102826233 A CN 102826233A CN 2012103024155 A CN2012103024155 A CN 2012103024155A CN 201210302415 A CN201210302415 A CN 201210302415A CN 102826233 A CN102826233 A CN 102826233A
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Abstract
The invention provides a combined multipurpose aircraft carrier land-based catapult-assisted take-off training device which structurally comprises an engine base, a hydraulic lifting device, a cantilever runway, an aircraft carrier and a catapult assembly. The engine base is arranged in a groove excavated in the ground, one end of the cantilever runway is connected with the engine base through a hinge shaft, the catapult assembly is arranged in the engine base, the upper end of the hydraulic lifting device is hinged with the bottom of the cantilever runway, and the lower end of the hydraulic lifting device is connected with the bottom of the groove. The combined multipurpose aircraft carrier land-based catapult-assisted take-off training device has the advantages that the device is simple in structure, high in automation degree, convenient to operate, long in service life and easy to maintain and is safe and reliable; the device is high in adaptability since building of a land-based take-off runway is omitted; and due to the fact that a main take-off runway of an existing airport is occupied, the device can be mounted and used in any airport squares, and accordingly has high adaptability and powerful combat readiness function.
Description
Technical field
The present invention relates to a kind of military equipment or the ejection training of aircraft carrier continental rise equipment, a kind of specifically composite and multi-purpose aircraft carrier continental rise catapult-assisted take-off trainer.
Background technology
At present, China has successfully reequiped a cunning that supplies the carrier-borne aircraft cunning to jump up and the fly formula aircraft carrier that jumps, and it is said the aircraft carrier of also having built two same types in Changxing Island; But because the sliding formula aircraft carrier that jumps can not be built large-scale early warning plane, antisubmarine plane and transport plane in, also have carrier-borne aircraft not fully loaded takeoff, determine its fight capability far away from the U.S.'s existing steam catapult aircraft carrier fight capability; Can't contend with the aircraft carrier of the U.S., so the aircraft carrier that development has ejector is the basic outlet of Chinese aircraft carrier at all; Though the Chinese military has built the training base of the sliding formula carrier-borne aircraft that jumps in 3-5 place in various places; Because thinking is not right, also be to waste military expenditure even build many again training bases, can not fundamentally solve the backward problem of Chinese aircraft carrier training; Because adopting the sliding formula of jumping takes off; Can not use fixed-wing formula antisubmarine plane, early warning plane and transport plane on the aircraft carrier, fight capability has only 30% of catapult-assisted take-off carrier-borne aircraft, at present owing to China does not train carrier-borne aircraft with the aircraft carrier of ejector at all; So the carrier-borne aircraft aviator of China launches the blank that flight training is the carrier-borne aircraft pilot training of China naval; For strong my naval, accelerate development land machine carrier-borne aircraft ejection training equipment, for my naval fast the large quantities of carrier-borne aircraft aviator of training be the task of top priority.
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, easy to use, safe; Can be applied to the continental rise airport is that carrier-borne aircraft provides the short distance catapult-assisted take-off, also can be transplanted to a kind of composite and multi-purpose aircraft carrier continental rise catapult-assisted take-off trainer that uses on the various aircraft carriers fast.
Technical scheme of the present invention realizes by following mode: comprise support, hydraulic lifting device, cantilever runway, carrier-borne aircraft, ejector assembly; Wherein, Support is arranged among the trough of ground excavation, and an end of cantilever runway is connected with support through twisted axis, and the ejector assembly is arranged among the outstanding support; The bottom-hinged of the upper end of hydraulic lifting device and cantilever runway, the lower end is connected with the trough bottom;
The cantilever runway be to process with U type channel-section steel; The flange of bending in the both sides, top of U type channel-section steel are provided with mutually is provided with two-layer carrying roller in the middle of the U type channel-section steel, and the top of upper strata carrying roller is provided with the grooved slide plate; Roll with the carrying roller two ends and be connected in grooved slide plate bottom; Grooved slide plate top is provided with the aircraft pallet, and the aircraft pallet is the T type, and the aircraft tray upper surface has the T type hole that matches with the undercarriage position; The detouchable undercarriage connects frame bottom and is connected with T type hole through the dovetail structure, and the two ends of cantilever runway are provided with leading sheave, start position sensor and final position sensor;
The ejector assembly; Comprise: frame, ejection controller, primary mover, main driving axle, pay transmission shaft, coupler, bearing seat, towing capstan, return capstan winch, machine leader base band, return the sheet base band; Wherein ejection controller, primary mover are fixed on the frame; The end that one end of machine leader base band is wrapped on the towing capstan axle, return the sheet base band is wrapped in and returns on the capsizing moment spindle; The other end of machine leader base band is through the leading sheave of cantilever runway bottom, through the carrying roller of cantilever runway bottom; Be connected fixingly again with grooved slide plate left end in the cantilever runway through the leading sheave of cantilever runway left part and upper strata carrying roller, the other end that returns the sheet base band is connected with grooved slide plate right-hand member in the cantilever runway through the leading sheave of cantilever runway right-hand member to be fixed;
Towing capstan and the both sides of returning capstan winch are respectively even power-transfer clutch and drg arranged; Towing capstan is arranged on the main driving axle through bearing; Returning capstan winch is arranged on pair transmission shaft through bearing; Main driving axle is fixed through bearing frame and frame respectively with pair transmission shaft two ends; One end of main driving axle is connected with primary mover through coupler, and the other end is provided with small belt pulley and is connected with the big belt pulley of paying the moving axis end through belt, and then an interlock pair transmission shaft rotates synchronously; All fix with the grooved slide plate bottom that is arranged in the cantilever runway owing to be wrapped in the machine leader base band on the towing capstan and be wrapped in the other end of returning the sheet base band of returning capstan winch, towing capstan comes and goes mobile on the cantilever runway with the aircraft pallet that the alternate rotation of returning capstan winch drives its top of grooved slide plate drive;
Carrier-borne aircraft continental rise catapult-assisted take-off training step is following:
1) primary mover starts; Primary mover is given main driving axle through coupler with transmission of power; Main driving axle drives the good fortune transmission shaft through big small belt pulley and rotates, this moment towing capstan with return capstan winch and receive the drg braking to keep static, the aircraft pallet is positioned at the starting point of taking off of cantilever runway; The machine leader base band that connects towing capstan and grooved slide plate all extends among the cantilever runway, and the sheet base band of returning that connects the grooved slide plate and return capstan winch all is wrapped in and returns on the capstan winch;
2) carrier-borne aircraft slides on the aircraft pallet, and the rear portion of three alighting gears is connected support and connects the location with alighting gear on the aircraft pallet, and aero-engine quickens to wait for the catapult-assisted take-off instruction;
3) control tower is assigned the instruction of taking off, and the ejector operator presses and launches button, and towing capstan discharges with the drg that returns on the capstan winch; Power-transfer clutch adhesive on the towing capstan, main driving axle drives towing capstan through power-transfer clutch and rotates, and the machine leader base band is twined on towing capstan fast; In the winding process of machine leader base band on the towing capstan axle, the speed of wrap of machine leader base band becomes acceleration with fast towing aircraft pallet and moves by accelerating slowly on the cantilever runway; Be in returning of free rotary state and return the sheet base band on the capstan winch,, will return the sheet base band fast and discharge along with moving of aircraft pallet; The winding process of dispose procedure and towing capstan is opposite; The cooling diameter of traction belt from big to small, rotating speed is by accelerating, with leading aircraft pallet quick travel on the cantilever runway slowly; Carrier-borne aircraft is implemented to launch towing, for carrier-borne aircraft provides the optimum training takeoff speed;
4) when the aircraft pallet moves to cantilever runway terminal point; Carrier-borne aircraft has reached the training takeoff speed; Depart, the aircraft pallet triggers end point sensor, and the power-transfer clutch that ejection controller is controlled on the towing capstan immediately discharges; Towing capstan is implemented braking with the drg adhesive of returning on the capstan winch simultaneously, and the aircraft pallet stops at cantilever runway terminal point; At this moment, the machine leader base band all is wrapped on the towing capstan, returns the sheet base band and extends among the cantilever runway;
5) towing capstan with return capstan winch braking after, drg discharges immediately, ejection controller is controlled the power-transfer clutch adhesive of returning on the capstan winch immediately; Pay transmission shaft and return the rotation of capstan winch dish through the power-transfer clutch driving, the sheet base band enforcement winding of returning that extends in the cantilever runway is regained, the aircraft pallet returns at random; At this moment, towing capstan is in free rotary state, and the machine leader base band that is wrapped on the towing capstan extends among the cantilever runway in the return course of aircraft pallet again; When aircraft pallet return to origin; The starting point sensor-triggered, the power-transfer clutch that returns on the capstan winch discharges, and towing capstan is braked with the drg that returns capstan winch simultaneously; The aircraft pallet is positioned on the starting point of taking off of cantilever runway, prepares next frame carrier-borne aircraft is implemented to launch.
When the cantilever runway is parallel to the ground, be used for dynamic heavy airplane catapult-assisted take-off, when the cantilever runway is kicked up by the lifting of hydraulic lifting device, be used for light-duty dynamic aircraft or unpowered glider launching.
Drg and power-transfer clutch are magnet stopper, magnetic clutch or hydraulic brake, hydraulic clutch or pneumatic braking device, pneumatic clutch.
Primary mover is a kind of in electrical motor, diesel engine, steam turbine, the fanjet.
Excellent effect of the present invention is:
1) design is super rationally, and the accelerated mode of ejector can find out that through speed time curve speed is by accelerating slowly; The even change quickens, if aircraft departure time on 100 meters runways is 2.5 seconds, the takeoff speed at first second end is no more than 30 meters; The takeoff speed at second second end can reach the takeoff speed requirement of 80 meter per seconds, so power utilization can reach more than 90%; Because ejector of the present invention is the ingenious pure theory of machines of having used, all data parameters all can design and calculate, and comprise speed, time, use power and mechanical strength; According to present state-of-art, comprise primary mover, electronic controller and traction belt, can both satisfy the requirement that ejector launches at present known various carrier-borne aircrafts; So using steam ejection mode and electromagnetic launch mode is not the optimal selection of Chinese aircraft carrier; Say that from cost steam catapult of the U.S. of known active service is 8,000 ten thousand dollars of prices at least, at least 26 hundred million dollars of electromagnetic launch devices; And ejector of the present invention also have more than is needed 5,000,000 Renminbi that reckon in every item, investment is far away from the remnant of above-mentioned two kinds of ejectors.
2) height hommization; Ejection process has slower initial velocity and the controlled end speed of taking off; Very hommization; The pilot ejection take-off process is fast to the overload reactive adaptation, can as traditional carrier-based aircraft ejector, not use constant ejection speed, the moment stupor that occurs when causing pilot ejection to take off.
3) volume is little, and is simple in structure, occupies little space; The cantilever landing airdrome length is unrestricted, not limited by radian, not only can on the continental rise airport, use; Also can on various aircraft carriers deck, use, the groove depth of cantilever runway on flight deck is no more than 30 centimeters, and width is no more than 50 centimeters; Sectional area is no more than 0.15 square meter, can save a large amount of usage spaces for aircraft carrier, and main frame takies the cabin area and is no more than 10 square meters; If the capstan winch diameter that uses is two meters, the base inner spatial altitude is 3 meters and gets final product.
4) the primary mover range of choice is wide; More than the horsepower input 2000KW, can make carrier-borne aircraft launching more than 60-100 rice obtain the above takeoff speed of 80 meter per seconds in the runway, so; Primary mover can use any power on the aircraft carrier, comprises steam engine, electrical motor or combustion engine.
5) operation realizes Based Intelligent Control, can realize that the aircraft pallet launches automatically and returns automatically, can adapt to the needs that launch that various carrier-borne aircrafts comprise unmanned plane through the wireless remote control operation.
Description of drawings:
Fig. 1 is a composite and multi-purpose aircraft carrier continental rise catapult-assisted take-off trainer master TV structure scheme drawing:
Fig. 2 is the plan structure scheme drawing of Fig. 1
Fig. 3 is the structural representation of cantilever runway when steeving;
Fig. 4 is the section structure scheme drawing of cantilever runway
Fig. 5 is the plan structure scheme drawing of ejector assembly;
Fig. 6 is the working state schematic representation of ejector assembly when preparing to launch;
Fig. 7 is the working state schematic representation after the ejector assembly launches;
Fig. 8 is that the cantilever runway is transplanted to the plan structure scheme drawing on the aircraft carrier deck;
Fig. 9 is that the cantilever runway is transplanted to the section structure scheme drawing on the aircraft carrier deck;
Figure 10 is that ejector of the present invention is taken off velocity curve.
Description of reference numerals: support 1; Hinge 2; Aircraft pallet 3; Trough 4; Hydraulic lifting device 5; Cantilever runway 6; Carrier-borne aircraft 7; Machine leader base band 8; Drg 9; Power-transfer clutch 10; Main driving axle 11; Small belt pulley 12; Towing capstan 13; Return capstan winch 14; Return sheet base band 15; Big belt pulley 16; Pay transmission shaft 17; Bearing seat 18; Frame 19. primary movers 20; Coupler 21; Leading sheave 22; Carrying roller 23; Undercarriage connects support 24; Play point sensor 25; End point sensor 26; Ejection controller 27; Grooved slide plate 28.
The specific embodiment
Detailed explanation below with reference to accompanying drawing composite and multi-purpose aircraft carrier continental rise catapult-assisted take-off trainer of the present invention being done.
Composite and multi-purpose aircraft carrier continental rise catapult-assisted take-off trainer of the present invention; Comprise support 1, hydraulic lifting device 5, cantilever runway 6, carrier-borne aircraft 7, ejector assembly, wherein, support 1 is arranged among the trough 4 of ground excavation; One end of cantilever runway 6 is connected with support 1 through twisted axis; The ejector assembly is arranged among the outstanding support 1, the bottom-hinged of the upper end of hydraulic lifting device 5 and cantilever runway 6, and the lower end is connected with trough 4 bottoms;
The ejector assembly; Comprise: frame 19, ejection controller 27, primary mover 20, main driving axle 11, pay transmission shaft 17, coupler 21, bearing seat 18, towing capstan 13, return capstan winch 14, machine leader base band 8, return sheet base band 15; Wherein ejection controller 27, primary mover 20 are fixed on the frame 19; One end of machine leader base band 8 is wrapped in 13 of towing capstans and goes up, returns ends of sheet base band 15 and be wrapped in and return on 14 on the capstan winch; The other end of machine leader base band 8 is through the leading sheave 22 of cantilever runway 6 bottoms, through the carrying roller 23 of cantilever runway 6 bottoms; Be connected fixingly again with grooved slide plate 28 left ends in the cantilever runway 6 through the leading sheave 22 of cantilever runway left part and upper strata carrying roller 23, the other end that returns sheet base band 15 is connected with grooved slide plate 28 right-hand members in the cantilever runway 6 through the leading sheave 22 of cantilever runway 6 right-hand members to be fixed;
Towing capstan 13 and the both sides of returning capstan winch 14 are respectively even power-transfer clutch 9 and drg 10 arranged; Towing capstan 13 is arranged on the main driving axle 11 through bearing; Returning capstan winch 14 is arranged on pair transmission shaft 17 through bearing; Main driving axle 11 is fixing with frame 19 through bearing frame 18 respectively with pair transmission shaft 17 two ends; One end of main driving axle 11 is connected with primary mover 20 through coupler 21; The other end is provided with small belt pulley 12 and is connected with the big belt pulley 16 of paying the moving axis end through belt; And then interlock pays a transmission shaft 17 and rotates synchronously and since be wrapped on the towing capstan 13 machine leader base band 8 be wrapped in the other end of returning the sheet base band of returning capstan winch 14 and all fix with grooved slide plate 28 bottoms that are arranged in the cantilever runway 6, towing capstan 13 is round mobile on cantilever runway 6 with the aircraft pallet 3 that the alternate rotation of returning capstan winch 14 drives grooved slide plate 28 its tops of drive;
Embodiment
Carrier-borne aircraft continental rise catapult-assisted take-off training step is following:
1) primary mover starts; Primary mover is given main driving axle through coupler with transmission of power; Main driving axle drives the good fortune transmission shaft through big small belt pulley and rotates, this moment towing capstan with return capstan winch and receive the drg braking to keep static, the aircraft pallet is positioned at the starting point of taking off of cantilever runway; The machine leader base band that connects towing capstan and grooved slide plate all extends among the cantilever runway, and the sheet base band of returning that connects the grooved slide plate and return capstan winch all is wrapped in and returns on the capstan winch;
2) carrier-borne aircraft slides on the aircraft pallet, and the rear portion of three alighting gears is connected support and connects the location with alighting gear on the aircraft pallet, and aero-engine quickens to wait for the catapult-assisted take-off instruction;
3) control tower is assigned the instruction of taking off, and the ejector operator presses and launches button, and towing capstan discharges with the drg that returns on the capstan winch; Power-transfer clutch adhesive on the towing capstan, main driving axle drives towing capstan through power-transfer clutch and rotates, and the machine leader base band is twined on towing capstan fast; In the winding process of machine leader base band on the towing capstan axle, the speed of wrap of machine leader base band becomes acceleration with fast towing aircraft pallet and moves by accelerating slowly on the cantilever runway; Be in returning of free rotary state and return the sheet base band on the capstan winch,, will return the sheet base band fast and discharge along with moving of aircraft pallet; The winding process of dispose procedure and towing capstan is opposite; The cooling diameter of traction belt from big to small, rotating speed is by accelerating, with leading aircraft pallet quick travel on the cantilever runway slowly; Carrier-borne aircraft is implemented to launch towing, for carrier-borne aircraft provides the optimum training takeoff speed;
4) when the aircraft pallet moves to cantilever runway terminal point; Carrier-borne aircraft has reached the training takeoff speed; Depart, the aircraft pallet triggers end point sensor, and the power-transfer clutch that ejection controller is controlled on the towing capstan immediately discharges; Towing capstan is implemented braking with the drg adhesive of returning on the capstan winch simultaneously, and the aircraft pallet stops at cantilever runway terminal point; At this moment, the machine leader base band all is wrapped on the towing capstan, returns the sheet base band and extends among the cantilever runway;
5) towing capstan with return capstan winch braking after, drg discharges immediately, ejection controller is controlled the power-transfer clutch adhesive of returning on the capstan winch immediately; Pay transmission shaft and return the rotation of capstan winch dish through the power-transfer clutch driving, the sheet base band enforcement winding of returning that extends in the cantilever runway is regained, the aircraft pallet returns at random; At this moment, towing capstan is in free rotary state, and the machine leader base band that is wrapped on the towing capstan extends among the cantilever runway in the return course of aircraft pallet again; When aircraft pallet return to origin; The starting point sensor-triggered, the power-transfer clutch that returns on the capstan winch discharges, and towing capstan is braked with the drg that returns capstan winch simultaneously; The aircraft pallet is positioned on the starting point of taking off of cantilever runway, prepares next frame carrier-borne aircraft is implemented to launch.
When the cantilever runway is parallel to the ground, be used for dynamic heavy airplane catapult-assisted take-off, when the cantilever runway is kicked up by the lifting of hydraulic lifting device, be used for light-duty dynamic aircraft or unpowered glider launching.
Drg and power-transfer clutch are magnet stopper, magnetic clutch or hydraulic brake, hydraulic clutch or pneumatic braking device, pneumatic clutch.Ejection controller is a general single chip.
Primary mover is a kind of in electrical motor, diesel engine, steam turbine, the fanjet.
Embodiment 1:
1) launches unpowered or during aviette, rise, be to face upward and penetrate shape through the end of hydraulic lifting device with the cantilever runway.
Launch dynamic or during heavy airplane, the cantilever runway is all fallen in the trough, the cantilever runway is parallel to the ground, and aircraft taxi is to the aircraft pallet, and ejection process is identical with embodiment 1.
Device of the present invention not only can use on the continental rise airport; Also can complete machine be transplanted on the aircraft carrier deck and use, when being transplanted on the aircraft carrier deck, directly utilize steel plate belowdecks cantilever runway lid; Only stay one to supply cracking of shuttle slip to get final product, shown in Fig. 8-9.
The length of cantilever runway is controlled between the 60-100 rice, and the quantity of hydraulic lifting device is set according to the cantilever landing airdrome length.
Ejector assembly design procedure is following:
Carrier-borne aircraft must obtain 30m/s on 100 meters runway
2Acceleration/accel just can take off, take off speed and acceleration movement Time Calculation formula is following:
V＝√(2aL)＝√(200×30)≈77.46m/s (1)
t＝√(2L/a)＝√(200/30)≈2.58s (2)
The length of the length L=runway of machine leader base band=100 meter, 100 meters long machine leader base band is wrapped on the capsizing moment spindle, each layer machine leader base band length L i sum=machine leader base band length L (i=1,2,3 ... N)
L=(L1+L2+ ... LX)=100 meter (3)
Be wrapped in the length computation formula of the every synusia base band length on the capsizing moment spindle:
Li＝3.14(D+2hn) (4)
D is the diameter of capsizing moment spindle,
The thickness of h=sheet base band length;
The number of plies of n=sheet base band
Calculate the winding number of plies n of sheet base band and the maximum gauge (D+2hn) of capstan winch through formula (4)
The density that cable wire twines is ignored in length=100 of the length of runway=be wrapped in cable wire on the capstan winch meter, sets the diameter D=0.3 rice of capsizing moment spindle; The thickness h of sheet base band=0.02 meter; Length according to each synusia base band of formula (4) Li=3.14 (D+2hn) is respectively:
The length of every layer of cable wire (rice) cumulative length (rice)
L1＝3.14(0.3+0.04*1)＝3.14*0.34＝1.07 1.07
L2＝3.14(0.3+0.04*2)＝3.14*0.38＝1.19 2.26
L3＝3.14(0.3+0.04*3)＝3.14*0.42＝1.3 3.56
L4＝3.14(0.3+0.04*4)＝3.14*0.46＝1.45 5.01
L5＝3.14(0.3+0.04*5)＝3.14*0.5＝1.57 6.58
L6＝3.14(0.3+0.04*6)＝3.14*0.54＝1.695 8.275
L7＝3.14(0.3+0.04*7)＝3.14*0.58＝1.62 9.895
L8＝3.14(0.3+0.04*8)＝3.14*0.62＝1.945 11.84
L9＝3.14(0.3+0.04*9)＝3.14*0.66＝2.07 13.91
L10＝3.14(0.3+0.04*10)＝3.14*0.7＝2.195 16.105
L11＝3.14(0.3+0.04*11)＝3.14*0.74＝2.32 18.425
L12＝3.14(0.3+0.04*12)＝3.14*0.78＝2.45 20.875
L13＝3.14(0.3+0.04*13)＝3.14*0.82＝2.575 23.45
L14＝3.14(0.3+0.04*14)＝3.14*0.86＝2.7 26.15
L15＝3.14(0.3+0.04*15)＝3.14*0.9＝2.825 28.975
L16＝3.14(0.3+0.04*16)＝3.14*0.94＝2.95 32.05
L17＝3.14(0.3+0.04*17)＝3.14*0.98＝3.075 35.125
L18＝3.14(0.3+0.04*18)＝3.14*1.02＝3.2 38.325
L19＝3.14(0.3+0.04*19)＝3.14*1.06＝3.325 41.65
L20＝3.14(0.3+0.04*20)＝3.14*1.1＝3.45 45.1
L21＝3.14(0.3+0.04*21)＝3.14*1.14＝3.5795 48.68
L22＝3.14(0.3+0.04*22)＝3.14*1.18＝3.705 52.385
L23＝3.14(0.3+0.04*23)＝3.14*1.22＝3.83 56.215
L24＝3.14(0.3+0.04*24)＝3.14*1.26＝3.956 60.171
L25＝3.14(0.3+0.04*25)＝3.14*1.3＝4.08 64.251
L26＝3.14(0.3+0.04*26)＝3.14*1.34＝4.2 68.451
L27＝3.14(0.3+0.04*27)＝3.14*1.38＝4.33 72.781
L28＝3.14(0.3+0.04*28)＝3.14*1.42＝4.4588 77.2398
L29＝3.14(0.3+0.04*29)＝3.14*1.46＝4.5844 81.82
L30＝3.14(0.3+0.04*30)＝3.14*1.5＝4.71 86.5342
L31＝3.14(0.3+0.04*31)＝3.14*1.54＝4.8356 91.3698
L32＝3.14(0.3+0.04*32)＝3.14*1.58＝4.9612 96.331
L33＝3.14(0.3+0.04*33)＝3.14*1.62＝5.0868 101.4178
Known aircraft quickens the departure time on 101 meters runways be 2.58 seconds; Capstan winch has twined 101 meters sheet base band in 2.58 seconds; Twine 33 layers altogether, average per second rope woolding is 13 layers/second of 33/2.58 ≈, and the cumulative length of cable wire after twining 33 layers is 101 meters; The cooling diameter of the 33rd layer of cable wire on capstan winch is 1.62 meters, and design capstan winch maximum gauge is 1.8 meters.
If select for use diesel engine that power is provided; The rated speed of rotation of diesel engine is 1500 rev/mins, and the per second rotating speed is 25 commentaries on classics, is adjusted into 13 revolutions per seconds through the belt pulley speed change; Be that diesel engine needs only to the winch capstan winch provides 13 revolutions per seconds rotating speed, can reach the takeoff speed of carrier-borne aircraft.Speed time curve is shown in figure 10:
Can find out through velocity curve; Aircraft is identical at the velocity curve of take off on 100 meters runways 2.58 seconds times spent and the time spent 6-10 second of on 300 meters runways, taking off; Since velocity curve is identical, remaining issues is the power of diesel engine, if the thrust of aircraft jet engine is soft thrust; Diesel engine just can provide 1-3 hard thrust doubly for aircraft is extra, and the various carrier-borne aircrafts that launch the 33-60 ton are exactly easily and the problem of lifting.
If use the directly shaft coupling transmission of low speed high-power diesel engine, as shown in Figure 5, can be that aircraft provides extra power and acceleration/accel also later in the power-transfer clutch adhesive through the throttle of regulating diesel engine.
No matter be steam catapult or electromagnetic launch device, must possess following characteristic:
1) must possess powerful accumulation of energy, can in 2.5 seconds, discharge maximum thrust rapidly is that aircraft provides the initial velocity that takes off; And for aircraft the takeoff speed of 80 meter per seconds is provided at 2.5 seconds ends;
The huge inertia that 2) must overcome shuttle during at the runway terminal when shuttle stops it in short range;
3) shuttle rapidly return to origin prepare to launch next time;
Here we that bulky, the complex structure and the huge waste of power of steam catapult and electromagnetic launch device no longer is discussed is not enough, the present invention is only described how to the ingenious realization of above-mentioned three characteristics;
1) ejection process shown in Fig. 5-6, is an example with the electrical motor; The root diameter of supposing 2000 kilowatts of electrical motors is 2 meters, and the diameter of capsizing moment spindle is 0.3, and radius ratio is 1: 0.15=6.7: 1; Utilize the great power of electrical motor self and the rotation potential of rotor; Add the rotation potential that comprises transmission shaft, belt pulley and flywheel, combine the driving towing capstan to twine the machine leader base band through power-transfer clutch, so have powerful driving torque since the axle of 0.3 rice diameter; Under 2000 kilowatts of direct motor drive; When the machine leader base band twines full capstan winch gradually, the diameter of capstan winch and the equal diameters of rotor, moment of torsion equates; 2000 kilowatts power is identical with the power of carrier-borne aircraft; Be equivalent to carrier-borne aircraft and absorbed the extra powerful thrust of ejector with identical accelerated speed, this extra-push model can also be multiplied through synthetic method, and aircraft catapult-assisted take-off under the boosting with the above extra-push model of twice is very easily like this.
2) the shuttle braking procedure is as shown in Figure 7, when the sheet base band of returning on the capstan winch has discharged; Power-transfer clutch discharges, and towing capstan runs out of steam, at this moment; Return the end of only returning the sheet base band on the capstan winch and be connected with capsizing moment spindle, the diameter that returns capstan winch is 2 meters, and the diameter of capsizing moment spindle is 0.3 meter; Radius ratio is 1: 0.15=6.7: 1, if drg is braked returning on the cylindrical of capstan winch, torque ratio then is 1: 6.7; Return capstan winch and be easy to drag, return that the sheet base band is drawn shuttle simultaneously and towing capstan is braked simultaneously, add the braking force that the drg on the towing capstan produces; Shuttle brakes immediately that to stop effect will be very obvious, and the moment brake is feasible.It also is feasible not using drg directly to use and returning the windlass braking, because the sheet base band has good elastic buffer property, reason is the same with kiteflying, and kite string is put and is over, and kite can be not out of control yet.All known ejection modes of root tool at present do not have this kind traction braking characteristic.
No matter use which kind of primary mover, in a single day ejector of the present invention gets into combat readiness, and primary mover is in operative condition or dynamic energy accumulating state all the time; Have only when cataplane power-transfer clutch just to give capstan winch with transfer of energy; Finish in case launch, power-transfer clutch breaks off the energy of capstan winch again, and braking procedure is just braked the inertia kinetic energy of capstan winch, shuttle and machine leader base band; And need not motor and other rotatable parts are braked; The rotation potential of other rotatable parts can continue to be left and launches use next time, and it is distinctive feature of the present invention that energy efficient improves rate of energy, and the preresearch estimates capacity usage ratio is more than 95%; The capacity usage ratio of the steam catapult of the U.S. has only 30%, and the capacity usage ratio of electromagnetic launch device has only 25%.
3) returning of shuttle has been exactly very simple thing; Owing to return the sheet base band is to twine from the axial region that returns capstan winch; And shuttle is in zero load, only needs very little power to drive, and drives identical with towing capstan with the principle of work of braking; Because adopt the speed change of big small belt pulley, shuttle can use lower safety speed to return.
About the machine leader base band; Comprise the nylon6 chips base band; Carbon fiber sheet base band, rubber combined base band of carbon fiber, nylon rubber composite sheet base band and rubber combined base band of steel wire or the like, kind is very complete, if select general thickness 20mm for use; The nylon fibre sheet base band of width 400mm, rupture strength is 200 tons.The carrier-borne aircraft of traction 30-50 ton also has 4-5 intensity doubly redundant.According to the intensity needs, the width and the thickness that just increase the sheet base band get final product, therefore; Utilizing high-strength nylon sheet base band or carbon fiber sheet base band is safe and feasible as the transmission of energy medium fully, not only in light weight, and intensity is high; Also have the anti-corrosion characteristic, adapt to marine equipment most.
In sum; Carrier-borne aircraft of the present invention launches the ejector of driving method and prior art and compares, and has very outstanding remarkable advantages, and this advantage comprises; Design science, volume are little, simple in structure, in light weight, the utilization ratio of power is high, also have height can be handling, high security or the like.
Claims (4)
1. composite and multi-purpose aircraft carrier continental rise catapult-assisted take-off trainer is characterized in that, comprises support, hydraulic lifting device, cantilever runway, carrier-borne aircraft, ejector assembly; Wherein, Support is arranged among the trough of ground excavation, and an end of cantilever runway is connected with support through twisted axis, and the ejector assembly is arranged among the outstanding support; The bottom-hinged of the upper end of hydraulic lifting device and cantilever runway, the lower end is connected with the trough bottom;
The cantilever runway be to process with U type channel-section steel; The flange of bending in the both sides, top of U type channel-section steel are provided with mutually is provided with two-layer carrying roller in the middle of the U type channel-section steel, and the top of upper strata carrying roller is provided with the grooved slide plate; Roll with the carrying roller two ends and be connected in grooved slide plate bottom; Grooved slide plate top is provided with the aircraft pallet, and the aircraft pallet is the T type, and the aircraft tray upper surface has the T type hole that matches with the undercarriage position; The detouchable undercarriage connects frame bottom and is connected with T type hole through the dovetail structure, and the two ends of cantilever runway are provided with leading sheave, start position sensor and final position sensor;
The ejector assembly; Comprise: frame, ejection controller, primary mover, main driving axle, pay transmission shaft, coupler, bearing seat, towing capstan, return capstan winch, machine leader base band, return the sheet base band; Wherein ejection controller, primary mover are fixed on the frame; The end that one end of machine leader base band is wrapped on the towing capstan axle, return the sheet base band is wrapped in and returns on the capsizing moment spindle; The other end of machine leader base band is through the leading sheave of cantilever runway bottom, through the carrying roller of cantilever runway bottom; Be connected fixingly again with grooved slide plate left end in the cantilever runway through the leading sheave of cantilever runway left part and upper strata carrying roller, the other end that returns the sheet base band is connected with grooved slide plate right-hand member in the cantilever runway through the leading sheave of cantilever runway right-hand member to be fixed;
Towing capstan and the both sides of returning capstan winch are respectively even power-transfer clutch and drg arranged; Towing capstan is arranged on the main driving axle through bearing; Returning capstan winch is arranged on pair transmission shaft through bearing; Main driving axle is fixed through bearing frame and frame respectively with pair transmission shaft two ends; One end of main driving axle is connected with primary mover through coupler, and the other end is provided with small belt pulley and is connected with the big belt pulley of paying the moving axis end through belt, and then an interlock pair transmission shaft rotates synchronously; All fix with the grooved slide plate bottom that is arranged in the cantilever runway owing to be wrapped in the machine leader base band on the towing capstan and be wrapped in the other end of returning the sheet base band of returning capstan winch, towing capstan comes and goes mobile on the cantilever runway with the aircraft pallet that the alternate rotation of returning capstan winch drives its top of grooved slide plate drive;
Carrier-borne aircraft continental rise catapult-assisted take-off training step is following:
1) primary mover starts; Primary mover is given main driving axle through coupler with transmission of power; Main driving axle drives the good fortune transmission shaft through big small belt pulley and rotates, this moment towing capstan with return capstan winch and receive the drg braking to keep static, the aircraft pallet is positioned at the starting point of taking off of cantilever runway; The machine leader base band that connects towing capstan and grooved slide plate all extends among the cantilever runway, and the sheet base band of returning that connects the grooved slide plate and return capstan winch all is wrapped in and returns on the capstan winch;
2) carrier-borne aircraft slides on the aircraft pallet, and the rear portion of three alighting gears is connected support and connects the location with alighting gear on the aircraft pallet, and aero-engine quickens to wait for the catapult-assisted take-off instruction;
3) control tower is assigned the instruction of taking off, and the ejector operator presses and launches button, and towing capstan discharges with the drg that returns on the capstan winch; Power-transfer clutch adhesive on the towing capstan, main driving axle drives towing capstan through power-transfer clutch and rotates, and the machine leader base band is twined on towing capstan fast; In the winding process of machine leader base band on the towing capstan axle, the speed of wrap of machine leader base band becomes acceleration with fast towing aircraft pallet and moves by accelerating slowly on the cantilever runway; Be in returning of free rotary state and return the sheet base band on the capstan winch,, will return the sheet base band fast and discharge along with moving of aircraft pallet; The winding process of dispose procedure and towing capstan is opposite; The cooling diameter of traction belt from big to small, rotating speed is by accelerating, with leading aircraft pallet quick travel on the cantilever runway slowly; Carrier-borne aircraft is implemented to launch towing, for carrier-borne aircraft provides the optimum training takeoff speed;
4) when the aircraft pallet moved to cantilever runway terminal point, carrier-borne aircraft had reached the training takeoff speed, departs; The aircraft pallet triggers end point sensor, and the power-transfer clutch that ejection controller is controlled on the towing capstan immediately discharges, and towing capstan is implemented braking with the drg adhesive of returning on the capstan winch simultaneously; The aircraft pallet stops at cantilever runway terminal point; At this moment, the machine leader base band all is wrapped on the towing capstan, returns the sheet base band and extends among the cantilever runway;
5) towing capstan with return capstan winch braking after, drg discharges immediately, ejection controller is controlled the power-transfer clutch adhesive of returning on the capstan winch immediately; Pay transmission shaft and return the rotation of capstan winch dish through the power-transfer clutch driving, the sheet base band enforcement winding of returning that extends in the cantilever runway is regained, the aircraft pallet returns at random; At this moment, towing capstan is in free rotary state, and the machine leader base band that is wrapped on the towing capstan extends among the cantilever runway in the return course of aircraft pallet again; When aircraft pallet return to origin; The starting point sensor-triggered, the power-transfer clutch that returns on the capstan winch discharges, and towing capstan is braked with the drg that returns capstan winch simultaneously; The aircraft pallet is positioned on the starting point of taking off of cantilever runway, prepares next frame carrier-borne aircraft is implemented to launch.
2. catapult-assisted take-off trainer according to claim 1; It is characterized in that when the cantilever runway is parallel to the ground, being used for dynamic heavy airplane catapult-assisted take-off, when the cantilever runway is kicked up by the lifting of hydraulic lifting device, be used for light-duty dynamic aircraft or unpowered glider launching.
3. catapult-assisted take-off trainer according to claim 1 is characterized in that drg and power-transfer clutch are magnet stopper, magnetic clutch or hydraulic brake, hydraulic clutch or pneumatic braking device, pneumatic clutch.
4. catapult-assisted take-off trainer according to claim 1 is characterized in that primary mover is a kind of in electrical motor, diesel engine, steam turbine, the fanjet.
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| CN103112591A (en) * | 2013-01-31 | 2013-05-22 | 济南环太机电技术有限公司 | Multipurpose pneumatic type launch airborne landing flight training device |
| CN103910069A (en) * | 2013-01-03 | 2014-07-09 | 滕德选 | Aircraft catapult driven by jet engine |
| CN104092015A (en) * | 2014-07-29 | 2014-10-08 | 零八一电子集团四川红轮机械有限公司 | Four-cantilever torsion shaft device for turning over shelter top cover |
| WO2015073091A1 (en) * | 2013-08-27 | 2015-05-21 | Engineered Arresting Systems Corporation | Electric unmanned aerial vehicle launcher |
| CN104787353A (en) * | 2014-01-17 | 2015-07-22 | 凌春林 | Magnetic ejection device |
| CN106904289A (en) * | 2017-03-21 | 2017-06-30 | 张宏 | Aircraft elevation angle ejector |
| US10118713B2 (en) | 2013-08-27 | 2018-11-06 | Engineered Arresting Systems Corporation | Electric unmanned aerial vehicle launcher |
| CN112829961A (en) * | 2021-02-19 | 2021-05-25 | 王运宏 | Aircraft carrier catapult |
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| CN106904289A (en) * | 2017-03-21 | 2017-06-30 | 张宏 | Aircraft elevation angle ejector |
| CN112829961A (en) * | 2021-02-19 | 2021-05-25 | 王运宏 | Aircraft carrier catapult |
| CN113479340A (en) * | 2021-07-23 | 2021-10-08 | 航天时代飞鹏有限公司 | Unmanned aerial vehicle ejection method |
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