CN105584641A - Synchronous shipboard aircraft catapult and dispersed energy storage and concentrated acting method - Google Patents
Synchronous shipboard aircraft catapult and dispersed energy storage and concentrated acting method Download PDFInfo
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- CN105584641A CN105584641A CN201610004329.4A CN201610004329A CN105584641A CN 105584641 A CN105584641 A CN 105584641A CN 201610004329 A CN201610004329 A CN 201610004329A CN 105584641 A CN105584641 A CN 105584641A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Launching or towing gear
- B64F1/06—Launching or towing gear using catapults
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Abstract
The invention provides a synchronous shipboard aircraft catapult and a dispersed energy storage and concentrated acting method. The synchronous shipboard aircraft catapult comprises a pneumatic device, an acting tunnel, a sliding shuttle tractor and a controller. The controller controls the pneumatic device to introduce high-pressure air into the two ends of the acting tunnel, the sliding shuttle tractor located in the acting tunnel is driven to move in a reciprocating manner at a high speed, a sliding shuttle is driven to be catapulted from a start point to an end point, and a shipboard aircraft is catapulted to lift off; and then the sliding shuttle is driven to automatically return to the catapulting start point, and kinetic energy of the pneumatic device is transmitted to the shipboard aircraft. Compared with various traditional catapults in the prior art, the synchronous shipboard aircraft catapult has the beneficial effects of being simple in structure, easy to machine, reliable in work, high in man-machine effect, small in occupied space, high in energy use rate, capable of saving energy by over 90%, free of pollution to the environment and easy to maintain, and therefore the tunnel type shipboard aircraft catapult can be used for column mounting of aircraft carriers in various power manners or land-based airports.
Description
Technical field
The present invention relates to aircraft carrier equipment technology field, the method for acting is concentrated in specifically a kind of synchronous mode carrier-based aircraft ejector and dispersion accumulation of energy.
Background technology
Can see that at present the aircraft carrier ejector reruning mainly contains two kinds, one is openly to use steam catapult in 10 aircraft-carrier battle groups of the U.S., tradition steam catapult is two open cylinder, machining accuracy is high, difficulty of processing is large, poor durability, need often maintenance, often launching 500-1000 sortie will overhaul three months, more than maintenance personal 500 people, steam-cylinder piston frictional resistance is large, energy transformation ratio is low, service efficiency is low, maintenance cost is high, and steam catapult needs nuclear reactor that high steam is provided, also need the steam storage tank of two 200 cubic metres, take up room large, system complex, manufacturing process only has the U.S. to grasp.
The second is the Electromagnetical ejector that the U.S. is is researching and developing, the deficiency existing is complex structure, cost is high, consume energy high, 100,000 kilowatts of electrical power are equivalent to the power consumption in whole Shanghai City, when use, the electric energy of 100000 kilowatts will store through forcing accumulating mechanism to convert rotation function to, used time converts rotation function to electric energy again, the power delivery converting to converts magnetic energy to the superconducting coil in linear electric motors, magnetic energy drives mover to produce the kinetic energy that drives shuttle to move, through four power conversion, the electric energy of 100000 kilowatts has lost more than 60%, the electric energy less than 30% of actual acting. and transfer process not only produces a large amount of used heat and needs low-temperature cooling system cooling rapidly, launch at every turn and also will produce superpower magnetic storm, high-intensity magnetic storm can produce badly damaged to shipborne radar communication apparatus, therefore huge power consumption Electromagnetical ejector can only use on the super nuclear aircraft carrier of Ford level of the U.S., and also demonstration of researcher, can Electromagnetical ejector replace steam catapult to use on being on active service aircraft carrier future completely, hang in doubt at present, only have at present the U.S. to grasp electromagnetic launch technology, for the country of those construction at the early-stage aircraft carrier powered by conventional energy, the development that spends huge sums has the Electromagnetical ejector of numerous drawbacks, the selection of losing more than gain of a kind of blindness really.
The linear electric motors that two open cylinder that steam catapult adopts and Electromagnetical ejector adopt, the monomer power consumption in 3 seconds of two kinds of ejectors is respectively 70,000 kilowatts and 100,000 kilowatts, the big and grade manufacture difficulty of power consumption is big is conceivable.
By finding out two of prior art kinds of carrier-based aircraft ejector researchs, carrier-based aircraft ejector is exactly a kind ofly to convert electric energy or fluid media (medium) potential energy moment to shuttle and launching the kinetic energy switching mechanism that drives carrier-borne aircraft high speed slide on runway, science select power conversion mechanism be carrier-based aircraft ejector can be practical, durable, the key of efficient energy-saving and reduction processing technology and cost.
Summary of the invention
Technical assignment of the present invention is to solve the deficiencies in the prior art, a kind of synchronous mode carrier-based aircraft ejector is provided and disperses accumulation of energy to concentrate the method for acting.
As everyone knows, fanjet and turboshaft engine are the highest power-equipments of power density that people produce up to now, fanjet is widely used in aerospace field at present, such as aircarrier aircraft engine, Launch Vehicle Engine, modiolus engine is widely used in the technical field such as helicopter, gas turbine, and therefore fanjet and turboshaft engine can apply to reduce carrier-borne aircraft taking up room and improving the tonnage that launches carrier-borne aircraft on aircraft carrier on carrier-based aircraft ejector.
Technical scheme of the present invention realizes in the following manner, adopt some cover monomer pneumatic equipments mode in parallel or series connection to disperse accumulation of energy, then unifying to control synchronous acting by controller focuses on kinetic energy on shuttle, allow the speed synchronised of taking off of shuttle acting and carrier-borne aircraft, drive carrier-borne aircraft to take off on short distance runway.
A kind of synchronous mode carrier-based aircraft ejector, comprise pneumatic equipment, acting tunnel, shuttle tractor and controller, controller control pneumatic equipment is introduced pressure-air respectively the two ends in acting tunnel, driving is arranged in the shuttle tractor high speed back and forth movement in acting tunnel, drive shuttle to launch terminal from starting point carrier-borne aircraft is launched to lift-off, then drive shuttle to automatically return to and launch starting point, realize pneumatic equipment transmission to carrier-borne aircraft by kinetic energy, wherein:
Pneumatic equipment comprises and launches pneumatic equipment and return to pneumatic equipment, launch pneumatic equipment and return to pneumatic equipment the both sides or the bottom that are separately positioned on acting tunnel, launching pneumatic equipment is launched starting point and is connected with the right-hand member in acting tunnel by air supply duct, returning to pneumatic equipment launches terminal by air supply duct with acting tunnel left end and is connected, the right-hand member in acting tunnel launches the end that starting point and left end return to terminal and is also provided with air bleeder valve, the both ends in acting tunnel are also provided with isolation damper, play point sensor and end point sensor, playing point sensor is connected with controller by data wire with end point sensor, on air supply duct, be also provided with air velocity transducer, wind pressure sensor, temperature sensor and cooling system,
The upper opening in acting tunnel is provided with laminated deck, in the middle of laminated deck, be provided with and crack, laminated deck is by installing plate, sealing strip and runway deck compound composition from bottom to top, installing plate is fixed on the top of air supply duct, installing plate and runway deck relative level stretch in the middle of acting tunnel and retain and crack, and the relative edge who is clipped in two sealing strips between installing plate and runway deck is bent downwardly composition lip seal configuration at the place of cracking;
The two ends of shuttle tractor are provided with the sealing plate matching with the tunnel cross sectional shape that does work, the arranged outside of sealing plate has the elastic sealing element matching with acting tunnel cross sectional shape, the center top of shuttle tractor is provided with shuttle connecting plate, the top margin of shuttle connecting plate protrudes upward with shuttle and links together through the slotting in middle of laminated deck, upper and lower and the both sides of shuttle tractor are also provided with directive wheel, directive wheel is connected with both sides and the bottom rolling in acting tunnel, and the directive wheel at top rolls and is connected with installing plate bottom;
Controller is made up of remote controller, single-chip microcomputer, remote controller receives the running parameter of end point sensor, a point sensor, air velocity transducer, temperature sensor, wind pressure sensor, pneumatic equipment power controller by single-chip microcomputer, and control pressure-air supply equipment power stage, control reversal valve, the switching of air bleeder valve and the work of cooling system, that realizes shuttle launches, returns and launch power stage.
Described a kind of synchronous mode carrier-based aircraft ejector, pneumatic equipment is electric motor driven tandem type shaft flow fan, the engine-driven axial flow blower of modiolus or fanjet.
Described a kind of synchronous mode carrier-based aircraft ejector, end point sensor, a point sensor are infrared photoelectric sensor or magnetic induction sensor.
Described a kind of synchronous mode carrier-based aircraft ejector, pneumatic equipment power controller is the throttle control of fanjet, modiolus engine or the frequency converter of tandem Axial-flow fan motor.
Described a kind of synchronous mode carrier-based aircraft ejector, isolation damper is one or more the complex in spring, pneumatic cylinder or elastic sponge mattress.
Work method is concentrated in a kind of dispersion accumulation of energy of synchronous mode carrier-based aircraft ejector, comprise pneumatic equipment, acting tunnel, shuttle tractor and controller, controller control pneumatic equipment is introduced pressure-air respectively the two ends in acting tunnel, driving is arranged in the shuttle tractor high speed back and forth movement in acting tunnel, drive shuttle to launch terminal from starting point carrier-borne aircraft is launched to lift-off, then drive shuttle to automatically return to and launch starting point, realize pneumatic equipment transmission to carrier-borne aircraft by kinetic energy, specifically launch step as follows:
Set the right-hand member in acting tunnel for launching starting point, left end, for launching terminal, is made pneumatic equipment with aviation turbofan engine or modiolus motor driven axial flow blower and is produced the absolutely empty air-flow of high pressure;
When carrier-borne aircraft is launched in preparation, the air bleeder valve at acting two ends, tunnel is opened, controller starts some and launches pneumatic equipment and run up and make it simultaneously in disperseing energy accumulating state, the air-flow of turbojet engine or the ejection of modiolus engine operation, not only there are high flow capacity and high blast, also there are 2000 DEG C of above high temperature, air supply duct is added thermosetting heat storage boiler by high temperature gas flow, the pressure-air that launches pneumatic equipment generation flows the starting point that enters acting tunnel by air supply duct, emptying from the air bleeder valve of acting tunnel starting point, now shuttle tractor is positioned at the starting point in acting tunnel, shuttle is positioned on the right-hand member ejector point that laminated deck cracks, the draw bar of carrier-borne aircraft nose-gear and shuttle hook link together, carrier-borne aircraft is in the SBR that takes off of awaiting orders,
When flight control tower sends after carrier-borne aircraft catapult-assisted take-off order, controller controls the air bleeder valve of cutting out acting starting point place, tunnel immediately, some run up in disperseing the pressure-air stream concentrated starting point that enters acting tunnel right-hand member immediately that pneumatic equipment produces of launching of energy accumulating state, cooling system sprays into water smoke and low-pressure water steam in air supply duct simultaneously, water smoke and low-pressure water steam mix vaporized expanding immediately with the high temperature air stream that launches the ejection of pneumatic equipment tail in air duct, in reducing air supply duct temperature, produce the right-hand member that acts on shuttle tractor higher than the HTHP mist of original volume several times, drive shuttle tractor to move to the left end in acting tunnel at a high speed, drive the shuttle above deck to move to terminal from runway starting point simultaneously, complete kinetic energy and speed transmission to carrier-borne aircraft by shuttle of pneumatic equipment, carrier-borne aircraft is launched to lift-off, because the engine that launches pneumatic equipment and carrier-borne aircraft all belongs to steam spraying engine, the thrust of launching pneumatic equipment is far longer than the motor power of carrier-borne aircraft, and accelerated speed and carrier-borne aircraft synchronised, can make up being short of power of various carrier-borne aircraft short takeoffs,
When shuttle tractor moves to after acting tunnel left end terminal, through the stop motion of isolation damper buffer damping, trigger runway end point sensor simultaneously, acting tunnel does the air bleeder valve of holding and closes immediately, the air bleeder valve of acting tunnel right-hand member is opened immediately, entered immediately the left end in acting tunnel by air supply duct in the pressure-air stream that returns to pneumatic equipment generation of energy accumulating state, in returning to pneumatic equipment tail spray pressure-air stream to introduce air supply duct, cooling system sprays into water smoke or water at low temperature steam, in reducing air supply duct temperature, water smoke or the water at low temperature steam vaporized expanding that is heated, the high temperature HTHP air stream that has increased expansion energy is sent into acting tunnel left end, automatically drive shuttle tractor to turn back to rapidly the right-hand member in acting tunnel, through isolation damper buffer damping, stop motion is awaited orders, triggered point sensor simultaneously, the air bleeder valve at two ends, tunnel is opened, launch pneumatic equipment and return to pneumatic equipment and enter dispersion energy accumulating state simultaneously, prepare second carrier-borne aircraft catapult-assisted take-off.
A kind of synchronous mode carrier-based aircraft ejector of the present invention and dispersion accumulation of energy concentrate the method for acting to have following outstanding excellent effect:
1) launch power flexible allocation: because launch the summation that power is some cover single devices power, acting as required, according to the quantity of carrier-borne aircraft flexible configuration monomer power of launching different tonnages, as everybody's tug-of-war or boat tracker tow;
2) energy-saving and cost-reducing: well-known, destroying 15 fully loaded tonnage is 33 tons, adopting the sliding formula of jumping to take off can only 27 tons take off, filling it up with 6 tons of fuel and ammunition just can not slide the formula of jumping and take off, if allow fully loaded 33 tons to destroy 15 and take off to be just necessary for and destroy 15 and increase in addition the thrusts of 6 tons, knownly destroy 15 and have the steam spraying engine of two 1200 kilowatts, general power is 2400 kilowatts, the power of 2400 kilowatts can only be slided the formula of jumping and take off 27 tons, the power consumption of average needs per ton is 2400 kilowatts/27 tons=88.9 kilowatts/ton, need to increase thrust 88.9*6=533.28 kilowatt if increase by 6 tons of load, can find out by calculating, adopt synchronous mode carrier-based aircraft ejector to launch 15 carrier-borne aircrafts of destroying of 33 tons, the power of ejector only needs 533.28 kilowatts, if launching 1 ton by 100 kilowatts calculates, do not include the power of carrier-borne aircraft self, the carrier-borne aircraft that launches one 33 tons at most also only needs 3300 kilowatts, launch at most namely 6000 kilowatts of the carrier-borne aircrafts of 60 tons, the power consumption of the steam catapult using on known U.S. active service aircraft carrier is 6.5 ten thousand kilowatts, the Electromagnetical ejector power consumption of developing is 100,000 kilowatts, by contrast, the design power consumption of synchronous mode carrier-based aircraft ejector be steam catapult 1/10, 1/16 of Electromagnetical ejector, energy-saving effect is apparent.
Pneumatic equipment can utilize the aviation power equipment of various high power densities or wind-tunnel facilities to produce pressure-air stream, the wind speed that known wind-tunnel facilities produces can reach 9 Mach, flow the shuttle tractor high-speed mobile driving in acting tunnel by pressure-air, realize the object of carrier-borne aircraft short distance catapult-assisted take-off, compared with various traditional ejector of prior art, have simple in structure, reliable operation, be easy to processing, take up room little, energy transformation ratio is high, environmentally safe, for ease of maintenaince, it is adjustable that control pressure-air flow velocity and flow are realized ejection speed, launch quality adjustable, most importantly can use the feature such as various energy resources and working media, therefore tunnel type carrier-based aircraft ejector ejector can be equipped use on the aircraft carrier of various power form or continental rise airport.
Compared with the acting manufacturing process in tunnel and the open cylinder of traditional steam catapult, technique is simpler, is more prone to processing and improves machining accuracy, realizes by the two ends of pressure-air being introduced respectively to acting tunnel the full-automation of launching and returning. the shuttle tractor that directive wheel is equipped with in employing does work in rectangle acting tunnel, has increased lifting surface area, has reduced frictional resistance, has improved energy conversion efficiency. from manufacturing process with power consumption compared with steam catapult or Electromagnetical ejector, manufacture steam catapult or Electromagnetical ejector and can be compared to the climbing Himalayas, manufacture synchronous mode carrier-based aircraft ejector as carried out level land, because no matter be fanjet or modiolus engine, or tandem type shaft flow fan is all existing electromechanical equipment, as long as shuttle can be realized in the high-speed air flow introducing acting tunnel of its generation to be driven with the driving of synchronizeing of carrier-borne aircraft, the back and forth movement of shuttle dolly just changes air-flow direction simply, acting tunnel and air supply duct are processed into universal steel plate rivet welding, very simple and reliable.
Brief description of the drawings
Fig. 1 is the overall structure schematic diagram of synchronous mode aircraft carrier ejector;
Fig. 2 is the section structure schematic diagram of synchronous mode aircraft carrier ejector;
Fig. 3 is the acting schematic diagram of shuttle tractor in acting tunnel;
Fig. 4 is the plan structure schematic diagram of shuttle tractor;
Fig. 5 is controller operation principle block diagram;
Fig. 6 is the second embodiment schematic diagram of synchronous mode aircraft carrier ejector.
Mark in accompanying drawing represents respectively: launch pneumatic equipment 1, return to pneumatic equipment 2, air supply duct 3, air bleeder valve 4, shuttle tractor 5, shuttle 6, isolation damper 7, directive wheel 8, crack 9, installing plate 10, sealing strip 11, runway deck 12, acting tunnel 13, shuttle connecting plate 14, sealing plate 15, elastic sealing element 16.
Detailed description of the invention
Below in conjunction with accompanying drawing, a kind of synchronous mode carrier-based aircraft ejector of the present invention is described in further detail.
A kind of synchronous mode carrier-based aircraft ejector of the present invention, as shown in Figure 1. Comprise pneumatic equipment, acting tunnel 13, shuttle tractor 5 and controller, controller control pneumatic equipment is introduced pressure-air respectively the two ends in acting tunnel 5, driving is arranged in the shuttle tractor 5 high speed back and forth movements in acting tunnel 13, drive shuttle 6 to launch terminal from starting point carrier-borne aircraft is launched to lift-off, then drive shuttle 6 to automatically return to and launch starting point, realize pneumatic equipment transmission to carrier-borne aircraft by kinetic energy, wherein:
Pneumatic equipment comprises and launches pneumatic equipment 1 and return to pneumatic equipment 2, launch pneumatic equipment 1 and return to pneumatic equipment 2 both sides or the bottom that are separately positioned on acting tunnel 13, launching pneumatic equipment 1 is launched starting point and is connected with the right-hand member in acting tunnel 13 by air supply duct 3, returning to pneumatic equipment 2 launches terminal by air supply duct 3 with acting tunnel 13 left ends and is connected, the right-hand member in acting tunnel 13 launches the end that starting point and left end return to terminal and is also provided with air bleeder valve 4, the both ends in acting tunnel 13 are also provided with isolation damper 7, play point sensor and end point sensor, playing point sensor is connected with controller by data wire with end point sensor, on air supply duct 3, be also provided with air velocity transducer, wind pressure sensor, temperature sensor and cooling system,
As shown in Figure 2 and Figure 3, the upper opening in acting tunnel 13 is provided with laminated deck, in the middle of laminated deck, be provided with and crack, laminated deck is by installing plate 10, sealing strip 11 and runway deck 12 compound composition from bottom to top, installing plate 10 is fixed on the top of air supply duct, installing plate 10 and runway deck 12 relative levels stretch in the middle of acting tunnel 13 and retain and crack 9, and the relative edge who is clipped in two sealing strips 11 between installing plate 10 and runway deck 12 is bent downwardly composition lip seal configuration at 9 places of cracking;
As Fig. 3, shown in Fig. 4, the two ends of shuttle tractor 5 are provided with the sealing plate 15 matching with tunnel 13 cross sectional shapes that do work, the arranged outside of sealing plate 15 has the elastic sealing element 16 matching with acting tunnel 13 cross sectional shapes, the center top of shuttle tractor 5 is provided with shuttle connecting plate 14, the top margin of shuttle connecting plate 14 protrudes upward with shuttle 6 and links together through the slotting in middle 9 of laminated deck, upper and lower and the both sides of shuttle tractor 5 are also provided with directive wheel 8, directive wheel 8 is connected with both sides and the bottom rolling in acting tunnel 13, the directive wheel 8 at top rolls and is connected with installing plate 12 bottoms,
As shown in Figure 5, controller is made up of remote controller, single-chip microcomputer, remote controller receives the running parameter of end point sensor, a point sensor, air velocity transducer, temperature sensor, wind pressure sensor, pneumatic equipment power controller by single-chip microcomputer, and control pressure-air supply equipment power stage, control reversal valve, the switching of air bleeder valve and the work of cooling system, that realizes shuttle launches, returns and launch power stage.
Described a kind of synchronous mode carrier-based aircraft ejector, pneumatic equipment is electric motor driven tandem type shaft flow fan, the engine-driven axial flow blower of modiolus or fanjet.
Described a kind of synchronous mode carrier-based aircraft ejector, end point sensor, a point sensor are infrared photoelectric sensor or magnetic induction sensor.
Described a kind of synchronous mode carrier-based aircraft ejector, pneumatic equipment power controller is the throttle control of fanjet, modiolus engine or the frequency converter of tandem Axial-flow fan motor.
Described a kind of synchronous mode carrier-based aircraft ejector, isolation damper is one or more the complex in spring, pneumatic cylinder or elastic sponge mattress.
Embodiment 1
A kind of synchronous mode carrier-based aircraft ejector, as shown in Figure 1, comprise pneumatic equipment, acting tunnel, shuttle tractor and controller, controller control pneumatic equipment is introduced pressure-air respectively the two ends in acting tunnel, driving is arranged in the shuttle tractor high speed back and forth movement in acting tunnel, drives shuttle to launch terminal from starting point carrier-borne aircraft is launched to lift-off, then drives shuttle to automatically return to and launches starting point, realize pneumatic equipment transmission to carrier-borne aircraft by kinetic energy, specifically launch step as follows:
Set the right-hand member in acting tunnel for launching starting point, left end, for launching terminal, is made pneumatic equipment with aviation turbofan engine or modiolus motor driven axial flow blower and is produced the absolutely empty air-flow of high pressure;
When carrier-borne aircraft is launched in preparation, the air bleeder valve at acting two ends, tunnel is opened, controller starts some and launches pneumatic equipment and run up and make it simultaneously in disperseing energy accumulating state, the air-flow of turbojet engine or the ejection of modiolus engine operation, not only there are high flow capacity and high blast, also there are 2000 DEG C of above high temperature, air supply duct is added thermosetting heat storage boiler by high temperature gas flow, the pressure-air that launches pneumatic equipment generation flows the starting point that enters acting tunnel by air supply duct, emptying from the air bleeder valve of acting tunnel starting point, now shuttle tractor is positioned at the starting point in acting tunnel, shuttle is positioned at the right-hand member that laminated deck cracks and launches in starting point, the draw bar of carrier-borne aircraft nose-gear and shuttle hook link together, carrier-borne aircraft is in the SBR that takes off of awaiting orders,
When flight control tower sends after carrier-borne aircraft catapult-assisted take-off order, controller controls the air bleeder valve of cutting out acting starting point place, tunnel immediately, some run up in disperseing the pressure-air stream concentrated starting point that enters acting tunnel right-hand member immediately that pneumatic equipment produces of launching of energy accumulating state, cooling system sprays into water smoke and low-pressure water steam in air supply duct simultaneously, water smoke and low-pressure water steam mix vaporized expanding immediately with the high temperature air stream that launches the ejection of pneumatic equipment tail in air duct, in reducing air supply duct temperature, produce the right-hand member that acts on shuttle tractor higher than the HTHP mist of original volume several times, drive shuttle tractor to move to the left end in acting tunnel at a high speed, drive the shuttle above deck to move to terminal from runway starting point simultaneously, complete kinetic energy and speed transmission to carrier-borne aircraft by shuttle of pneumatic equipment, carrier-borne aircraft is launched to lift-off, because the engine that launches pneumatic equipment and carrier-borne aircraft all belongs to steam spraying engine, the thrust of launching pneumatic equipment is far longer than the motor power of carrier-borne aircraft, and accelerated speed and carrier-borne aircraft synchronised, can make up being short of power of various carrier-borne aircraft short takeoffs,
When shuttle tractor moves to after acting tunnel left end terminal, through the stop motion of isolation damper buffer damping, trigger runway end point sensor simultaneously, acting tunnel does the air bleeder valve of holding and closes immediately, the air bleeder valve of acting tunnel right-hand member is opened immediately, entered immediately the left end in acting tunnel by air supply duct in the pressure-air stream that returns to pneumatic equipment generation of energy accumulating state, in returning to pneumatic equipment tail spray pressure-air stream to introduce air supply duct, cooling system sprays into water smoke or water at low temperature steam, in reducing air supply duct temperature, water smoke or the water at low temperature steam vaporized expanding that is heated, the high temperature HTHP air stream that has increased expansion energy is sent into acting tunnel left end, automatically drive shuttle tractor to turn back to rapidly the right-hand member in acting tunnel, through isolation damper buffer damping, stop motion is awaited orders, triggered point sensor simultaneously, the air bleeder valve at two ends, tunnel is opened, launch pneumatic equipment and return to pneumatic equipment and enter dispersion energy accumulating state simultaneously, prepare second carrier-borne aircraft catapult-assisted take-off.
Embodiment 2
As shown in Figure 6, a kind of synchronous mode carrier-based aircraft ejector, comprises pneumatic equipment, acting tunnel, shuttle tractor and controller, sets the right-hand member in acting tunnel for launching starting point, left end, for launching terminal, is made pneumatic equipment with tandem type shaft flow fan and is produced pressure-air stream; The air inlet of tandem type shaft flow fan is connected with the two ends in acting tunnel by air supply duct respectively with air outlet, controller control pneumatic equipment is introduced pressure-air respectively the two ends in acting tunnel, driving is arranged in the shuttle tractor high speed back and forth movement in acting tunnel, drive shuttle to launch terminal from starting point carrier-borne aircraft is launched to lift-off, then drive shuttle to automatically return to and launch starting point, realize pneumatic equipment transmission to carrier-borne aircraft by kinetic energy, specifically launch step as follows:
When carrier-borne aircraft is launched in preparation, the air bleeder valve at acting two ends, tunnel is opened, controller startup tandem type shaft flow fan runs up and makes it in energy accumulating state, the 6-9 Mach pressure-air stream that tandem type shaft flow fan produces enters the starting point in acting tunnel by air supply duct, emptying from the air bleeder valve of acting tunnel starting point, now shuttle tractor is positioned at the starting point in acting tunnel, shuttle is positioned in the right-hand member ejector starting point that laminated deck cracks, the draw bar of carrier-borne aircraft nose-gear and shuttle hook link together, and carrier-borne aircraft is in the SBR that takes off of awaiting orders;
When flight control tower sends after carrier-borne aircraft catapult-assisted take-off order, controller controls the air bleeder valve of cutting out acting two ends, tunnel immediately, flow the starting point of sending into immediately acting tunnel right-hand member in the pressure-air that disperses the tandem type shaft flow fan right-hand member running up of energy accumulating state to produce, act on the right-hand member of shuttle tractor, the negative pressure that tandem type shaft flow fan left end produces acts on the left end in acting tunnel immediately, the driving force that malleation and negative pressure produce acts on the two ends of shuttle dolly, drive shuttle tractor to move to the left end in acting tunnel at a high speed, drive the shuttle above deck to move to terminal from runway starting point simultaneously, complete kinetic energy and speed transmission to carrier-borne aircraft by shuttle of tandem type shaft flow fan, carrier-borne aircraft is launched to lift-off, because the power of tandem type shaft flow fan is far longer than the motor power of carrier-borne aircraft, and accelerated speed and carrier-borne aircraft synchronised, can make up being short of power of various carrier-borne aircraft short takeoffs,
When shuttle tractor moves to after acting tunnel left end terminal, through the stop motion of isolation damper buffer damping, trigger runway end point sensor simultaneously, the reversion that commutates under the effect of controller of tandem type shaft flow fan, pressure-air stream enters the left end generation positive high voltage in acting tunnel immediately by air supply duct, the right-hand member of shuttle dolly produces negative pressure, positive/negative-pressure stack drives shuttle tractor to turn back to rapidly the right-hand member in acting tunnel automatically, through isolation damper buffer damping, stop motion is awaited orders, triggered point sensor simultaneously, the air bleeder valve at two ends, tunnel is opened, tandem type shaft flow fan enters again energy accumulating state, prepare second carrier-borne aircraft catapult-assisted take-off.
By changing the trend of air supply duct, use fanjet or modiolus engine parallel axial fan also can realize to acting tunnel two-way ventilating and drive shuttle dolly back and forth movement in acting tunnel.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, although the present invention is had been described in detail with reference to previous embodiment, for a person skilled in the art, its technical scheme that still can record aforementioned each embodiment is modified, or part technical characterictic is wherein equal to replacement. All any amendments of doing within the spirit and principles in the present invention, be equal to and replace or improvement etc., within all should being included in protection scope of the present invention.
Except the disclosed technical characterictic of description of the present invention, be the known technology of those skilled in the art.
Claims (7)
1. a synchronous mode carrier-based aircraft ejector, is characterized in that comprising that pneumatic equipment, acting tunnel, shuttle leadDraw car and controller, controller control pneumatic equipment is introduced pressure-air respectively the two ends in acting tunnel, drivesBe arranged in the shuttle tractor high speed back and forth movement in acting tunnel, drive shuttle to launch terminal by carrier-borne from starting pointMachine launches lift-off, then drives shuttle to automatically return to and launches starting point, realize pneumatic equipment by kinetic energy to carrier-borne aircraftTransmission, wherein:
Pneumatic equipment comprises and launches pneumatic equipment and return to pneumatic equipment, launches pneumatic equipment and returns to pneumatic equipmentBe separately positioned on both sides or the bottom of acting tunnel, launch pneumatic equipment by the right side in air supply duct and acting tunnelEnd launches starting point and connects, and returns to pneumatic equipment and launches terminal by air supply duct with the tunnel left end of doing work and be connected, and doesThe right-hand member in merit tunnel launches the end that starting point and left end return to terminal and is also provided with air bleeder valve, acting tunnelBoth ends are also provided with isolation damper, play point sensor and end point sensor, play point sensor and terminal sensingDevice is connected with controller by data wire, on air supply duct, be also provided with air velocity transducer, wind pressure sensor,Temperature sensor and cooling system;
The upper opening in acting tunnel is provided with laminated deck, is provided with and cracks, laminated deck in the middle of laminated deckBy installing plate, sealing strip and runway deck compound composition from bottom to top, installing plate is fixed on the top of air supply ductPortion, installing plate and runway deck relative level stretch in the middle of acting tunnel and retain and crack, and are clipped in installing plate and raceThe relative edge of two sealing strips between deck, road is bent downwardly composition lip seal configuration at the place of cracking;
The two ends of shuttle tractor are provided with the sealing plate matching with the tunnel cross sectional shape that does work, outside sealing plateSide is provided with the elastic sealing element matching with the tunnel cross sectional shape that does work, the center top setting of shuttle tractorHave shuttle connecting plate, the top margin of shuttle connecting plate protrudes upward with shuttle and is connected through the slotting in middle of laminated deckTogether, the upper and lower and both sides of shuttle tractor are also provided with directive wheel, the both sides in directive wheel and acting tunnel withRoll and connect in bottom, the directive wheel at top rolls and is connected with installing plate bottom;
Controller is made up of remote controller, single-chip microcomputer, and remote controller receives end point sensor, starting point by single-chip microcomputerThe work ginseng of sensor, air velocity transducer, temperature sensor, wind pressure sensor, pneumatic equipment power controllerNumber, and control pressure-air supply equipment power stage, control the switching of reversal valve, air bleeder valve and coldBut the work of system, that realizes shuttle launches, returns and launch power stage.
2. a kind of synchronous mode carrier-based aircraft ejector according to claim 1 is characterized in that, pneumatic equipment isElectric motor driven tandem type shaft flow fan, the engine-driven axial flow blower of modiolus or fanjet.
3. a kind of synchronous mode carrier-based aircraft ejector according to claim 1, is characterized in that terminal sensingDevice, a point sensor are infrared photoelectric sensor or magnetic induction sensor.
4. a kind of synchronous mode carrier-based aircraft ejector according to claim 1, is characterized in that pneumatic equipmentPower controller is the change of throttle control or the tandem Axial-flow fan motor of fanjet, modiolus engineFrequently device.
5. a kind of synchronous mode carrier-based aircraft ejector according to claim 1, isolation damper is spring, gasThe complex of one or more in cylinder pressure or elastic sponge mattress.
6. a work method is concentrated in the dispersion accumulation of energy of synchronous mode carrier-based aircraft ejector, it is characterized in that, comprises windMoving equipment, acting tunnel, shuttle tractor and controller, controller control pneumatic equipment by pressure-air respectivelyIntroduce the two ends in acting tunnel, drive the shuttle tractor high speed back and forth movement that is arranged in acting tunnel, drive slidingShuttle launches terminal from starting point carrier-borne aircraft is launched to lift-off, then drives shuttle to automatically return to and launches starting point, realExisting pneumatic equipment transmission to carrier-borne aircraft by kinetic energy, specifically launch step as follows:
Set the right-hand member in acting tunnel for launching starting point, left end is for launching terminal, with aviation turbofan engine or snailShaft generator driving shaft flow fan is made pneumatic equipment and is produced the absolutely empty air-flow of high pressure;
When carrier-borne aircraft is launched in preparation, the air bleeder valve at acting two ends, tunnel is opened, and controller starts some bulletsPenetrating pneumatic equipment runs up and makes it simultaneously in disperseing energy accumulating state, turbojet engine or modiolus engine operationThe air-flow of ejection, not only has high flow capacity and high blast, also has 2000 DEG C of above high temperature, and high temperature gas flow will sendWind pipeline adds thermosetting heat storage boiler, and the pressure-air stream that launches pneumatic equipment generation is entered and done by air supply ductThe starting point in merit tunnel, emptying from the air bleeder valve of acting tunnel starting point, now shuttle tractor is positioned at acting tunnelThe starting point in road, shuttle is positioned at the right-hand member that laminated deck cracks and launches in starting point, the draw bar of carrier-borne aircraft nose-gearLink together with shuttle hook, carrier-borne aircraft is in the SBR that takes off of awaiting orders;
When flight control tower sends after carrier-borne aircraft catapult-assisted take-off order, controller controls immediately and cuts out acting tunnel starting pointThe air bleeder valve at place, some run up in disperseing the high pressure that pneumatic equipment produces that launches of energy accumulating stateAir stream is concentrated the starting point that enters acting tunnel right-hand member immediately, and cooling system sprays into water smoke in air supply duct simultaneouslyWith low-pressure water steam, water smoke and low-pressure water steam in air duct with the high temperature sky that launches pneumatic equipment tail ejectionAir-flow mixes vaporized expanding immediately, in reducing air supply duct temperature, produces higher than original volume several timesHTHP mist acts on the right-hand member of shuttle tractor, drives shuttle tractor at a high speed to acting tunnelLeft end moves, and drives the shuttle above deck to move to terminal from runway starting point simultaneously, completes the moving of pneumatic equipmentCan the transmission to carrier-borne aircraft by shuttle with speed, carrier-borne aircraft is launched to lift-off, owing to launching pneumatic equipment and warshipThe engine of carrier aircraft all belongs to steam spraying engine, and the thrust of launching pneumatic equipment is far longer than the engine of carrier-borne aircraftThrust, and accelerated speed and carrier-borne aircraft synchronised, can make up being short of power of various carrier-borne aircraft short takeoffs;
When shuttle tractor moves to after acting tunnel left end terminal, stop fortune through isolation damper buffer dampingMoving, trigger runway end point sensor simultaneously, acting tunnel does the air bleeder valve of holding and closes immediately, acting tunnelThe air bleeder valve of right-hand member is opened immediately, the pressure-air that pneumatic equipment produces that returns in energy accumulating stateStream enters the left end in acting tunnel immediately by air supply duct, returning to the introducing of pneumatic equipment tail spray pressure-air streamWhen air supply duct, cooling system sprays into water smoke or water at low temperature steam, in reducing air supply duct temperature,Water smoke or the water at low temperature steam vaporized expanding that is heated, the high temperature HTHP air stream that has increased expansion energy is sent into actingTunnel left end, drives shuttle tractor to turn back to rapidly the right-hand member in acting tunnel automatically, delays through isolation damperRush damping stop motion and await orders, triggered point sensor simultaneously, the air bleeder valve at two ends, tunnel is opened to bulletPenetrate pneumatic equipment and return to pneumatic equipment and enter dispersion energy accumulating state simultaneously, preparing second carrier-borne aircraft catapult-assisted take-off.
7. a work method is concentrated in the dispersion accumulation of energy of synchronous mode carrier-based aircraft ejector, it is characterized in that, comprises windMoving equipment, acting tunnel, shuttle tractor and controller, set the right-hand member in acting tunnel for launching starting point, a left sideEnd, for launching terminal, is made pneumatic equipment with tandem type shaft flow fan and is produced pressure-air stream; Tandem type shaft flow fanAir inlet and air outlet be connected with the two ends in acting tunnel by air supply duct respectively, controller control is pneumatic establishesStandby two ends of pressure-air being introduced respectively to acting tunnel, drive the shuttle tractor high speed that is arranged in acting tunnelBack and forth movement, drives shuttle to launch terminal from starting point carrier-borne aircraft is launched to lift-off, then drives shuttle automatically to returnGet back to and launch starting point, realize pneumatic equipment transmission to carrier-borne aircraft by kinetic energy, specifically launch step as follows:
When carrier-borne aircraft is launched in preparation, the air bleeder valve at acting two ends, tunnel is opened, and controller starts tandem type shaftFlow fan runs up and makes it in energy accumulating state, the 6-9 Mach pressure-air stream that tandem type shaft flow fan producesEnter the starting point in acting tunnel by air supply duct, emptying from the air bleeder valve of acting tunnel starting point, now slidingShuttle tractor is positioned at the starting point in acting tunnel, and shuttle is positioned in the right-hand member ejector starting point that laminated deck cracks, warshipThe draw bar of carrier aircraft nose-gear and shuttle hook link together, and carrier-borne aircraft is in the SBR that takes off of awaiting orders;
When flight control tower sends after carrier-borne aircraft catapult-assisted take-off order, controller controls immediately and cuts out acting two ends, tunnelAir bleeder valve, in disperse energy accumulating state the tandem type shaft flow fan right-hand member running up produce high pressureAir stream is sent into the starting point of acting tunnel right-hand member immediately, acts on the right-hand member of shuttle tractor, tandem axial flow windThe negative pressure that machine left end produces acts on the left end in acting tunnel immediately, and the driving force that malleation and negative pressure produce acts onThe two ends of shuttle dolly, drive shuttle tractor to move to the left end in acting tunnel at a high speed, drive on deck simultaneouslyThe shuttle of face moves to terminal from runway starting point, complete the kinetic energy of tandem type shaft flow fan and speed by shuttle toThe transmission of carrier-borne aircraft, launches lift-off by carrier-borne aircraft, because the power of tandem type shaft flow fan is far longer than carrier-borne aircraftMotor power, and accelerated speed and carrier-borne aircraft synchronised, can make up the moving of various carrier-borne aircraft short takeoffsPower deficiency;
When shuttle tractor moves to after acting tunnel left end terminal, stop fortune through isolation damper buffer dampingMoving, trigger runway end point sensor, the reversion that commutates of tandem type shaft flow fan, height under the effect of controller simultaneouslyPress air stream to enter immediately the left end generation positive high voltage in acting tunnel by air supply duct, the right-hand member of shuttle dollyProduce negative pressure, the automatic right-hand member that drives shuttle tractor to turn back to rapidly acting tunnel of positive/negative-pressure stack, through slowRush the stop motion of damper buffer damping and await orders, triggered point sensor, by the air venting at two ends, tunnel simultaneouslyValve is opened, and tandem type shaft flow fan enters again energy accumulating state, prepares second carrier-borne aircraft catapult-assisted take-off.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111762334A (en) * | 2020-07-02 | 2020-10-13 | 李广 | Storage-type steam catapult with direction-adjusting ejection element |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6007022A (en) * | 1996-11-08 | 1999-12-28 | Newport News Shipbuilding | Internal combustion catapult |
| CN102120497A (en) * | 2010-10-07 | 2011-07-13 | 朱炎炎 | Enclosed cylinder carrier aircraft steam catapult |
| CN102745333A (en) * | 2012-07-31 | 2012-10-24 | 李文铎 | Internal combustion steam boosting take-off unit of airplane |
| CN103786894A (en) * | 2012-10-31 | 2014-05-14 | 周庆才 | Slotted type steam-driven catapult for airplane short-distance take-off |
| CN103921952A (en) * | 2013-01-11 | 2014-07-16 | 李静 | C-shaped universal steam catapult |
| CN105035343A (en) * | 2015-08-13 | 2015-11-11 | 济南环太机电技术有限公司 | Vapor emission type shipboard aircraft carrier catapult |
-
2016
- 2016-01-04 CN CN201610004329.4A patent/CN105584641B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6007022A (en) * | 1996-11-08 | 1999-12-28 | Newport News Shipbuilding | Internal combustion catapult |
| CN102120497A (en) * | 2010-10-07 | 2011-07-13 | 朱炎炎 | Enclosed cylinder carrier aircraft steam catapult |
| CN102745333A (en) * | 2012-07-31 | 2012-10-24 | 李文铎 | Internal combustion steam boosting take-off unit of airplane |
| CN103786894A (en) * | 2012-10-31 | 2014-05-14 | 周庆才 | Slotted type steam-driven catapult for airplane short-distance take-off |
| CN103921952A (en) * | 2013-01-11 | 2014-07-16 | 李静 | C-shaped universal steam catapult |
| CN105035343A (en) * | 2015-08-13 | 2015-11-11 | 济南环太机电技术有限公司 | Vapor emission type shipboard aircraft carrier catapult |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111762334A (en) * | 2020-07-02 | 2020-10-13 | 李广 | Storage-type steam catapult with direction-adjusting ejection element |
| CN111762334B (en) * | 2020-07-02 | 2024-02-02 | 李广 | Reservoir type steam catapult with direction-adjusting catapulting element |
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| CN105584641B (en) | 2018-01-16 |
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Effective date of registration: 20180627 Address after: 518000 9D, C, Futian street, Futian District, Shenzhen, Guangdong. Patentee after: Shenzhen Chen Yue science and Technology Co., Ltd. Address before: 250101 room 702, Yingxiu Road, Ji'nan new and high tech Zone, Shandong, 702 Patentee before: Jinan Huantai Electromechanical Technology Co., Ltd. |