CN101934862A - High-fulcrum launch/ski-jump system for aircraft carrier - Google Patents
High-fulcrum launch/ski-jump system for aircraft carrier Download PDFInfo
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Abstract
The invention provides a high-fulcrum launch/ski-jump system for an aircraft carrier, which skillfully combines a steam ejector with a ski-jump deck together to realize double advantages. In the invention, high-fulcrum launch arms, a buffer launch assistor and a launch variable voltage design are combined with the ski-jump deck, which obviously reduces structural strength requirement and design difficulty of the aircraft carrier for catapult takeoff, increases takeoff reliability, useful load, flying range and application universality and simplifies preflight preparation operation; a slotted cylinder high-pressure water sealing system abandons a solid sealing form and simplifies steam exhaust and drainage functions of a cylinder; a high-pressure flow-control injection system and a brake reset valve simplify the design of a launch piston and a brake reset function; and a steam launch control valve set can accurately and reliably control flow rate and open-close of high-pressure steam entering the launch cylinder. A set of launch/ski-jump device on the aircraft carrier and a carrier landing arrested cable form a carrier landing arrested cable system for the aircraft carrier, which realizes unified command and control of takeoff and carrier landing and saves a damping hydraulic cylinder.
Description
Technical field
The present invention relates to the transformation of energy and the executive device of the auxiliary ship-board aircraft short field take-off on a kind of aircraft carrier.It significantly reduces structural strength, design difficulty and the aviator's of carrier-borne aircraft sense of discomfort, has increased the reliability that takes off, capacity weight, voyage and widespread popularity, has dwindled the otherness of Lu Hang aircraft and carrier-borne aircraft, has simplified the beamhouse operation before taking off.In addition, it has simplified the structure composition of carrier-borne aircraft carrier landing system.
Background technology
At present, known aircraft carrier-based aircraft help-fly mode has two kinds, promptly in the steam catapult help-fly mode of the U.S. with in the cunning of the Russia deck help-fly mode that jumps.
The known steam ejector is the very reliable and help-fly mode efficiently of a kind of process long-term practice proof.Its key component cylinder that cracks one by one is different from the structure design of traditional cylinder.Maximum problem is knife plate on the piston sealing problem during through opening.What our known aircraft carrier ejector adopted is U type sealing band form.It and cylinder seam lid combines and forms a complete hook hermetically-sealed construction in that the cylinder seam is outer, can clamp the cylinder seam in case the cylinder seam expansion when increasing of cylinder interior pressure.But the trouble part of its maximum just is to launch the junction of knife plate and U type sealing band.Owing to launch knife plate and must back down U type sealing band at interface through out-of-date, back down the back and be certain to leaked steam with sealing cutter seam, if the sealing force of U type sealing band is very big, sealing effectiveness is fine certainly, also can increase but launch the knife plate resistance, the wearing and tearing of U type sealing band are also accelerated thereupon, and the maintenance cost of ejector is big, U type sealing band is changed frequent and the replacing process very bothers again, material is required high.U type sealing band wearing and tearing are the maximum worry of puzzlement ejector, and daily attention and maintenance be suitable trouble all, though updating material always and employing new technology, so far still can not be satisfactory, U.S. army is very big to this suggestion.
Secondly, the design of known ejector shuttle close proximity to ground is forward simultaneously downwards to the direction of the pulling force of carrier-borne aircraft in a flash what launch.The energy that steam launches also is that carrier-borne aircraft is given in direct and rigid effect.Low like this Moment Point is added rigid energy and is discharged, huge test beyond doubt for nose-gear, front tyre and housing construction intensity, launch huge energy release of moment in addition, cause carrier-borne aircraft and Lu Hang aircraft that huge difference is arranged in design.This consideration also is China's aircraft in design and is converted into a difficult problem and weakness aspect the carrier-borne aircraft.
In addition, known ejection piston is big and heavy, and its profile is the spitting image of one piece of guided missile.Even hollow, but can imagine that also the weight of this piston is appreciable.Piston is very large to the usefulness influence of steam propulsion.The unavoidable place of the designing institute of the U.S. is how to allow the stopping of the piston safety darted rapidly.The seal form of its cylinder and piston and original hydro retarder Design of device have determined the volume and weight of piston.
Also have, it is a cover independent device that known aircraft carrier warship arrester wires system, and it does not have with the ejector system unitized design, thereby has increased on-board equipment weight and commanded the unitarity of controlling.
Muscovite cunning layout and the efficient that deck help-fly mode has been limited to aircraft carrier that jumps.Reduced the usefulness of taking off of carrier-borne aircraft, the variety of capacity weight and machine.
Summary of the invention
In order to obtain a kind of better and advanced help-fly effect, and can solve the technical matters that known help-fly mode exists.The present invention proposes the aircraft carrier that is based upon on a plurality of innovative designs of cover and launch/slide the system of jumping.
One, the aircraft carrier high pivot point launches/slides the characteristics of the system of jumping
1, this aircraft carrier high pivot point launches/slides the unitized design scheme that the system of jumping is a steam catapult and the sliding deck help-fly that jumps.It has the efficient booster action of catapult-assisted take-off, also has the help-fly effect that upwarps the sliding deck that jumps simultaneously.Simultaneously, this scheme has solved steam catapult and has slided some technological deficiencies that the deck help-fly that jumps exists separately.
2, this aircraft carrier high pivot point launches/slides the otherness that Lu Hang aircraft and carrier-borne aircraft have been dwindled in the design of the system of jumping.High pivot point ejection arm and buffering help the design of ereisma can make the structural strength (particularly nose-gear structural strength) of carrier-borne aircraft require significantly to reduce.Reduce the design difficulty of carrier-borne aircraft and increase its reliability that takes off, capacity weight and voyage.Launch protrudingly and launch recessed design, substituted and launched shuttle, launch pull bar, parts such as holdback pull bar.Significantly reduced the design difficulty of carrier-borne aircraft nose-gear.Simplified the beamhouse operation before taking off.
3, this aircraft carrier high pivot point launches/slides the system's of jumping cylinder that cracks and adopts the design of high pressure water sealing system, has abandoned the sealed solid form.The design of high pressure jet nozzle assembly and flow control valve makes sealing function and launches the ingenious fusion of cylinder.By calculating, high pressure water leak free bearing pressure launches delivery pressure greater than known aircraft carrier steam, and the cylinder steam that can very desirable accomplishing cracks does not leak, and will effectively improve and launch cylinder usefulness.High voltage-controlled stream injection system design has realized the localized ejection function of quick stepping injection of high pressure water leak free and any part, has solved the brake reset issues of ejection piston, thereby reduces structure of piston complexity and weight.And can solve piston, launch friction drag sealing effectiveness and frictional loss between knife plate and cylinder.Improve ejector life-span and reliability.In addition, the steam discharge of cylinder, the design of drain function have been simplified in the design of high voltage-controlled stream injection system.In the different phase of cylinder operation, residue vapor and water can both be autotelic from the cylinder that stops the to spray earial drainage that cracks.
4, this aircraft carrier high pivot point launches/slides the system that jumps and adopts and to launch the transformation design, promptly allows to launch pressure and adjusts according to the variation of actually launching needs, launching load.The widespread popularity that this helps launching is enriched the kind of carrier-borne aircraft.Steam launch control cock group design can be accurate and failure-free control high pressure steam and enter and launch cylinder.This valve supports the transformation of ejection system to use.
5, to launch/slide the brake reset function of the system of jumping be to be realized by the vapour of taking all factors into consideration, the hydraulic pressure damping form that contracts to this aircraft carrier high pivot point.The brake valve that resets can accurately be controlled the brake homing action of high pressure steam to piston.
6, utilize a wherein cover high pivot point on the aircraft carrier to launch/slide the device that jumps and combine with the warship arrester wires, the composition aircraft carrier warship arrester wires system.But the buffering that the strength transmission of passing to arrester wires when carrier-borne aircraft is landed uses for pressure regulation helps ereisma and steam to launch cylinder.Like this, not only realized taking off and the unified control commander of warship, also improved usage ratio of equipment on the warship, and saved the damping liquid cylinder pressure.
Two, the aircraft carrier high pivot point launches/slides the operational process of the system of jumping
Fig. 2 ejection status scheme drawing
1, launches the new field of technical activity
Carrier-borne aircraft is located in the ejection seat, at this moment, launches protruding stuckly by holdback, and piston can not advance.Steam launch on the control cock group to launch the mould bottom valve crack, launch open and close valve and open, launch cylinder and begin slow inflation.Help in buffering under the regulating control of ereisma mould bottom valve, part steam injects buffering by air guide channel to be helped ereisma and launches plunger cylinder on protruding, plunger rod jack-up upwards under gas pressure, insert launching of carrier-borne aircraft nose-gear recessed in.Buffering helps the ereisma piston rod to be in punctured position under gas pressure.The high pressure water sealing is not sprayed as yet.
2, launch the off stage
When carrier-borne aircraft takes off, put into high gear, the mould bottom valve that launches that steam launches on the control cock group is adjusted to the required aperture of launching of target ship carrier aircraft, ejection command person when launching optimum regime, unclamp be stuck on the holdback launch protruding.The high pressure water sealing is sprayed with piston steps.To acceleration, buffering helps the gas in the ereisma to compress afterwards earlier and rebounds from static, forms and cushions earlier the effect that afterwards helps bullet.Huge steam energy reaches the accelerated take-off purpose by launching the protruding carrier-borne aircraft that sends to.The cylinder back cavity (steam side) that cracks of this moment is a complete fully enclosed pressure chamber under the high pressure water sealing function, and ante-chamber is an open state.When launch protruding pushing away carrier-borne aircraft and entering the ramp after, head begins to raise up under the support of front-wheel, level is advanced launches and protrudingly extracts until disengaging gradually from launching of aircraft is recessed.It is protruding stealthy to launching under the deck of upwarping fast to lose launching of load, and near the brake section.And the aircraft of this moment will rise to the sky.
3, piston end brake/reseting stage
Near the ejector end time, the steam ceiling capacity has passed to carrier-borne aircraft takes off it.At this moment, launch the control cock group and close, the sealing of cylinder back cavity high pressure water stops to spray, and cylinder cracks and locates to begin to discharge remaining steam.And the sealing of brake section high pressure water is sprayed, and the brake valve that resets is in closed condition, and the cylinder ante-chamber forms the pressure chamber that carbonated drink is mixed.The impulse force that gas compression counteracting is not fallen is remedied by terminal water resistance Buddhist nun.When brake section pressure was lower than high-pressure steam pressure, the brake valve that resets was opened, and high pressure steam enters cylinder, and piston helps ereisma and launches protruding the beginning together with buffering and returns.
4, the ejection piston playback stage
In the ejection piston return course, the high pressure water sealing can be adopted lower slightly high pressure water jets emission mode.The brake valve group that resets begins throttling and closing gradually.In end of reset, the sealing of piston ante-chamber high pressure water stops to spray, and the of short duration low-pressure fuel injection of piston back cavity produces braking effect, until piston reset.One is launched end cycle.
Three, the aircraft carrier high pivot point launches/slides the formation of the system of jumping
The formation of aircraft carrier steam ejection system is very huge.A non-people's power can all design and realize.Only set forth in the technical program relating to the part that this aircraft carrier high pivot point launched/slided the multinomial technology innovation of the system of jumping.
Each group aircraft carrier high pivot point launches/slides the system of jumping and launches the cylinder that cracks by two steam of arrangement in parallel and form, and is installed in and launches underdeck launching in the groove.It is one that every steam launches that the cylinder that cracks is connected and fixed with form of flanges by some joint individual cylinders, and two ends are equipped with front end cover and rear side housing respectively.Be installed in continuous, symmetrical manner by several high pressure jet nozzle assembly unit at the complete high pressure jet nozzle assembly on the cylinder that cracks and crack about cylinder between two sides of a ship.
The nozzle flow control valve is installed in and cracks about cylinder in two side of a ship bodies, couples together by high pressure hose and the high pressure water collector that is arranged in parallel with the cylinder that cracks.The cylinder high pressure water sealing system that cracks is made of high-pressure water prmp room system and high voltage-controlled stream injection system two parts.Under the control of the voltage-controlled stream injection system of height, realize cracking the cylinder sealing function from the high pressure water that the high-pressure water prmp room system transports.
The design of cylinder high pressure water sealing system of cracking has solved traditional steam and has launched cylinder crack the sealed solid that the place adopts and the defective of seal cover cap.The high pressure jet nozzle assembly can be realized the stepping injection along with advancing rapidly of ejection piston.In the cylinder of the ejection piston process position of cracking, the high pressure water of high pressure jet nozzle assembly ejection at piston, launch between the tolerance clearance of knife plate and cylinder inner wall, nozzle wear plate and form pressure water-stop and positive lubrication effect; And the cylinder that piston has passed through the position of cracking, the high pressure water curtain of high pressure jet nozzle assembly symmetry ejection forms complete energy sealing surface, guarantees that the steam in the cylinder does not leak; And the piston cylinder of the process position of cracking not, the high pressure jet nozzle assembly does not spray, and the air free dredging flow in the cylinder guarantees that to greatest extent piston is not subjected to advance resistance; In the brake reset section, the high pressure jet nozzle assembly can be realized boosting jet, guarantees to realize the carbonated drink of ejection piston is mixed the brake reset function in this section cylinder.Also therefore, the design of ejection piston has had huge simplified design on structure and weight.In addition, launching the groove bottom is Open architecture, and its spatial design satisfies the harmless drainage of residue vapor and water.
The aircraft carrier high pivot point launches/slides the system of jumping and launches the control cock group by steam the rear side housing position that steam pipe and steam launch the cylinder that cracks is coupled together, control pressure and the flow that steam enters cylinder in order to accurate and failure-free, the strength of steam will act on the interior ejection piston of the cylinder that cracks.Ejection piston stretches out by cracking from cylinder launches knife plate and helps the ereisma support to be fixed together in order to be connected the buffering that two groups of steam launch the cylinder that cracks.Buffering helps the ereisma support to help ereisma to be connected the top buffering by jointed shaft.Help the piston rod of ereisma and the sunken bottom portion of launching on the coaxial line to fix by buffering.Launch the cooperation of sunken bottom portion by guide rail wheel and guide rail make launch protruding can only be along launching the stable slip of the direction of cracking on the deck.Launch and protrudingly crack and protrude upward a higher position, be equipped with an oval deep hole at the centre bit that launches protruding top of thickening gradually and use as the plunger cylinder tube with forward leaning angle from launching the deck.In adorn an ovallized column stopper rod, the top of plunger rod is that a circular columns is prominent.Height when plunger rod is in punctured position does not hinder carrier-borne aircraft to enter into the ejection seat.When plunger rod stretches out the circular projection in top insert be fixed on launching of aircraft nose-gear and fuselage bonded assembly root recessed in.A carrier-borne aircraft front-wheel bumping post is arranged launching the rear end that protrudes out the position, deck, in order to realize carrier-borne aircraft when entering the ejection seat the location and prevent nose-gear knock launch protruding.Help ereisma and launch in the connection structure that convexes in ejection piston and buffering, be provided with an air guide channel.Very little a part of steam energy that injection is cracked in the cylinder will be controlled its flow and be injected into buffering by air guide channel and help ereisma and launch plunger cylinder on protruding by being installed in small steam mould bottom valve that buffering helps ereisma end cap position, insert and will launch recessed and cushion the realization that the buffering that helps ereisma to set according to different carrier-borne aircraft load helps bouncing function thereby guarantee to launch the projection stopper rod.The steam energy of the overwhelming majority will be by ejection piston, launch knife plate, buffering helps ereisma support, buffering to help ereisma and launch the protruding energy delivery mechanisms that is built into jointly and send carrier-borne aircraft to, thereby realizes the catapult-assisted take-off purpose.
The aircraft carrier high pivot point launches/slides the deck of launching of the system of jumping and launches the deck by level and have the cunning that necessarily the upwarps radian deck that jumps and constitute.Launch groove lid and curved surface by some amalgamations plane together and launch the groove lid and combine, and launch the deck and crack launching on the line of centers of protruding process formation.Have one with launching the sliding-rail groove that the cylinder that cracks is arranged in parallel launching the downside that cracks, the cooperation by guide rail wheel and guide rail is in order to stabilized ejection protruding ejection trjectory and transmission of torque.Below in conjunction with drawings and Examples the utility model is further specified:
Fig. 1. aircraft carrier launches/slides the systematic schematic diagram that jumps
Aircraft carrier launch/slide the system of jumping mainly by 1 upwarp the sliding deck that jumps, 2 planes launch deck, 3 launch protruding, 4 launch recessed, 5 guide rails, 6 deflecting plates, 7 holdbacks, 8 and launch cylinder, 9 bufferings and help ereisma, 10 ejection pistons, 11 high pressure nozzle fabricate blocks, 12 nozzle flow control valves, 13 steams to launch control cock group, 14 brakes reset valve, 15 high pressure waters sealing control streaming system, 16 high-pressure water prmp room systems, 17 steam gas tanks, 18 steam boilers
High pressure jet nozzle assembly Fig. 3.
The complete high pressure jet nozzle combination on the cylinder of cracking is installed in continuous, symmetrical manner by several high pressure jet nozzle assembly unit cracks about cylinder between two sides of a ship.
The high pressure jet nozzle assembly is structurally mainly by forming with the lower part: side nozzle wear plate on 1 nozzle body, 2 fan-shaped chambeies, 3O type circle, 4 linear sealings, the 5 times side nozzle wear plates, 6
1 nozzle body
The difference of the acute purposes of root, nozzle body can be designed to monomer or fabricate block form respectively.For different application conditions and applied environment, can select unlike material and processing, processing means to be achieved.
Consider that based on this ejection system nozzle body adopts the design of fabricate block form, the length of fabricate block depends on the length of cylinder segmentation.Compartment on the fabricate block between side by side the fan-shaped chamber shortens satisfying on the basis of requirement of strength as far as possible.Be connected so that the water curtain that guarantees ejection is compact.
Nozzle body (comprising other equipment and parts) should adopt withstanding corrosion (seawater), wear-resisting, high temperature resistant and pressure-proof alloy steel forging material.
The tapped bore at the nozzle back side is used for the fastening of nozzle and cylinder band.For consideration easy to maintenance, nozzle assembly and cylinder band horizontally connect.Can realize like this light maintenance of high pressure water leak free is handled, improve its combat capabilities.
2 fan-shaped chambeies
This structure is the maximum characteristics and the maximum technological breakthrough point of this nozzle.It is fan-shaped that all to be fluid just form after the spray orifice ejection tradition fan nozzle.Sectorial area is directly proportional with jet length.Can't avoid between adjacent nozzle, forming the triangle vacancy.
The present invention forms fan-shaped chamber in nozzle chamber.Cavity geometry be from the circle of nozzle rear end (or oval, square) hole to the elongated slit-like hole of spray nozzle front end excessively.For satisfying the requirement of injection pressure and flow, circular (or oval, square) hole sectional area is greater than the sectional area (concrete ratio can design according to the difference difference of purposes) of elongated slit-like hole.
According to the difference of purposes, the elongated slit-like hole of front end can be linear, circular arc or irregularly shaped.For understanding and the improved uncertainty of scheme to ejection system.The front end elongate slot hole of this ejection system scheme is designed with linear temporarily.
This fan-shaped chamber is to make fluid just be fan-shaped before not spraying.
Side nozzle wear plate on 5 times side nozzle wear plates and 6
The elongated slit-like hole of spray nozzle front end does not directly use (unless being used for middle low-pressure system design) as spray orifice.Spray nozzle front end is embedded with the spray orifice that high-abrasive material constitutes.
The pressure of steam ejection system high-pressure water jet may need very high.Therefore, be necessary to use good high-abrasive material or process of surface treatment.As use the carbon tungsten alloy, or the material of surface carbon tungsten spraying is used to process down side nozzle wear plate and last side nozzle wear plate.
Last side nozzle wear plate and following side nozzle wear plate have three functions.The one, the upper limb of formation spray orifice; The 2nd, when launch knife plate by the time play the effect of bearing shell; The 3rd, avoid launching knife plate, mechanical wear that high pressure water produces and the cavitation that might form causes direct infringement to nozzle body and cylinder band.
The length of last side nozzle wear plate and following side nozzle wear plate depends on the length of cylinder segmentation.
3O type circle and 4 linear sealings
Prevent the seepage of high pressure water and to the infringement of parts.Same linear leak free length depends on the length of cylinder segmentation.
The high pressure jet nozzle assembly can be realized the stepping injection along with advancing rapidly of ejection piston.In the cylinder of the ejection piston process position of cracking, the high pressure water of high pressure jet nozzle assembly ejection at piston, launch between the tolerance clearance of knife plate and cylinder inner wall, nozzle wear plate and form pressure water-stop and positive lubrication effect; And the cylinder that piston has passed through the position of cracking, the high pressure water curtain of high pressure jet nozzle assembly symmetry ejection forms complete energy sealing surface, guarantees that the steam in the cylinder does not leak; And the piston cylinder of the process position of cracking not, the high pressure jet nozzle assembly does not spray, and the air free dredging flow in the cylinder guarantees that to greatest extent piston is not subjected to advance resistance; In the brake reset section, the high pressure jet nozzle assembly can be realized boosting jet, guarantees to realize the carbonated drink of ejection piston is mixed the brake reset function in this section cylinder.The design of cylinder high pressure water sealing system of cracking has solved traditional steam and has launched cylinder crack the sealed solid that the place adopts and the defective of seal cover cap.Also therefore, the design of ejection piston has had huge simplified design on structure and weight.
High pressure water sealing control streaming system Fig. 4, Fig. 6 (1, cylinder band winds up 2, nozzle assembly 3, spray and splash down water 5, high pressure water arm after water curtain 4, the air exercise)
One, high pressure water sealing control streaming system principle of design---hydraulic balance design
The control streaming system why can the generation effect, and can realize flow control function under multiple pressure, and is closely related with the Design Mechanism of hydraulic balance.In this system, control the high pressure water itself that control effort that whether each nozzle spray comes from the high pressure water sealing system.Sealing system pressure is much, and control effort is just much.
1, launching the new field of technical activity, guarantee to fill with high pressure water in the high pressure water sealing system pipeline, but the control nozzle assembly is not spraying.
2, launching the off stage, control is launched the whole nozzle assemblies of section and is sprayed, and guarantees that the sealing of piston rear side (launching steam side) high pressure water curtain formation is effectively powerful.
3, entering the brake stage, the whole section nozzle assembly that brakes of opening, and brake section nozzle assembly is a boosting jet.
4, entering the piston reset stage, the control nozzle assembly move with piston reset and stepping spray, but injection pressure can suitably reduce under the condition of steam pressure that guarantees to reset.
5, entering the terminal stage of piston reset, the whole reset section nozzle assembly of opening is until piston reset.Controlling whole nozzle assemblies at last stops to spray.
Two, the formation of high pressure water sealing control streaming system
High pressure water sealing control streaming system is made up of electricity-gas guide 23 logical high pressure change-over valves, nozzle flow control valve, high pressure water hydraulic power line, high pressure water bypass line.
1, electricity-2 3 logical high pressure change-over valves of gas guide
All high pressure change-over valves are installed on several total vavle shelves.Be used to control the state that the stream high pressure water is realized pressurize or pressure release.DC24V solenoid control 6-10bar pneumatic piston drives 23 logical valve core movements.
2, high pressure water hydraulic power line
Be connected between each flow control valve and the corresponding high pressure change-over valve.Be used to control the state of flow control valve.
3, high pressure water bypass line
Be connected between high pressure sealing system trunk line and the total vavle shelf of control stream.Be used for providing high pressure water with high pressure sealing system equipressure to the control streaming system.
4, nozzle flow control valve figure .5
This valve is installed in the cylinder port and starboard body of each nozzle rear end.Be used for the switching of nozzle, principle of work is the hydraulic balance principle.Valve body mainly is made of: 1 valve pocket, 2 springs, 3 spools, 4 valve seats, 5 control stream interfaces, 6 sealings.
Three, high-pressure water prmp room systematic schematic diagram Fig. 7
The high-pressure water prmp room system is the energy source of high pressure water sealing system.Pumping plant will provide sufficient pressure and flow for the sealing position.Therefore, the design of pumping plant is important too.The high-pressure water prmp room system is mainly by forming with the lower part:
1, feeds water pump
Assurance system water abundance, and certain hello the hydraulic pressure of water supply maintenance that enters high pressure pump.Or cooperate the current stabilization jar together to use.If the front end pipe network can ensure, but simplified design.
2, self-cleaning filter and pipeline y-type filter
Guarantee the cleaning of system water.Reduce the wearing and tearing of high-tension apparatus, nozzle and pipe network.If the front end pipe network can ensure, but simplified design.
3, high pressure pump
Mainly be divided into two kinds: high-pressure plunger pump and multistage centrifugal pump.Concrete selection need be calculated by spout part and realize that needed pressure of high pressure sealing effect and flow decide.Should adopt variable-frequency control technique for the purpose energy-conservation and operation of multiple pressure power.
4, circulation valve
When the high pressure sealing system does not spray, guarantee the running state of high pressure pump.
5, pressure switch
6, flow counter
7, liquidometer
8, pressure sensor
9, compression indicator
10, high pressure, low pressure valve
11, high pressure, low pressure pipeline and pipe fitting
12, electrical equipment
13, PLC control system
High pressure water system on the aircraft carrier should be the water purification medium system.Like this, system especially the wearing and tearing of spout part will be very limited.If of course, consider obviously to solve the wear problem of ejection system and high pressure sealing system like this with the feasibility of high-flash emulsion as sealing medium.
The cylinder unit of cracking Fig. 8
Based on the design of high pressure water sealing system, I will comprise that a plurality of parts of the cylinder that cracks have proposed the design suggestion of oneself.Cylinder band, nozzle assembly, front end cover, rear side housing that the cylinder that cracks is combined into by segmentation are formed.
1, cylinder band and nozzle assembly
For high pressure water sealing being sprayed and control part does not take the slot space that launches on the aircraft carrier separately, the design takes nozzle combination and flow control valve and cylinder band are combined the design-calculated method, to form the most rational cylinder crack sealing effectiveness, theory of structure effect and space utilization effect.
The design has cancelled the design of hook-type seal cover cap.Therefore, in ejection process cylinder crack the place the easiest deforming.Therefore, cylinder band is taked the eccentric design of inside and outside circle.Make the thickness of cylinder band form down thick approach excessive of going up.Form the powerful supporting role that countercylinder cracks and locates.
The width that cracks that the port and starboard that cylinder cracks has bigger scantling of structure and formation is also very big.Being convenient to nozzle assembly like this is separately fixed on the inner plane of two sides of a ship with symmetric form.The developed width that cylinder cracks is the slit between the nozzle assembly.
The nozzle assembly and two sides of a ship are horizontal fixed.Be convenient to the dismounting of nozzle assembly like this.Can realize like this light maintenance of high pressure water leak free is handled, improve its combat capabilities.
High pressure water sealing injection control valve is directly installed in the port and starboard body that cylinder cracks.So both save the space, satisfied bearing requirements again.High-Pressure Water is direct contact side of a ship body not, therefore, can not cause the direct infringement of countercylinder body.
There is a thicker high-pressure water pipeline of internal diameter to pass through the head and the tail of whole steam catapult in the bottom of cylinder band.This pipeline is connected with each injection control valve on the cylinder port and starboard body by the high pressure hose that is symmetrically distributed.Thereby guarantee the high service of spout part and the nozzle injection pressure equilibrium on the assurance cylinder port and starboard body.
Equally, entire cylinder adopts segment design, manufacturing, is formed by connecting at last.It is to be fixed on the cylinder rail that launches tank by base to fuse that the interface design has flange connection and seal groove, whole cylinder.This many sections connect air cylinder structures and help reducing and produce, the cost of transportation and maintenance, and can deal with on the whole thermal deformation more neatly.The length of single-nozzle fabricate block and the section length of cylinder coincide.
2, rear side housing
Rear side housing can play the effect of booster cavity for the design of heavy wall conical hollow in the initial period of launching.Tail end is that a heavy caliber admission port is connected with induction tract.
3, front end cover
Front end cover is terminal Cushioning Design, when launching end, cooperates the pressurized air and the water that make in the cylinder to form mixing braking action (this function will be introduced separately) with the pyramidal projections of piston.Tail end and brake the valve group that resets be connected.
4, one group of ejector system launches cylinder by two and forms side by side.
The constructional drawing of piston and brake function Fig. 9 piston and brake section
Why, I will brake and plunger designs elaborations of putting together, be to notice the design of U.S.'s ejection piston because of me, and its profile is the spitting image of one piece of guided missile.Even what describe to him is hollow, but can imagine that also the weight of this piston is appreciable.Piston is very large to the usefulness influence of steam propulsion.The unavoidable place of the designing institute of the U.S. is how to allow the stopping of the piston safety darted rapidly.In technical application, I have certain understanding to the structure of fast suction casig.In addition, I am based on the design thinking of high pressure water leak free, propose a kind of new thinking at this and design piston and brake function in this ejection system.
The formation of piston
1, piston body
Piston body comprises piston, launches knife plate, wear plate and awl cylindricality lordosis.Integral body should adopt casting forging form, is hollow design in the piston.Preferably adopt titanium alloy material.Like this, when guaranteeing its requirement of strength, expendable weight to greatest extent again.Help the help-fly usefulness aspect that energy that steam launches is applied to carrier-borne aircraft greatly like this.
2, hermetically-sealed construction
I have no way of understanding more detailed ejector data.Volume is so huge launches cylinder, its steam energy, cylinder diameter, surface working precision, free-running fit, tolerance fit, piston movement speed, heat distortion amount or the like.My thought long on, can not determine known to me leakproofing material which be more suitable for.
But I have a Seal Design design with matching.The sealing of piston is realized by the Y type high pressure water sealing function that is sealed and matched.Promptly launch knife plate the high pressure water sealing section of process, the high pressure water of the overwhelming majority will be injected in the gap that forms between gap that piston and cylinder inner wall form and wear plate that launches the knife plate both sides and the nozzle wear plate, thus formation positive lubrication and water-stop usefulness; The seal ring of both sides adopts Y type seal form, can play the swelling effect;
High pressure water system on the aircraft carrier should be the water purification medium system.Like this, the wearing and tearing of ejection system will be very limited.If of course, consider obviously to solve the wear problem of ejection system and high pressure sealing system like this with the feasibility of high-flash emulsion as sealing medium.
Brake function
Entering brake during the stage, whole opening brake section nozzle assembly, and brake section nozzle assembly is boosting jet, will form the compression of the interior air of brake section like this.Close ejection valve simultaneously, stop steam and inject, the sealing of cylinder back cavity (steam side) high pressure water stops to spray remaining carbonated drink earial drainage.
The length (cylinder volume) of brake section determines that offsetting the piston-advance force of inertia by air compression application force in the brake section is that benchmark calculates gained.
For the piston-advance force of inertia that can't accurately balance out, will form terminal buffering (the awl cylindricality lordosis on the piston forms the throttling deceleration effort to water) at the brake tail end by the water that sprays into the brake section.
If the length (cylinder volume) of brake section is long, influence is effectively launched the effect of section or exceed the installation dimension that ejector allows on aircraft carrier.Then air compression effect and terminal water buffer action can be taken all factors into consideration and design, reach best brake ratio.
Buffering helps ereisma Figure 10
As a military fan, I notice that many articles, forum mention the difficulty of our country's (also having the Soviet Union) development carrier-borne aircraft and the difficulty of development aircraft carrier ejector.One of them important difficult point is that the Intensity Design and the ejector of undercarriage launching the restriction of energy controlling party in the face of the carrier-borne aircraft overall construction intensity.Ejector is a device that has huge energy, to it accurately control and allow its balmy and bracing, be a global difficult problem.
Based on high pressure water leak free design with to the redesign of brake function, I have proposed the design of piston weight reducing design-calculated.At this, my a new idea is exactly piston to be subtracted the weight of getting off use, at piston and launch and set up a new device between protruding---and buffering helps ereisma.
1, buffering helps the effect of ereisma
It is equivalent to secondary and launches cylinder.For forged steel or titanium alloy material are made.
Launching the off starting stage, having a small amount of high pressure steam and enter buffering by conduit and help the ereisma cylinder, ejection piston starts in a flash, cushions and helps ereisma will play the air damping effect.From static to acceleration, carrier-borne aircraft can be with a huge power by launching the protruding piston rod that buffering helps ereisma of passing to, and piston rod is drawn out, and the air in the cylinder barrel is compressed, when the air compression antagonistic force when launching load balance, launch protruding drive carrier-borne aircraft and travel forward.To lag behind the run up time of carrier-borne aircraft in this process.Especially toggle speed will form velocity contrast with piston velocity, prolong the time of carrier-borne aircraft from static to motion.Like this, will reduce the restriction of ejector to undercarriage and strength of aircraft, and aviator's sense of discomfort.
Launching off period middle and later periods, cushioning the air compression antagonistic force that helps in the ereisma will be gradually greater than launching load.Make buffering help the ereisma pulling to launch protruding and the carrier-borne aircraft acceleration.The takeoff speed of carrier-borne aircraft will be that piston velocity and buffering help ereisma pulling speed sum.Like this, carrier-borne aircraft will obtain bigger takeoff speed and safety.In other words, under the certain situation of takeoff speed, will allow bigger carrier-borne aircraft load to carry out catapult-assisted take-off.
2, the formation of buffering ejector
Double-acting cylinder
It is the main body that buffering helps ereisma.It is the critical component of realizing compression and helping the bullet effect.Constitute by 1 back cavity pore, 2 terminal bufferings, 3 pistons, 4 piston rods, 5 cylinder barrels, 6 steam mould bottom valves, 7 high pressure hoses.Be installed in launching on the knife plate that piston protrudes upward by jointed shaft.
6 steam mould bottom valves
It is a little latus rectum steam mould bottom valve, is used for accuracy control to enter buffering and help the quantity of steam that plays cylinder from the main cylinder that launches.Guarantee that buffering helps ereisma to realize effective air compression ratio at the different loads carrier-borne aircraft.Being installed in buffering helps in the front end cover that plays cylinder.
7 high-pressure pipes and water conservancy diversion air flue
It is used for being communicated with the vapor chamber that buffering helps ereisma, launches protruding and master cylinder piston.
High pivot point ejection arm Figure 11
U.S.'s design-calculated ejector is the present best jato unit of effect in the world.It is superior performance not only, merges do also very good with the integral body on the deck of aircraft carrier.Especially launch not only firm but also small and exquisite that shuttle does, on whole aircraft carrier, seem very unremarkable.I was also once wanting to follow this design direction when considering the design of launching shuttle.But I find that the design of this close proximity to ground is forward simultaneously downwards in the direction of the pulling force in a flash that launches.Low like this Moment Point, huge test beyond doubt for nose-gear, front tyre and housing construction intensity.Also therefore, carrier-borne aircraft and Lu Hang aircraft have huge difference in design.This consideration also be China's aircraft in design and be converted into a difficult problem and the weakness of carrier-borne aircraft aspect.
The shuttle design-calculated is littler, and it also is " short wooden stake " of tripping when aircraft does not launch.Since be short wooden stake bigger again why not.In fact according to my design concept, when not launching usually, launch protruding may be collapsed to the cunning that upwarps jump the deck below.Like this, can be very smooth on the deck.
The formation of high pivot point ejection arm
I temporarily can not find suitable title and call the special-shaped plunger cylinder in this design and be fixed on forged steel cover on the carrier-borne aircraft.Describe their shape and matching relationship with " recessed " " protruding " two words in the Chinese character, I feel very vivid.Therefore, two critical components in the high pivot point ejection arm are referred to as respectively to launch protruding and launch recessed.
1, launch protruding
Launching protruding is that a complete special forged steel or titanium alloy material are made.Bottom rectangle helps the piston rod of ereisma to be connected with buffering.Rectangle is upwards elongated gradually to narrow down to stretch out and launches behind the seam again thickening projection significantly upward.Being equipped with an oval deep hole with forward leaning angle in the interposition of projection uses as cylinder barrel.In adorn an ovallized column stopper rod, the top of plunger rod is that a circular columns is prominent.Launching protruding design height and be exactly plunger rod stretches out the circular projection in top, back and approaches aircraft nose-gear and fuselage bonded assembly root.Launching protruding unit design and material selects to take into full account it and satisfies maximum load needs when launching.Launching protruding cylinder bottom has an aperture and buffering to help the centre hole of the piston rod of ereisma to be communicated with, make to enter to cushion the small amount of steam that helps ereisma and can enter and launch protruding cylinder, in order to launch new field of technical activity jack-up plunger rod insertion launch recessed in.If oval cylinder design becomes gravity reduction unreliable, also can be designed to double-acting cylinder, reset with steam.
2, launch recessed.
Launch the recessed forward position that approaches aircraft nose-gear and body bonded assembly root that is installed in.Launch recessed best and nose-gear unit design, be subjected to force intensity thereby strengthen it.And should adopt the materials processing of firm abrasion resistant forged steel to form.Launching recessed bottom center position has one can hold and launch the prominent deep hole of protruding top circular columns.After taking off, launch recessed can the income in the cabin with nose-gear.It is unrestricted that nose-gear is packed up direction.
The effect of high pivot point ejection arm
Launch protruding with launch recessed being used, make between ejector and the carrier-borne aircraft to form a high some virial arm.At the beginning of launching, be used to overcome the thrust of aero-engine, make carrier-borne aircraft remain on original position; During the ejection piston setting in motion, the huge tension when launching makes the overall aircraft structure can rationally absorb impulsive force at the root of nose-gear.
When launch protruding pushing away carrier-borne aircraft and entering the ramp after, head begins to raise up under the support of front-wheel, level is advanced launches and protrudingly extracts until disengaging gradually from launching of aircraft is recessed.It is protruding fast stealthy to launching under the deck to lose launching of load, and near the brake section.
When ejection piston brake with when resetting, launch the plunger rod by gravity withdrawal on protruding.
Steam launches control cock picture group 12
Aircraft carrier steam ejector is a huge system integration.He needs the very tight and complicated hierarchy of control of a cover to ensure the accurate realization of its function.Wherein, be undoubtedly the most important thing for the control of launching cylinder.By the understanding to domestic and international high pressure valve, I propose the design concept that steam launches control cock at this.
The steam ejection valve that aircraft carrier is used is different from our understanding to the industrial steam valve.For example at thermoelectric power station, we need control the superheated steam of big pressure, big flow.But we are when opening, closing and regulating superheated steam, and what we pursued is slow and stable, and steam valve is opened more slowly or closed.So just can avoid impact to Steam Turbine.And for the steam catapult on the aircraft carrier, what we needed is that the energy fast speed that superheated steam contains is discharged, in moment of several seconds only with carrier-borne aircraft from the static state of liter that flies away from that accelerates to.
One, steam launches the effect of control cock group
Because the restriction on the aircaft configuration intensity, ejector not only will have enough horsepower outputs, and will accurately be controlled at horsepower output in the aircraft acceptable degree.This is that the flow of cylinder is launched in the steam injection and the variation of flow realizes by controlling.Launch control cock and play the effect of most critical here.The switching speed of this valve and the accuracy rate of amplitude can directly have influence on the controllability of ejection acceleration.Whole ejection process is to finish by the switching time and the amplitude that change valve to the control of acceleration/accel.In operation, launch the control of valve and need be undertaken by a set valve regulated curve.The collocation of different aircrafts and different equipments all can have the different load of launching.Guarantee enough ejection speeds and correct acceleration/accel, will formulate corresponding valve regulated curve according to different weight when launching.
In brief, steam launches the control cock group should have slowly the function of opening, closing soon, has in circulation process the accurate regulatory function to flow again simultaneously.
This steam launch control cock have sturdy and durable, compact conformation, small and exquisite, valve body vibration is little, complete function, reliable carries out being active in one's movements, smoothly, service life is lasting, is convenient to numerous characteristics of modularization management and easy maintenance.Play for the overall performance that improves ejection system positive, crucial effects.
Two, steam launches the principle of design of control cock group---the hydraulic balance design
Herewith the principle of design of the control streaming system that arrives of prerequisite is the same, and it is closely related that steam launches the Design Mechanism of the realization of function of control cock and hydraulic balance, and can realize flow control function under multiple pressure.In the inside of this valve, the control effort of control steam flow and flow velocity comes from high pressure steam itself.Steam pressure is much, and control effort just nearly.
What is particularly worth mentioning is that this valve supports the transformation of ejection system to use.Promptly allowing to launch pressure adjusts according to the variation of actually launching needs, launching load.All parts of whole ejection system are as long as design based on the transformation factor, and steam launches control cock can guarantee the control ability of ejection system under different pressures accurate and effective still.The widespread popularity that the design of this transformation helps launching is enriched the kind of carrier-borne aircraft.
Three, steam launches the formation of control cock group
Steam launches the control cock group and is actually a valve group that realizes full automatic control, and it is made up of steam open and close valve and steam mould bottom valve two large divisions respectively.
1, steam open and close valve
The steam open and close valve is used to realize quick unlatching and the shutoff to superheated steam.Its big latus rectum design can be satisfied the requirement of big flow of moment.By realizing that to the automatic guidance of opening speed regulator, closing velocity regulating control main valve plug is in the 0.N～opening and closing of N in second.
1.1, the function of steam open and close valve
The steam open and close valve is opened: when priority valve was in unloaded position, the P-C path C-T path that dams was communicated with, and the spool epicoele is because of steam off-load decompression, and the steam pressure of spool bottom is greater than the spool epicoele, thereby automatically spool jack-up was realized that main line is through-flow;
The steam open and close valve is closed: the P-C path is communicated with and the C-T path dams when priority valve commutates, reject steam enters the spool epicoele, spool upper and lower cavity equilibrium of pressure, because of the spool upper section forms pressure difference greater than its lower section, the application force spool of spring is closed downwards and is realized that main line dams in addition.
This steam open and close valve has taken into full account the desired reliable and safety of ejection system in design.The steam open and close valve designs for normally closed valve.Lose industry control voltage or industry control air pressure if system hinders for some reason, 2/3 guiding valve of priority valve will be pushed to that the P-C path is communicated with and position that the C-T path dams, the steam open and close valve under the effect of steam with SELF CL.
1.2, the formation of steam open and close valve
The steam open and close valve is the inserted valve structure, is made of priority valve, main valve plug, valve seat, valve gap and valve body respectively.
1.2.1, priority valve
Priority valve and steam open and close valve main valve plug be direct connection not.It realizes the opening and closing of main valve plug by the control to the bypass low discharge steam of the main valve plug upper and lower cavity of flowing through.Priority valve is made of 2/3 electromagnetic valve, little cylinder, 2/3 guiding valve, opening speed regulating control, closing velocity regulating control etc.
2/3 electromagnetic valve is used to control the row of giving of the industry control source of the gas that promotes little cylinder, gets electric air inlet, the dead electricity exhaust; Little cylinder is used to control the position of 2/3 guiding valve;
The opening speed regulating control by the throttle governing to main valve plug epicoele superheated steam off-load flow, is realized the control to the main valve plug opening speed.
The closing velocity regulating control is gone into the throttle governing of the superheat steam flow of main valve plug epicoele by convection current, realizes the control to the main valve plug closing velocity.
The accuracy control of opening timing control and shut regulating control is helped to realize accurate assurance to launching time point, launching load and carrier-borne aircraft bearing strength to help to improve aviator's traveling comfort.Opening speed regulating control, closing velocity regulating control are made of flow regulating valve, screw rod, servomotor and displacement pickup respectively.
1.2.2, main valve plug
Main valve plug is that flow of superheated steam is realized unlatching or the key of closing, and spool is a soft seal inserted valve structure.Spool is made of valve pocket, spring, spool, valve seat, sealing and orienting sleeve etc.The selection of material is based on its special pressure and requires and bad working environment.The bottom that in the bottom of spool is a carbon tungsten alloy is fixed together soft sealing and carrier ring and spool by screw thread, and bottom plays simultaneously to being subjected to steam worn-down important mission.Be free-running fit between spool and the valve pocket, the support bottom spool of seal ring and orienting sleeve can be in valve pocket up-and-down movement.In normal danger, the soft seal of spool and the soft contact the-face sealing effect that is pressed in following valve seat realization spool by valve pocket.This seal form have sealing tight, be difficult for cavitating, high temperature high voltage resistant and the low characteristics of component wear rate.In the control system of high-pressure fluid, soft contact-face sealing form is a kind of good and advanced seal form.
1.2.3, valve gap
Valve gap is used for spool is fixed in the valve pocket of valve inner, the carrier that simultaneously to be again priority valve be connected and fix with valve pocket and little bypass realization.
1.2.4, valve seat
The soft seal of valve seat and spool realizes the soft contact the-face sealing effect of spool.The wear resisting property of closing sealing effectiveness and valve seat of steam open and close valve is the important indicator to valve seat.
2, steam mould bottom valve
Steam mould bottom valve is to realize thereby the steam flow accuracy control is realized different keys of launching the load effect.It is a full automatic control valve equally.
2.1, the accurate regulatory function of steam mould bottom valve
Under the Long-distance Control of launching curve, servomotor is the turn screw rod under the control of the precise displacement feedback signal of displacement pickup, forms precise displacement thereby drive between spool and the valve seat.Reach accurate adjustment orifice size to realize accuracy control purpose to steam flow.
Steam mould bottom valve adopts pressure balanced design equally.Flow through next steam when flowing through steam mould bottom valve main valve plug from the steam open and close valve, the spool lower end centre hole that is communicated with the spool epicoele can import steam pressure into epicoele, makes the upper and lower cavity equilibrium of pressure of spool, and screw rod does not stress.Like this, steam mould bottom valve steam regulation flow freely still in ejection process.Thereby realize launching the details control in the time period.Realization is launched time point, is launched the accurate assurance of load, helps to improve aviator's traveling comfort.
2.2, the formation of steam mould bottom valve
Steam mould bottom valve partly is made of displacement pickup, servomotor, screw rod, spool, valve gap, valve body and sealing etc.
2.2.1, displacement pickup
2.2.2, servomotor
2.2.3, screw rod
Screw rod effectively is connected by bearing with spool, drives the spool up-and-down movement.The screw flight fineness degree has important decisive to degree of regulation.
2.2.4, spool
Spool is the inserted valve structure.Spool is made of valve pocket, spool, valve seat, sealing and orienting sleeve etc.Adopting stainless steel material to be based on its special pressure requires and bad working environment.Spool is a charcoal tungsten alloy material cone valve structure.Form the fixed restriction curvilinear motion between the conical surface and the valve seat.
Valve gap is used for spool is fixed in the valve pocket of valve inner equally, the carrier that simultaneously to be again displacement pickup, servomotor, screw rod be connected and fix with the spool realization.
2.2.5, valve body
Valve body is the body that steam launches the control cock group, and he is combined into one steam open and close valve and steam mould bottom valve.Adopt the steam of inserted valve structure to launch the control cock fabricate block and have good pipeline and become straightforward, can effectively reduce the steam drop loss that causes because of valve, improve system effectiveness.The material of valve body and size depend on media type, flow and pressure requirement.Select the forged steel material for use, require and bad working environment with regard to being based on its special pressure.Valve body is connected with pressure piping by flange, helps the modularization of steam open and close valve in system like this and safeguards.
Steam launches control cock and has made full use of the pressure balanced design theory in design.The concussion damage that the design of no valve rod has avoided valve rod causes in the conventional valves design spool and the mechanical external force between the valve seat to cause.
The valve Figure 13 that resets brakes
In brake reset function design plan, the brake valve that resets plays crucial effects.It is a full automatic control valve equally, is based on the pressure balanced design theory equally.Brake resets, and structurally to launch control cock very similar to steam for valve.Unique difference is to be that it has increased an one-way function.
The reset function of valve of brake
Launching new field of technical activity and launching the stage, the brake valve that resets is in closed condition.Be that the P-C path of priority valve is communicated with and the C-T path dams, come from the reset steam of valve import of brake and impelling main valve plug in the closed position.At the coda that launches, ejection piston produces the savings of pressurized air and water in the brake section, and pressure rises rapidly.Pressurized air or water enter in the valve pocket from the reset outlet of valve of brake, enter into bypass check valve position by little bypass.The steam pressure of valve import if the pressure of pressurized air or water resets above braking, it is in the closed position through P-C path continuation control main valve plug to substitute steam.Assist the brake section to realize brake function.
When ejection piston stops and beginning to reset, the pressurized air of brake section or the pressure of water begin to lower, the pressure sensor of brake section is given the remote control center signal, the remote control center control brake 2/3 priority valve commutation P-C path of the valve C-T path that dams that resets is communicated with, main valve plug epicoele decompression, the brake valve that resets is in opening.Steam enters the brake section and impels piston reset.Simultaneously, piston reset speed feeds back signal to remote control center by displacement pickup, controls the steam mould bottom valve of valve that resets that brakes by remote control center, thereby controls the flow that steam enters the brake section.Finish until resetting, close the valve that resets that brakes once more.
Claims (1)
1. aircraft carrier launches/slides the core technology that has in the system of jumping with lower part ten the design:
(1) high pressure jet nozzle assembly
The complete high pressure jet nozzle assembly on the cylinder of cracking is to be installed in by several high pressure jet nozzle assembly unit (length depends on the length of cylinder segmentation) modes continuous, horizontal symmetrical to crack about cylinder between two sides of a ship.Each high pressure jet nozzle assembly unit is to be made of nozzle body, fan-shaped chamber, O type circle, linear sealing, last side nozzle wear plate, following side nozzle wear plate etc.Its function is to crack at cylinder to locate to form high pressure water sealing and positive lubrication, and forms the hydro retarder function at the brake section.
(2) nozzle flow control valve
Each nozzle rear end on the high pressure jet nozzle assembly all correspondence is connecting a nozzle flow control valve.The nozzle flow control valve is made of overcoat, valve pocket, spring, spool, valve seat and sealing.Symmetry is installed in cracks about cylinder in two side of a ship bodies, and its function is to realize the injection switching and the step function of each nozzle, and can make nozzle realize that increase and decrease is pressed to spray.
(3) high pressure water sealing control streaming system
High pressure water sealing control streaming system is made of electricity-gas guide 23 logical high pressure change-over valves, nozzle flow control valve, high pressure water hydraulic power line, high pressure water bypass line.Link between the total vavle shelf that the high pressure water trunk line is constituted 23 logical high pressure change-over valves of electricity-gas guide by the high pressure water hydraulic power line and each the nozzle flow control valve.This system can realize injection switching and the step function and the injection of increase and decrease pressure of each nozzle.
(4) ejection piston
Based on the ejection piston of titanium alloy material by the piston body of hollow, launch knife plate, wear plate, awl cylindricality lordosis and water conservancy diversion air flue and constitute.It is the key that steam can convert ejection force to.
(5) cylinder unit of cracking
The cylinder unit of cracking is made up of two cylinders that crack, and cylinder segmentation, front end cover and rear side housing that every open cylinder is being adorned the jetting assembly body by some joints constitute.The high pressure water collector of both sides, top is connected the crack rear end of each nozzle flow control valve of two sides of a ship of cylinder by the high pressure hose that is symmetrically distributed.Two pistons launch knife plate from the below tiltedly right cylinder crack and stretch out the back and buffering helps the ereisma bracing frame to be fixed together.It is the core component of ejector.
(6) buffering helps ereisma
Buffering helps ereisma to be made of double-acting cylinder, steam mould bottom valve, bracing frame, jointed shaft, high pressure hose and water conservancy diversion air flue.The time compole short ejection process in, buffering helps ereisma compression earlier to be buffered in the bounce-back power-assisted.Damping protection and the auxiliary double action of quickening have been played to carrier-borne aircraft.
(7) launch recessed
Launch the recessed forward position that is installed in aircraft nose-gear and body bonded assembly root.The bottom center position has one can hold and launch the prominent deep hole of protruding top circular columns.It is used for giving carrier-borne aircraft with launching transfer of energy, reduces to launch the requirement to the carrier-borne aircraft structural strength.
(8) launch protruding
Launching protruding is a different in nature plunger cylinder, and its bottom helps the piston rod of ereisma to be connected with buffering and is stuck in the guide rail by the guide rail wheel, and top is an oval plunger cylinder, and ovallized column stopper rod top has a circular columns prominent.It is recessed that it is used for that ejection force is passed to launching of carrier-borne aircraft alighting gear root, thereby reduce the impact to housing construction.
(9) steam launches the control cock group
Be a valve group that realizes full automatic control, it is made up of steam open and close valve and steam mould bottom valve two large divisions respectively.It is used to control the switching that enters the steam that launches cylinder and the accuracy control of flow.
(10) the brake valve that resets
He is a full automatic control valve equally, is used for the switching of steam and the flow of accuracy control steam, makes steam enter cylinder from the cylinder end and plays the ejection piston reset response later on.
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| Application Number | Priority Date | Filing Date | Title |
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| CN2009101485526A CN101934862A (en) | 2009-06-29 | 2009-06-29 | High-fulcrum launch/ski-jump system for aircraft carrier |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009101485526A CN101934862A (en) | 2009-06-29 | 2009-06-29 | High-fulcrum launch/ski-jump system for aircraft carrier |
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Cited By (13)
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|---|---|---|---|---|
| CN102343982A (en) * | 2011-07-21 | 2012-02-08 | 鲁小朔 | Semi-open interlayer booster takeoff runway of aircraft carrier |
| CN102745333A (en) * | 2012-07-31 | 2012-10-24 | 李文铎 | Internal combustion steam boosting take-off unit of airplane |
| CN102849221A (en) * | 2011-06-27 | 2013-01-02 | 王长存 | Short-distance lift-off vehicle for military aircraft |
| CN102980439A (en) * | 2011-09-06 | 2013-03-20 | 罗云 | Rubber strip type steam ejection device |
| CN104787354A (en) * | 2015-03-11 | 2015-07-22 | 西北农林科技大学 | Linear accelerating ejecting-sliding combined ejector |
| CN105035344A (en) * | 2015-08-13 | 2015-11-11 | 济南环太机电技术有限公司 | Liquid emission type shipboard aircraft carrier catapult |
| CN106742026A (en) * | 2017-01-10 | 2017-05-31 | 胡达广 | Intelligent aircraft catapult |
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| CN108216671A (en) * | 2018-01-26 | 2018-06-29 | 白景魁 | A kind of boosting of aircraft carrier slides jump formula takeoff method |
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| CN102849221A (en) * | 2011-06-27 | 2013-01-02 | 王长存 | Short-distance lift-off vehicle for military aircraft |
| CN102343982A (en) * | 2011-07-21 | 2012-02-08 | 鲁小朔 | Semi-open interlayer booster takeoff runway of aircraft carrier |
| CN102980439A (en) * | 2011-09-06 | 2013-03-20 | 罗云 | Rubber strip type steam ejection device |
| CN102745333A (en) * | 2012-07-31 | 2012-10-24 | 李文铎 | Internal combustion steam boosting take-off unit of airplane |
| CN104787354A (en) * | 2015-03-11 | 2015-07-22 | 西北农林科技大学 | Linear accelerating ejecting-sliding combined ejector |
| CN105035344A (en) * | 2015-08-13 | 2015-11-11 | 济南环太机电技术有限公司 | Liquid emission type shipboard aircraft carrier catapult |
| CN106742026A (en) * | 2017-01-10 | 2017-05-31 | 胡达广 | Intelligent aircraft catapult |
| CN107264830B (en) * | 2017-07-31 | 2023-06-02 | 威海广泰空港设备股份有限公司 | Active safety docking aircraft system for aviation ground equipment |
| CN107264830A (en) * | 2017-07-31 | 2017-10-20 | 威海广泰空港设备股份有限公司 | Air Ground Equipment active safety docks aircraft system |
| CN108190041A (en) * | 2018-01-19 | 2018-06-22 | 扬州飞虎航空科技有限公司 | A kind of portable fixed-wing catapult-launching gear |
| CN108216671A (en) * | 2018-01-26 | 2018-06-29 | 白景魁 | A kind of boosting of aircraft carrier slides jump formula takeoff method |
| CN111216915A (en) * | 2018-11-26 | 2020-06-02 | 韩伟立 | Boosting ejection device |
| CN111216915B (en) * | 2018-11-26 | 2021-07-09 | 韩伟立 | Boosting ejection device |
| CN109795708A (en) * | 2019-01-20 | 2019-05-24 | 陈厚然 | A kind of linear accelerating power device |
| CN110243581A (en) * | 2019-06-05 | 2019-09-17 | 南京航空航天大学 | A kind of undercarriage wheel pressure rope experimental rig and test method |
| CN110243581B (en) * | 2019-06-05 | 2021-01-08 | 南京航空航天大学 | Airplane wheel compression cable test device and method for airplane landing gear |
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Application publication date: 20110105 |