CN103057722B - Active maglev electromagnetic catapult - Google Patents

Active maglev electromagnetic catapult Download PDF

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Publication number
CN103057722B
CN103057722B CN201310005736.3A CN201310005736A CN103057722B CN 103057722 B CN103057722 B CN 103057722B CN 201310005736 A CN201310005736 A CN 201310005736A CN 103057722 B CN103057722 B CN 103057722B
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China
Prior art keywords
ejection platform
ship
magnetic
ejection
platform
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Expired - Fee Related
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CN201310005736.3A
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CN103057722A (en
Inventor
张钢
张海龙
张坚
李明彦
孙昌
孟庆涛
支汉立
姜笑颖
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University of Shanghai for Science and Technology
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University of Shanghai for Science and Technology
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Publication of CN103057722A publication Critical patent/CN103057722A/en
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Publication of CN103057722B publication Critical patent/CN103057722B/en
Expired - Fee Related legal-status Critical Current
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Abstract

The invention relates to an active maglev electromagnetic catapult for aircraft carriers. The active maglev electromagnetic catapult comprises a maglev guide rail fixed on a catapult base, a catapult platform sleeved on the guide rail, and a linear motor. The shipboard aircraft catapult platform is supported by active maglev supporting technology and is driven by the high-power linear catapult motor, and catapult-assisted take-off of shipboard aircrafts is achieved. The active maglev supporting technology is introduced, a catapult platform position control system and a speed control system are provided, and accordingly positioning precision and catapulting speed of the catapult platform are increased greatly, electrification is achieved and the service life is prolonged. The active maglev electromagnetic catapult has the advantages of adjustable supporting rigidity and damping, no friction, no need of lubrication, no environment pollution and the like.

Description

Active maglev electromagnetic catapult
Technical field
The present invention relates to the Electromagnetical ejector on a kind of aircraft carrier, particularly a kind of active maglev electromagnetic catapult.
Background technology
Aircraft carrier, as maritime overlord, occupies core status in naval weapon.One of critical component of aircraft carrier ejector is the large difficult point of one in aircraft carrier technology always.Along with the growth at full speed of China's economy, the continuous lifting of state-of-art, there have been certain economic strength and technical capacity in China to develop the aircraft carrier of oneself.Liaoning warship aircraft carrier repacked into by watt good lattice number is the real starting point of Chinese aircraft carrier, but it to be the aircraft carrier that do not complete bought from Ukraine by China reequip, do not comprise the critical component of ejector at all, only have relatively backward cunning to jump formula take-off-helping deck.
First, from the mode of taking off, China can not rest on the backward cunning formula of jumping and take off, and the aircraft carrier fighting capacity of this Hui Shi China is had a greatly reduced quality.Secondly, due to the steam type ejector technical sophistication of current foreign duty, China also has no construction experience, moreover the U.S. can not sell China this technology, so selection that neither be best.Finally, more advanced ejector-Electromagnetical ejector of future generation is the selection of our the best.So, Electromagnetical ejector technology is researched and developed very important.
The U.S. is the country that Electromagnetical ejector development is leading, and it is reported, the U.S. tests successfully on land, expectation will be equipped on Ford aircraft carrier of future generation, it is reported that equipment four is overlapped the electromagnetic launch phase by Ford aircraft carrier, but be all mechanical support, is not magnetic suspension bearing.And the domestic Electromagnetical ejector model machine of research as naval engineering university develops to this of China is also mechanical support, therefore, need to drop into relevant research to magnetic levitation electromagnetic catapult.
The active maglev electromagnetic catapult of the present patent application comprises two gordian techniquies: active magnetic supporting technology and high-power straight line launch motor technology.
Active magnetic supporting technology is one of universally acknowledged new and high technology.Its maximum feature achieves noncontact, exactly without friction supporting.Magnetic levitation technology is applied on Electromagnetical ejector and brings very large lifting by the performance of ejector.
It is a kind of linear electric motors actuation techniques electric energy being directly changed into straight-line motion mechanical energy that the high-power straight line that Electromagnetical ejector adopts launches motor technology, it is the novel linear actuation techniques that one does not need by any buffering mechanism (as chain, tooth bar or leading screw etc.), it is the up-to-date technology with new principle, new theory occurred in the second half in 20th century electrical field, the same with microelectronic technique, computer technology and rotary motor technology, have broad application prospects in the every field of the mankind.
At present, the U.S. has successfully utilized Electromagnetical ejector to launch aircraft on land, but just the piston of steam catapult has been changed into high-power straight line launches motor to the Electromagnetical ejector of development before u. s. mesh, launch motor with roller, run along catapult track under the effect of electromagnetic force with a shuttle trffic, haul aircraft and accelerate to takeoff speed along launching stroke above deck, aircraft is still placed directly on deck by wheel, does not eliminate the rolling frictional resistance between airplane wheel and deck.This point can all not mentioned active magnetic supporting technology these two aspects and is confirmed from the Electromagnetical ejector video of United States Navy's announcement and numerous Electromagnetical ejector document.And the application's scheme launches motor as driving except adopting straight line, also introduce active magnetic supporting technology, utilize magnetic levitation technology that the ejection platform of placing aircraft is suspended, can be more advanced in the ejector performance eliminating friction drag, not only can exceed the U.S., also can reach the international leading level.
Summary of the invention
The object of the invention is to the defect existed for prior art, a kind of active maglev electromagnetic catapult is provided, it utilizes active magnetic supporting technology to support the ejection platform of placing carrier-borne aircraft, and launch motor driving ejection platform with high-power straight line, realize the object of ship-board aircraft catapult-assisted take-off.
In order to achieve the above object, the present invention adopts following technical scheme:
A kind of active maglev electromagnetic catapult, comprise the ejection platform and linear electric motors that are fixed on and launch magnetic suspended guide on base and be sleeved on guide rail, it is characterized in that also including the link connecting ship-board aircraft above ejection platform, what have magnetic suspended guide launches base, be embedded in the magnetic material in ejection platform, corresponding with magnetic material and be fixed on launch base magnetic suspended guide on both sides, below and side, the carrying of controlled Systematical control and guiding electromagnet and be arranged on the inductosyn that this electromagnet side is used for detecting ejection platform change in displacement, be positioned at launch base magnetic suspended guide end face line of centers on be used to provide ejection power straight line launch electric motor primary winding and the corresponding secondary winding being embedded in ejection platform and pushing up, be arranged on armature winding side to be used for detection of straight lines and to launch motor and drive the speed sensor of ejection platform speed and be arranged on the aviation socket of all active electric wires of the connection of launching base head end, this aviation socket is connected on the control housing of ejector by the aviation plug matched with it.
In above-mentioned active maglev electromagnetic catapult, the described magnetic material be arranged in ejection platform forms magnetic suspension bearing device with the electromagnet launched on the magnetic suspended guide of base, this device adopts attractive magnetic levitation technology, corresponding on the same cross section of ejection platform, launch on the both sides of the magnetic suspended guide of base, a pair carrying differential electromagnet and corresponding coil pickup are installed respectively below, and a pair guiding differential electromagnet and corresponding inductosyn are installed in the two sides of this guide rail, controlled by No. 3 control circuits respectively, in the process that ejection platform is run, have at least 2 ' No. 3 control circuits to control ejection platform make it stable suspersion on the magnetic suspended guide launching base, whole magnetic-levitation has 2 ' 3n road control circuit, every road control circuit is made up of analog control circuit or digital control chip, the armature winding that straight line launches motor is installed in the middle of magnetic suspended guide, corresponding ejection platform is installed the secondary winding that straight line launches motor, all active electric wires are all concentrated on the aviation socket that connects and lead to and launch base head end launching chassis interior, then are connected on control housing by the aviation plug matched with it.
In above-mentioned active maglev electromagnetic catapult, the electric signal of the described inductosyn for detecting ejection platform displacement exports the input of a connection magnetic suspension controller, the control circuit of controller is made up of analog control circuit or digital control chip, and the output of this magnetic suspension controller connects carrying and guiding electromagnet through power amplifier; The electric signal of described speed sensor exports the input of a connection variable-frequency speed-regulating controller, and the output of this variable-frequency speed-regulating controller connects the armature winding that straight line launches motor; Its control process is as follows: ejection platform is after the effect of magnetic buoyancy is issued to balance position, if there is a disturbance to make ejection platform have the microvibration except launching direct of travel to offset, first this skew is monitored by a pair inductosyn, then detection signal is inputted a controller, export after the signal transacting of this controller and control the size of current that electric current controls a pair electromagnet, thus control electromagnetic force size makes ejection platform come back to balance position.And variable-frequency speed-regulating controller launches the adjustable straight-line motion magnetic field of the armature winding input speed of motor to straight line, drive the secondary winding in ejection platform to do straight line sling movement, the ejection speed of ejection platform is measured by speed sensor.
In above-mentioned active maglev electromagnetic catapult, described straight line launches the form that motor adopts elementary long stator, secondary short mover.
In above-mentioned active maglev electromagnetic catapult, the link of the described fixing ship-board aircraft be arranged in ejection platform plays effect ship-board aircraft is firmly connected in ejection platform, this link is by draw bar and pull bar and form, their effect is that before ship-board aircraft takes off, ejection platform draws ship-board aircraft operation by draw bar, and the engine start of ship-board aircraft also pulls ejection platform operation simultaneously; During owing to launching ship-board aircraft, under straight line launches motor and ship-board aircraft drives jointly, just must can complete the catapult-assisted take-off of ship-board aircraft, be traction ship-board aircraft and pull ejection platform jointly to accelerate launching accelerated period link Main Function; Launching latter stage, when namely ship-board aircraft has accelerated to its takeoff speed, link will decontrol the connection of ship-board aircraft and ejection platform automatically, ship-board aircraft launches the propulsive effort catapult-assisted take-off of inertia and self engine by utilizing, and ejection platform change reverse actuating force and under braking device drag effect brake deceleration, stop to during end, then return head end original position and prepare to launch next frame ship-board aircraft.
The present invention and existing steam catapult are compared with U.S. Electromagnetical ejector technology, there is following apparent outstanding substantive distinguishing features and remarkable advantage: in the present invention, adopt carrying electromagnet and guiding electromagnet to be suspended on guide rail by ejection platform, and be provided with ejection platform position control system and speed control system, thus substantially increase positioning precision and the ejection speed of ejection platform, extend service life, and have support stiffness damping adjustable, without friction, without the need to advantages such as lubrication, non-environmental-pollutions.
Active magnetic technology is one of of the present invention two large gordian techniquies.Owing to having very large relative velocity between the ship-board aircraft in ejection platform and ejection orbit, so supporting technology just seems extremely important.In the Electromagnetical ejector of steam-type ejector and the U.S., aircraft is directly contacted with type aircraft carrier deck by airplane wheel, friction between them belongs to friction of rolling, add air speed very large, friction force is the principal element hindering acceleration capability, and the present invention adopts active magnetic technology, the friction drag between ship-board aircraft in type aircraft carrier deck and ejection platform can be eliminated, make carrier-borne aircraft only by air resistance, the acceleration capability launching performance and carrier-borne aircraft for ejector has and significantly promotes effect.Magnetic levitation technology is successfully applied on magnetic suspension train, can prove its feasibility.What the present invention adopted is attractive magnetic levitation technology (also can adopt repulsion type magnetic levitation technology).
It is another gordian technique of the present invention that straight line launches motor.But ejector is due to self, designing requirement is different from generic linear motor.First feature is because aircraft will be accelerated to the speed of taking off by ejector in short time short travel, and as the heart of ejector, it is very large that this just requires that straight line launches the power of motor.In addition, because ejection platform wants there is larger relative velocity between type aircraft carrier deck, so will avoid arranging active electric wire in ejection platform, this is second feature.
Accompanying drawing explanation
Fig. 1 is the overall structure schematic diagram of one embodiment of the invention.
Fig. 2 is the constructional drawing that magnetic suspended guide in Fig. 1 ejection platform cross section and electromagnet and linear electric motors two-stage distribute.
Fig. 3 represents that displacement pickup detects the connection circuit figure of ejection platform vibration displacement and speed sensor detection ejection platform ejection speed.
Fig. 4 represents every road analog control circuit figure of ejection platform position control system middle controller.
Fig. 5 represents that detection signal exports after controller process and controls electric current to electromagnet and frequency-converting speed-governing control system to the control circuit schematic diagram of linear electric motor primary.
Fig. 6 is the basic principle schematic that high-power straight line launches motor.
Fig. 7 represents the structural representation of link 3.
Detailed description of the invention
The preferred embodiments of the present invention accompanying drawings is as follows:
Embodiment one:
See Fig. 1 and Fig. 2, this active maglev electromagnetic catapult, include by the carrier-borne aircraft 1 that launches and place ship-board aircraft and the ejection platform 2 be sleeved on guide rail, it is characterized in that also including the link 3 connecting ship-board aircraft 1 above ejection platform 2, what have magnetic suspended guide launches base 4, be embedded in the magnetic material 5 in ejection platform 2, corresponding with magnetic material 5 and be fixed on launch base 4 magnetic suspended guide on both sides, below and side, the carrying of controlled Systematical control and guiding electromagnet 6 and be arranged on the inductosyn 7 that this electromagnet 6 side is used for detecting ejection platform change in displacement, be positioned at launch base 4 magnetic suspended guide end face line of centers on be used to provide ejection power straight line launch electric motor primary winding 8 and the corresponding secondary winding 9 be embedded on ejection platform 2 top, be arranged on armature winding 8 side to be used for detection of straight lines and to launch motor and drive the speed sensor 10 of ejection platform 2 speed and be arranged on the aviation socket 11 of all active electric wires of the connection of launching base 4 head end, this aviation socket is connected on the control housing of ejector by the aviation plug matched with it.
Embodiment two:
See Fig. 1, this active maglev electromagnetic catapult includes by the carrier-borne aircraft model 1 launched, place the ejection platform 2 of ship-board aircraft, its material is intended adopting intensity maximum, density is minimum, the engineering plastics that quality is the lightest make, ejection platform connects the link 3 of ship-board aircraft, it makes ejection platform firmly connect when launching and drive carrier-borne aircraft ejection operation, what have magnetic suspended guide launches base 4, magnetic suspended guide on it makes the relative motion body between 2 with 4 realize mechanical and contacts the supporting of frictionless magnetic levitation technology, the ship-board aircraft in ejection platform is made only to be subject to air resistance, be embedded in the magnetic material 5 in ejection platform, be fixed on the electromagnet 6 of controlled Systematical control on guide rail, be used for detecting the inductosyn 7 of ejection platform change in displacement, the straight line being used to provide ejection power launches electric motor primary 8 and secondary 9, detection of straight lines is launched motor and is driven the speed sensor 10 of ejection platform speed and the aviation socket 11 being connected all active electric wires.
See Fig. 2, it is the constructional drawing that magnetic suspended guide in Fig. 1 example ejection platform cross section and electromagnet and linear electric motors two-stage distribute, magnetic material 5 wherein in ejection platform adopts attractive magnetic suspension principle with the electromagnet 6 on guide rail, and by inductosyn 7 detection platform 2 position and adopt control system to control, this principle refers to Fig. 3, Fig. 4 and Fig. 5.8,9 primary and secondaries being respectively linear electric motors (see Fig. 6), above ejection platform is secondary, without line, doing so avoids large power supply and be connected with the electric wire of ejection platform.Below on track is elementary, 10 is the speed sensor that detection of straight lines motor drives ejection platform speed, all active electric wires are all connected to aviation socket from the inner passage of ejector base, and associated aviation plug is connected (not shown in FIG.) with control housing.
See Fig. 3, Fig. 4 and and Fig. 5, they be attractive active magnetic control and straight line launch motor variable-frequency speed-regulating control basic connection circuit schematic diagram.Fig. 3 represents that displacement pickup detects the connection circuit figure of ejection platform vibration displacement and speed sensor detection ejection platform ejection speed.Fig. 4 represents every road analog control circuit figure of ejection platform position control system middle controller, as digital control in adopted, and selects corresponding chip to replace.Fig. 5 represents that detection signal exports after controller process and controls electric current to electromagnet and frequency-converting speed-governing control system to the control circuit schematic diagram of linear electric motor primary, wherein, electromagnet and linear electric motor primary stator and displacement, speed sensor is arranged on and launches on the guide rail of submounts, their electric wire is concentrated to connect to lead to and is launched on the aviation socket 11 of base head end launching chassis interior, be connected in control system by the aviation plug matched with it again, ejection platform then embeds installs wireless ferromagnet, the line demand in mobile ejection platform can be avoided like this.Its control process is as follows: ejection platform is after the effect of magnetic buoyancy is issued to balance position, if there is a disturbance to make ejection platform have the microvibration except launching direct of travel to offset, first this skew is monitored by a pair coil pickup, then by detection signal input control device (Fig. 4), export after the signal transacting of controller and control the size of current that electric current controls a pair electromagnet, thus control electromagnetic force size makes ejection platform come back to balance position.And variable-frequency speed-regulating controller launches the adjustable straight-line motion magnetic field of the elementary input speed of motor to straight line, to drive in ejection platform secondary does straight line sling movement, and the ejection speed of ejection platform is measured by speed sensor.
See Fig. 6, it is the basic principle schematic that high-power straight line launches motor, by rotating machine, stators and rotators is launched into elementary (stator) and secondary (mover) of linear electric motors, being secondary above in the expansion form of the present invention's design, is elementary below.This is contrary with the secondary order of common common linear electric motor primary, and it is identical with the elementary secondary order of high-speed maglev train, be fixed in ejection platform for permanent magnet secondary, such ejection platform does not just need large power supply, avoids ejection platform and be connected with the electric wire of emission base.
See Fig. 7, it is the structural representation of link 3, this link is by draw bar and pull bar and form, their effect is that before ship-board aircraft takes off, ejection platform is drawn ship-board aircraft by draw bar and run, and the engine start of ship-board aircraft also pulls ejection platform and runs simultaneously.During owing to launching ship-board aircraft, under straight line launches motor and ship-board aircraft drives jointly, just must can complete the catapult-assisted take-off of ship-board aircraft, be traction ship-board aircraft and pull ejection platform jointly to accelerate launching accelerated period link Main Function; Launching latter stage, when namely ship-board aircraft has accelerated to its takeoff speed, link will decontrol the connection of ship-board aircraft and ejection platform automatically.
Ship-board aircraft ejection process: ship-board aircraft is placed in ejection platform, by the link 3 on it, ship-board aircraft 1 is firmly connected in ejection platform 2, ejection platform is got up by magnetic levitation together with ship-board aircraft, under the common driving that straight line launches motor and ship-board aircraft at head end by static, when accelerating to ship-board aircraft takeoff speed, link 3 unclamps the connection of ship-board aircraft and ejection platform automatically, ship-board aircraft launch to launch under inertia and own drive power effect fly to aerial, and ejection platform changes into reverse actuating force and under braking device drag effect brake deceleration, stop to during end, then return head end original position to prepare to launch next frame ship-board aircraft.
The present embodiment and existing steam catapult are compared with U.S. Electromagnetical ejector technology, motor is launched as driving except adopting straight line, also introduce active magnetic supporting technology, be provided with ejection platform position control system and speed control system, thus substantially increase positioning precision and the ejection speed of ejection platform, achieve electrification, extend service life.Utilize magnetic levitation technology that the ejection platform of placing ship-board aircraft is suspended, eliminate the friction between aircraft and deck, have that support stiffness damping is adjustable, without friction, without the need to advantages such as lubrication, non-environmental-pollutions, the acceleration capability launching performance and carrier-borne aircraft for ejector has and significantly promotes effect.Adopt high-power linear electric motors to have to launch that efficiency setting range that is high, that launch carrier-borne aircraft type is wide, controllability good, responds the series of advantages such as rapid.Can be more advanced in the ejector performance eliminating friction drag, not only can exceed the U.S., also can reach the international leading level.

Claims (4)

1. an active maglev electromagnetic catapult, include by the carrier-borne aircraft (1) that launches and place ship-board aircraft and the ejection platform (2) be sleeved on guide rail, it is characterized in that also including the link (3) connecting ship-board aircraft (1) above ejection platform (2), what have magnetic suspended guide launches base (4), be embedded in the magnetic material (5) in ejection platform (2), corresponding with magnetic material (5) and be fixed on launch base (4) magnetic suspended guide on both sides, below and side, the carrying of controlled Systematical control and guiding electromagnet (6) and be arranged on the inductosyn (7) that this electromagnet (6) side is used for detecting ejection platform change in displacement, be positioned at launch base (4) magnetic suspended guide end face line of centers on be used to provide ejection power straight line launch electric motor primary winding (8) and correspondence and be embedded in secondary winding (9) on ejection platform (2) top, be arranged on armature winding (8) side to be used for detection of straight lines and to launch motor and drive the speed sensor (10) of ejection platform (2) speed and be arranged on the aviation socket (11) of all active electric wires of the connection of launching base (4) head end, this aviation socket is connected on the control housing of ejector by the aviation plug matched with it,
Described be arranged on the magnetic material (5) in ejection platform and launch electromagnet (6) on the magnetic suspended guide of base (4) form magnetic suspension bearing device, this device adopts attractive magnetic levitation technology, on same cross section corresponding to ejection platform (2), launch on the both sides of the magnetic suspended guide of base (4), a pair carrying differential electromagnet (6) and corresponding coil pickup (7) are installed respectively below, and a pair guiding differential electromagnet (6) and corresponding inductosyn (7) are installed in the two sides of this guide rail, controlled by No. 3 control circuits respectively, in the process that ejection platform (2) is run, have at least 2 × No. 3 control circuits to control ejection platform (2) make it stable suspersion on the magnetic suspended guide launching base (4), whole magnetic-levitation has 2 × 3n road control circuit, every road control circuit is made up of analog control circuit or digital control chip, the armature winding (8) that straight line launches motor is installed in the middle of magnetic suspended guide, the secondary winding (9) of motor is launched at corresponding ejection platform (2) upper installation straight line, all active electric wires all lead to and launch on the aviation socket (11) of base (4) head end launching base (4) inner integrated connection, then are connected on control housing by the aviation plug matched with it.
2. active maglev electromagnetic catapult according to claim 1, it is characterized in that the described electric signal for detecting the inductosyn (7) of ejection platform (2) displacement exports the input of a connection magnetic suspension controller, the control circuit of controller is made up of analog control circuit or digital control chip, and the output of this magnetic suspension controller connects carrying and guiding electromagnet (6) through power amplifier, the electric signal of described speed sensor (10) exports the input of a connection variable-frequency speed-regulating controller, and the output of this variable-frequency speed-regulating controller connects the armature winding (8) that straight line launches motor, its control process is as follows: ejection platform (2) is after the effect of magnetic buoyancy is issued to balance position, if there is a disturbance to make ejection platform (2) have the microvibration except launching direct of travel to offset, first this skew is monitored by a pair inductosyn (7), then detection signal is inputted a controller, export after the signal transacting of this controller and control the size of current that electric current controls a pair electromagnet (6), thus control electromagnetic force size makes ejection platform (2) come back to balance position, and variable-frequency speed-regulating controller launches the adjustable straight-line motion magnetic field of armature winding (8) input speed of motor to straight line, the secondary winding (9) in ejection platform (2) is driven to do straight line sling movement, the ejection speed of ejection platform (2) is measured by speed sensor (10).
3. active maglev electromagnetic catapult according to claim 2, is characterized in that described straight line launches the form that motor adopts elementary long stator, secondary short mover.
4. active maglev electromagnetic catapult according to claim 1, it is characterized in that the described link (3) ejection platform being fixed ship-board aircraft that is arranged on plays the effect firmly connecting ship-board aircraft and ejection platform, this link is by draw bar and pull bar and form, their effect is that before ship-board aircraft takes off, ejection platform draws ship-board aircraft operation by draw bar, and the engine start of ship-board aircraft also pulls ejection platform operation simultaneously; During owing to launching ship-board aircraft, under straight line launches motor and ship-board aircraft drives jointly, just must can complete the catapult-assisted take-off of ship-board aircraft, be traction ship-board aircraft and pull ejection platform jointly to accelerate launching accelerated period link Main Function; Launching latter stage, when namely ship-board aircraft has accelerated to its takeoff speed, link will decontrol the connection of ship-board aircraft and ejection platform automatically.
CN201310005736.3A 2013-01-08 2013-01-08 Active maglev electromagnetic catapult Expired - Fee Related CN103057722B (en)

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CN103523242A (en) * 2013-10-25 2014-01-22 东南大学 Electromagnetic catapult based on magnetic gear
CN104691776B (en) * 2013-12-04 2017-11-10 中国科学院宁波材料技术与工程研究所 Permanent-magnet linear catapult-launching gear
CN103754384A (en) * 2014-01-02 2014-04-30 上海大学 Passive magnetic suspension type electromagnetic launcher
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