CN104019698A - Superconducting electromagnetic rapid and continuous transmitting system and implementation method thereof - Google Patents

Superconducting electromagnetic rapid and continuous transmitting system and implementation method thereof Download PDF

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CN104019698A
CN104019698A CN201310064659.9A CN201310064659A CN104019698A CN 104019698 A CN104019698 A CN 104019698A CN 201310064659 A CN201310064659 A CN 201310064659A CN 104019698 A CN104019698 A CN 104019698A
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superconducting
superconducting magnetic
magnetic
flywheel
subsystem
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CN104019698B (en
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刘伟
王家素
马光同
米旺
王素玉
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BEIJING AEROSPACE CENTURY SUPERCONDUCTING TECHNOLOGY Co Ltd
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BEIJING AEROSPACE CENTURY SUPERCONDUCTING TECHNOLOGY Co Ltd
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Abstract

The invention discloses a superconducting electromagnetic rapid and continuous transmitting system and an implementation method of the superconducting electromagnetic rapid and continuous transmitting system. The system comprises a high-temperature superconducting magnetic suspension sub-system, a superconducting electromagnetic propelling sub-system and a superconducting magnetic suspension flywheel pulsed power supply sub-system. The high-temperature superconducting magnetic suspension sub-system comprises a suspension unit and an external magnetic excitation source. The superconducting electromagnetic propelling sub-system comprises a stator body, a transmitted body, a refrigeration device, a low-temperature heat insulation device and a foundation platform. The superconducting magnetic suspension flywheel pulsed power supply sub-system comprises a superconducting magnetic suspension flywheel and a pulse compensation motor and used for conducting energy storage through the flywheel supported by a superconducting magnetic suspension bearing. By means of the superconducting electromagnetic rapid and continuous transmitting system, non-contact transmitting of a carrier is achieved, and the propelling system can be repeatedly used for a long time; the energy storage density which is far higher than that of a super-capacitor can be achieved through the high-speed superconducting magnetic suspension flywheel, and therefore the electromagnetic force density of the propelling system can be effectively increased; the whole electromagnetic transmitting system is simple in control technology and solves the problems that a traditional electromagnetic transmitting system is large in size and complex in structure; the electromagnetic transmitting system is basically made of superconducting materials and has the capacity for conducting continuous transmitting in a short time.

Description

The fast continuous emission system of a kind of superconducting magnetic and its implementation
Technical field
The invention belongs to ELECTROMAGNETIC LAUNCH TECHNOLOGY, relate to a kind ofly can realize carrier propelled at high velocity, without ablation and full superconducting magnetic emission system and its implementation that can launch continuously fast.
Background technology
ELECTROMAGNETIC LAUNCH TECHNOLOGY is the main flow direction in following Aero-Space and weaponry field.Compared with rocket or artillery system, ELECTROMAGNETIC LAUNCH TECHNOLOGY is not limited by the combustion gas velocity of sound and the stagnation velocity of sound, the emitter of different quality can be accelerated to a few km per second to tens kms.In addition, Electromagnetic Launching is without the expensive chemical fuel of filling, and single emission cost is launched well below chemical energy, launch the small-sized bullet of same kinetic energy, its cost is only 1% left and right of cannon, and transmitting larger quality aerospace vehicle time, its cost is approximately the 2%-10% of rocket.
Current traditional ELECTROMAGNETIC LAUNCH TECHNOLOGY mainly can be divided into two large class, i.e. armature rail type and reclosing types.Armature rail type system architecture is simple, and muzzle velocity is higher, but must have electrical connection between emitter and armature, therefore self has frictional dissipation and ablation problem.Reclosing type can be divided into coil reclosing type and magnetic field reclosing type, it can be realized emitter and suspend, the friction of elimination body, but due to magnetic field structure and the reason such as stressed, must adopt propulsion system segmental structure, and need to accurately locate and FEEDBACK CONTROL emitter, the development level of power electronic equipment and control technology has greatly restricted acceleration and the muzzle velocity index of reclosing type Electro-magnetic Launcher System at present.All there is inherent technology defect in above-mentioned two kinds of Electro-magnetic Launcher Systems, and due to the restriction of traditional electrical material, need to force heat radiation, can not meet the armament systems application demand of transmitting continuously.In coming 10 years, as not having great theory or material to break through, above-mentioned two kinds of ELECTROMAGNETIC LAUNCH TECHNOLOGY are difficult to really be applied, therefore in the urgent need to finding a kind of new ELECTROMAGNETIC LAUNCH TECHNOLOGY, not only can realize without friction, high thrust and high muzzle velocity, and can meet continuous launch requirements.
The present invention is to overcome the intrinsic technological deficiency of traditional Electro-magnetic Launcher System as main target, by the introducing of high-temperature superconducting magnetic levitation technology and full superconductor, effectively solve the mechanical friction problem of armature type transmitting existence and the ACTIVE CONTROL difficult problem that the transmitting of reclosing type exists, and make emission system possess continuous emissivities, meet practical application request.Realize without friction, high thrust and high muzzle velocity, and can meet continuous launch requirements.
High-temperature superconducting magnetic levitation technology is based on the peculiar flux pinning ability of high-temperature superconducting block, it is a kind of new type of passive suspension technology, it can realize stable suspersion without ACTIVE CONTROL, both eliminate the frictional dissipation in traditional frame for movement, also avoided the introducing of control technology and equipment in suspension system initiatively.High-temperature superconducting magnetic levitation technology is simple in structure with it, principle reliable, the characteristic of superior performance, becomes one of ideal chose of practical magnetic levitation technology.High temperature superconducting magnetic suspension system can be for maintaining the stable suspersion of emitter, thereby eliminated mechanical friction and ablation, in addition, its suspending power density and rigidity are higher, can meet heavily loaded electromagnetic propulsion demand completely, can be for the launch assist of large aerospace spacecraft.And high-temperature superconducting magnetic levitation principle also can be used for high-speed bearing system, flywheel accumulator based on this has rotating speed height and the large feature of energy storage density, while adopting carbon nano-tube fibre material to make flywheel, its energy storage density can compare favourably with hydrogen fuel cell, far away higher than the energy storage density of super capacitor at present.Super-conductive magnetic suspension flywheel coordinates impulse compensation motor to carry out integrated design, can realize high-power pulse electric energy output, is therefore the ideal chose of the emission system pulse power.In addition, what super-conductive magnetic suspension flywheel stored is mechanical energy, and its property monitored and stability are far away higher than super capacitor and battery, and it is extremely many to recycle number of times, also can complete at short notice repeatedly charge and discharge process, therefore be applicable to very much having the electromagnetic propulsion system of continuous fire or mission need to use.
It is another feature of the present invention that emission system adopts full superconductor.Compared with the common electrical material such as copper, aluminium, practical superconductor has the advantage of order of magnitude formula in current density at present.With the low temperature superconducting material Nb-Ti and the Nb that commonly use 3sn is example, and its critical current density at 4.2K temperature approaches 1.5 × 10 4a/mm 2, be about 3000 times of copper.Be that the belt material of high temperature superconduct that the represents critical current density under 77K generally can reach 10 with Bi system and Y 3a/mm 2, part has exceeded 10 4a/mm 2, be about 2000 times of copper, and along with the reduction of temperature, its critical current density also can further improve, and reaches as high as about 10000 times of copper.At present, the application of the through engineering approaches of superconductor is very ripe.With Nb-Ti and Nb 3sn is that the cryogenic superconductor wire rod of representative is prepared more than length can reach several kms, and has ripe coil winding, quench detection and resist technology, and in large-scale magnet and accelerator, application is very extensive.And high temperature superconducting materia uses also comparatively maturation, common Bi based high-temperature superconductive strip product length is greater than 1000m, and electric current can reach 1000A/77K, and Y based high-temperature superconductive strip length has exceeded 100m, electric current can reach 350A/77K, meets every technical requirement of electromagnetic propulsion system completely.Y based high-temperature superconductive strip is more much lower than the price of Bi based high-temperature superconductive strip, and can be operated in liquid nitrogen temperature (77K), and for low temperature superconducting material, refrigeration and cryogenic system are simpler, and it is more convenient to apply.Superconductor is with its superior high current density characteristic, under identical electromagnetic thrust demand, for the common electrical material such as copper, aluminium, can greatly reduce propulsion system length and volume, generally can be contracted to 1/5 or following, be design, the ideal material that builds electromagnetic propulsion system.Meanwhile, superconductor self, without ohmic loss, coordinates iron-core-free design, almost there is no energy loss, and the cryogenic system of himself possesses certain thermal absorptivity, therefore without forcing heat radiation, can realize and can repeat Electromagnetic Launching in emission process.Taking high-temperature superconducting magnetic levitation technology as basis, adopt full superconductor to replace traditional electrical material of each links such as electromagnetic propulsion, impulse compensation motor and delivery of electrical energy, can effectively solve every technical barrier of traditional electrical magnetic emission system, be the ideal chose of realizing without the repeated Electro-magnetic Launcher System of ablation, high thrust, high muzzle velocity.
Summary of the invention
Object of the present invention: propose fast continuously emission system and its implementation of a kind of superconducting magnetic, effectively evade the inherent technology defect of traditional electromagnetism propulsion system, realize carrier propelled at high velocity, without ablation and can launch continuously fast.
Technical scheme: the fast continuous emission system of a kind of superconducting magnetic, comprises that high-temperature superconducting magnetic levitation subsystem, superconducting magnetic advance subsystem and superconducting magnetic levita flywheel pulse power subsystem, is characterized in that:
Described high-temperature superconducting magnetic levitation subsystem comprises floating unit and external magnetic driving source, described floating unit by low-temperature (low temperature) vessel with superconduction block material be wherein installed formed, its be launched body or carrying platform links together; Described external source is permanent magnetic guideway, and it is installed on ground or fixed pedestal conventionally, plays support suspension carrier and the effect that is launched body;
Described high-temperature superconducting magnetic levitation subsystem can be eliminated mechanical friction, avoid being launched body and advance all basic system generation ablations subsystem stator and support etc. including permanent magnetic guideway, superconducting magnetic, realizing emission system can reuse, its general principle is: utilize flux pinning characteristic and the high current density feature of superconduction block material uniqueness, form the completely stable driven suspension system of six degree of freedom with the acting in conjunction of external magnetic driving source; Rely on external magnetic driving source special magnetic field configuration, produce strong magnetic field gradient at specific direction, and then produce electromagnetic coupled effect with superconduction block material and retrain the skew of superconduction block material, realize stable suspersion; And in the direction of advance along superconduction block material without magnetic field gradient, thereby not can to motion superconduction block material cause reluctance force; Whole system is without the ACTIVE CONTROL such as position probing and feedback, and possesses compared with higher suspension rigidity, can meet the needs of different Electro-magnetic Launcher Systems;
Superconducting magnetic advances that subsystem comprises stator body, is launched body, refrigeration plant, Cryo Heat Insulation equipment and basic platform, wherein be launched body can equivalence to be considered as propulsion system mover part (but external except being launched in embodiment mono-, there is there in addition special mover, contradiction?); Described propulsion system stator body is by superconducting wire or band coiling, its current density is far away higher than traditional electrical material, coordinate iron-core-free design, can under pulse current effect, produce extremely strong high frequency travelling-magnetic-field, jointly form electromagnetic coupled system and drive body transmitting with magnetic or electrical material subsidiary on carrier; Because the current density of superconductor is high, the propulsive force density that therefore produced is far above common electrical material system; In addition, superconducting wire or band, in the time turning to stator coil winding, directly substitute iron core with non-conductive, non-magnetic high strength composite, no longer rely on iron core to gather magnetic; Superconduction stator coil, without ohmic loss, coordinates iron-core-free design can further eliminate magnetic hystersis loss, without forcing heat radiation, and can be in the short time every interior continuous transmitting; Described carrier refers to carrying platform and guided missile, aircraft or spacecraft on it; Described superconducting magnetic advances subsystem to utilize the high current density of superconductor and non-resistance characteristic to realize high thrust propelling, possesses fast emissivities continuously;
Described superconducting magnetic levita flywheel pulse power subsystem comprises super-conductive magnetic suspension flywheel, impulse compensation motor, utilize the flywheel of super-conductive magnetic suspension bearings to carry out energy storage, owing to having eliminated mechanical friction, flywheel can higher rotation speed move, and has therefore significantly promoted energy storage density; Using superconduction impulse compensation motor as pulse electric energy releasing device, and in frame for movement, carry out integrated design with fly wheel system, it combines the high rotating speed of superconduction flywheel, large energy storage capacity, the output of impulse compensation motor continuous high power and the loss-free characteristic of superconductor, make described superconducting magnetic levita flywheel pulse power subsystem realize high impulse power stage, discharge and recharge the time short, recycle number of times high;
Known whole I classes and II class superconductor before superconductor feeling the pulse with the finger-tip described above, comprises the various preparation forms such as bulk, wire rod and band;
When above-mentioned superconducting wire (band) is applied in the loop construction of propulsion system, according to the difference of superconductor, adopt different winding methods, consider the impact such as maximum curvature, insulation technology of coil; The type of cooling is liquid helium, liquid nitrogen cycle refrigeration system or refrigeration machine refrigeration, and is equipped with vacuum heat-preserving system;
Above-mentioned superconduction advances the stator coil of subsystem in the time producing strong pulsed magnetic field, also can produce higher electromagnetic induction power, thereby portion forms certain concentrated stress in coil, need the special mechanical mechanism of design to bear this electromagnetism concentrated stress, to ensure that overall structure is solid stable; This mechanical mechanism has been avoided wedge angle, acute angle etc., concentrated to prevent stress; Superconductor is wound around part need select high-strength material, avoids the excessive damage causing of stress;
In the time carrying out each part mentioned above system, need to consider the cooperation of cryogenic system, each subsystem adopts independent vacuum sealing and insulation, adjacent subsystems can share a set of refrigeration plant, as refrigeration machine and recirculated water cooling machine etc., introduce temperature monitoring and automatic control technology, ensure that superconducting coil and bulk are all the time in optimum working temperature; For low temperature superconducting material, optimum working temperature is at 4.2K and following; For high temperature superconducting materia, optimum temperature is between 30-50K;
Native system implementation method, comprises the following steps:
1, be launched before body transmitting, high-temperature superconducting magnetic levitation subsystem is introduced into duty in advance, ensures to be launched the stable suspersion of body in accelerator, avoids frictional dissipation and ablation phenomen to produce;
2, the superconducting magnetic levita fly wheel system in superconducting magnetic levita flywheel pulse power subsystem relies on impulse compensation motor that institute's store mechanical can be converted into pulse electric energy and supplies with superconducting magnetic propelling subsystem, produce strong travelling-magnetic-field, and with the electromagnetic thrust that is launched body effect and produces high force density, obtain high acceleration, in short distance, reach emission rate;
3, in emission process, according to superconducting magnetic levita flywheel energy storage number and single emission energy requirement, can realize multiple pulses energy output, coordinate to advance subsystem without the superconducting magnetic of heat radiation, realizing repeatedly can repeat its transmission;
4, after having launched, superconducting magnetic levita flywheel pulse power subsystem is connected with outside energy supplying system immediately, carries out stored energy, prepares transmitting next time.
Advantage of the present invention and beneficial effect:
Compared with prior art, advantage of the present invention and feature are:
1, reusable.The present invention adopts high-temperature superconducting magnetic levitation principle to realize the contactless transmitting of carrier, in whole emission process, carrier and stator are without any mechanical friction, ablation phenomen and the impact of traditional armature railgun are avoided, therefore propulsion system can be reused for a long time, effectively reduces system single emission cost.
2, high propulsive force density.High-speed superconducting magnetic suspension flywheel can be realized the energy storage density far above super capacitor, power density is far above battery energy storage, coordinate impulse compensation motor, can realize the pulse electric energy output of high-energy-density, and propulsion system adopts superconducting line strips to coordinate iron-core-free design, can bear compared with high impulse electric current and produce high impulse magnetic field, and then effectively promoting the electromagnetic force density of propulsion system.
3, control simply.Suspension Subsystem is complete driven suspension, without introducing any active control technology.Advance the stator of subsystem almost lossless, therefore can carry out long stator design, avoided a control difficult problem that traditional reclosing type magnetic artillery brings due to gun barrel segmentation reclosing and the restriction of power electronic devices.Whole Electro-magnetic Launcher System control technology is simple, has solved bulky, the baroque problem of traditional Electro-magnetic Launcher System, and realizability is high.
4, continuous emissivities.This Electro-magnetic Launcher System is made up of superconductor substantially, emission process almost noenergy loss produces, without configuration cooling system, and the superconducting magnetic levita flywheel energy storage system of high energy storage density and can provide required pulse electric energy for transmitting repeatedly without the superconduction impulse compensation motor of heat radiation, therefore it possesses in short-term emissivities continuously.
Brief description of the drawings
Fig. 1 is the cross section principle schematic that the embodiment of the present invention one is applied to heavily loaded Electro-magnetic Launcher System;
Fig. 2 is the cross section principle schematic that the embodiment of the present invention two is applied to underloading magnetic artillery system;
Fig. 3 is integrated system structure top view of the present invention;
Fig. 4 is the cross sectional representation of superconducting magnetic levita flywheel pulse power subsystem of the present invention.
Detailed description of the invention
In order to make the object, technical solutions and advantages of the present invention clearer, describe the present invention below in conjunction with the drawings and specific embodiments.
As shown in Figure 1, the present invention is applied to a kind of detailed description of the invention of heavily loaded Electromagnetic Launching to embodiment mono-: a kind of superconducting magnetic emission system cross section that can be used for the heavy aerospace vehicle such as booster rocket or guided missile.In figure, 1 is the combination of high-temperature superconducting block in high-temperature superconducting magnetic levitation subsystem and low-temperature (low temperature) vessel; In figure, 2 for being launched the cross section that body is large aerospace spacecraft; In figure, 3 is the permanent magnetic guideway of high-temperature superconducting magnetic levitation subsystem; In figure, 4 is the mover part in superconducting magnetic propelling subsystem; The 5 removable holder carrying platforms for holder year aerospace vehicle in figure; In figure, 6 is the stationary part in superconducting magnetic propelling subsystem; In figure, 7 is basic platform.
In embodiment shown in Fig. 1, the workflow of each part is: be launched aerospace vehicle 2 and install in advance and be fixed to removable holder carrying platform 5, this platform 5 carries out integrated design with high-temperature superconducting block 1 combination, and high-temperature superconducting block 1 is built in low-temperature (low temperature) vessel.Jointly form super-conductive magnetic suspension subsystem by high-temperature superconducting block combination 1 and permanent magnetic guideway 3, rely on the electromagnetic coupled effect between high-temperature superconducting block and permanent magnetic guideway to maintain holder carrying platform 5 stable suspersions.Superconducting magnetic propulsion system stationary part 6 advances winding by superconducting wire or band coiling, in the time that carrier is launched, advance winding to obtain pulse electric energy input from outside, produce flash travelling-magnetic-field, produce strong electromagnetic propulsive force with 4 actings in conjunction of propulsion system mover part, drive holder carrying platform and carrier to move.In the time accelerating to demand speed, aerospace vehicle 2 departs from holder carrying platform 5 automatically, along its predetermined launching track flight.Basic platform 7 need carry out special structural design, to bear active force after produce in emission process strong, also can supporting design Mechatronic Systems to regulate the level inclination of this basic platform, and then change the vertical emission angle of aerospace vehicle.
The super-conductive magnetic suspension subsystem of the present embodiment is made up of two guide rails of symmetry, the suspending power that can provide is larger, be applicable to holder and carry the aerospace vehicle of the large quality such as rocket or guided missile, and removable holder carrying platform is not launched with aerospace vehicle, therefore can recycle, effectively reduce single emission cost.The not shown superconductor temperature protection of the present embodiment system, and relevant machinery is fixed and power conduction mechanism.
Embodiment bis-is applied to a kind of detailed description of the invention of underloading Electromagnetic Launching for the present invention, as shown in Figure 2, and a kind of superconducting magnetic gun system cross section that can be used for launching less quality body.1 is depicted as superconducting magnetic big gun gun barrel; 3 are depicted as permanent magnetic guideway; 6 are depicted as superconducting magnetic propulsion system stationary part; 4 are depicted as body (being equivalent to mover); 5 are depicted as air gap between superconducting magnetic big gun gun barrel and body, body shown in 4 is made up of high temperature superconducting materia and composite, and wherein body shell is block high temperature superconducting materia, for generation of high density current vortex, inside stuffing is high strength complex fiber material, for reinforcing body intensity.
The course of work of the big gun of superconducting magnetic shown in Fig. 2 is: body 4 carries out cooling in advance, allows its shell be that high-temperature superconducting block enters duty.Body 4 and the common composition Suspension Subsystem of permanent magnetic guideway 3, rely on the special magnetic field configuration between the distinctive flux pinning characteristic of high-temperature superconducting block and permanent magnetic guideway to realize body stable suspersion.In the time having mission need, superconducting magnetic advances the stationary part 6 of subsystem to obtain pulse electric energy input from outside, at the interior generation flash of air gap 5 travelling-magnetic-field, this travelling-magnetic-field and body 4 shells are that high-temperature superconducting block produces electromagnetic induction effect jointly, make body obtain electromagnetic thrust.Because the critical current density of high-temperature superconducting block is high, and propulsion system stationary part 6 can flash travelling-magnetic-field, and therefore body can obtain high propulsive force and acceleration, realizes propelled at high velocity in short distance.In addition, body 4 shells are that high-temperature superconducting block does not have resistance, can not produce ohmic loss, and therefore whole accelerator efficiency is higher.After having launched, superconducting magnetic propulsion system stationary part 6, without forcing heat radiation can carry out immediately pulse electric energy input next time, is realized the continuous transmitting of body.It is own that in this embodiment, propulsion system mover is exactly body 4, and it is high-temperature superconducting block, under operating temperature, can be equivalent to desired electrical conductor.That is to say, in the present embodiment, body, as a part for floating unit, as a part for electromagnetic propulsion subsystem, had been both again body to be launched again simultaneously.
The present embodiment compact conformation, whole emission process body, without any mechanical friction, can solve the ablation problem of traditional armature railgun, and therefore this magnetic artillery can be reused; Between body and gun barrel, air gap is less, and the service efficiency of excitation field is higher, and the accelerator of body is induction propelling, does not need body to position and FEEDBACK CONTROL, therefore can evade a control difficult problem for traditional reclosing type magnetic artillery.In addition, owing to adopting full superconductor, emission process is without heat radiation, and superconduction flywheel accumulator coordinates impulse compensation motor that repeatedly flash electric energy can be provided in short-term, realizes repeatedly continuous fire, makes this structure magnetic artillery possess warfighting capabilities.The not shown superconduction flywheel accumulator of the present embodiment, superconductor temperature protection system, and relevant machinery is fixed and power conduction mechanism.
Fig. 3 illustrates the integrated system structure top view of the present invention in the time of practical application.Comprise the superconducting magnetic levita flywheel pulse power 10, be launched body 2, the electrical connection between the pulse power and superconduction propulsion system and power electronic equipment 11; The linear pattern accelerating sections 12 that permanent magnetic guideway and propulsion system stator form; The round accelerating sections 13 that permanent magnetic guideway and propulsion system stator form.12, the cross section of the accelerating sections shown in 13 can select to be designed to the transmitting of heavy duty or underloading, i.e. any one of Fig. 1 or cross section embodiment illustrated in fig. 2.Accelerating sections shown in 12 and 13 is all built-in with superconducting magnetic and advances subsystem.
The workflow of integrated system shown in Fig. 3 is: before transmitting or transmitting gap, the superconducting magnetic levita flywheel pulse power 10 (flywheel accumulator and the design of superconduction impulse compensation motor integration) obtains electric energy and stores with the rotation function of flywheel from outside, in the time having mission need, be that pulse electric energy supply propulsion system is used by superconduction impulse compensation motor by stored kinetic transformation.Electrical connection and power electronic equipment 11 are guaranteed the safe transmission of pulse energy, and DC pulse electric energy is modulated to the alternating-current pulse electric energy under the needed assigned frequency of superconduction propulsion system.Propulsion system in linear pattern accelerating sections 12, under pulse electric energy drives, is accelerated to be launched body 2 to command speed.As too short in acceleration distance or propulsive force index can not satisfy the demands, can in the time accelerate, allow and be launched body 2 and cut round accelerating sections 13 from linear pattern accelerating sections 12, acceleration circulates, round accelerating sections 13 circulate accelerate advantage be, the induction type that propulsion system in this section can be designed to lower acceleration index accelerates, be launched body every circulation in this accelerating sections and can obtain a certain speed increment in, accelerate to reach command speed by repeatedly circulating, then cut linear pattern accelerating sections 12 and finally launch.
The feature of integrated system shown in Fig. 3 is can free hold and the acceleration index that regulates propulsion system.Thereby adapt to different transmitting occasions.When for underloading transmitting and muzzle velocity be not when high, can a use figure shown in linear pattern accelerating sections 12 accelerate; When being, when heavy duty is launched or muzzle velocity demand is higher, can use the straight line one circle circulation aero modes of 12,13 compositions in figure, thereby effectively reduce the power demand of propulsion system, less system difficulty and expense on the whole.The concrete structure of the not shown superconduction flywheel of the present embodiment pulse power, power electronic equipment, superconductive suspension and superconduction propulsion system.
Fig. 4 is the cross sectional representation of superconducting magnetic levita flywheel pulse power subsystem of the present invention.In figure, 20 is top superconducting magnetic levita bearing, in figure, 21 is bottom superconducting magnetic levita bearing, two cover magnetic suspension bearing systems are for realizing the stable suspersion of flywheel rotor, and owing to having eliminated mechanical friction completely, can realize the high-speed cruising of flywheel rotor, more than rotating speed can reach 50000 revs/min (rpm), far away higher than the fly wheel system that uses standard machinery bearing or electromagnetic suspension bearing, and without external energy input, specific energy loss when its energy storage is lower, almost suitable with battery.In figure, 22 is main shaft, adopts alloy material to make, for connecting flywheel body and the rotating shaft of superconducting magnetic levita bearing.In figure, 23 is alloy wheel hub, and it can adopt high-intensity aluminum alloy materials, for wound composite.In figure, 24 is flywheel body, and it can adopt carbon fiber, graphite fibre or glass fibre, coordinates layering winding or epoxy impregnation processes to form, and being specifically wound around the number of plies can be according to actual energy storage capacity demand calculative determination, and the embodiment of the present invention is 3 layers and is wound around signal.In figure, 25 is the stationary part of impulse compensation motor, it adopts superconductor coiling, its current density is far away higher than conventional electrical materials such as copper, aluminium, silver and without ohmic loss, the magnetic field intensity producing is higher, can coordinate iron-core-free design, further eliminate magnetic hystersis loss, therefore entirety is without forcing heat radiation.In figure, the electric mover of impulse compensation shown in 26 adopts neodymium iron boron (NdFeB) permanent-magnet material, carries out integrated design with 23 alloy wheel hubs in figure.In figure 27 and figure in 28 dampers that are respectively bottom and top, for flywheel rotor from the static balance and stability that accelerates to the operating rate initial stage.In figure, 29 is base, and 30 is protecting sheathing, and because flywheel rotor need to move under vacuum environment, therefore base and protecting sheathing are mechanically realized and being closely cooperated, and ensures inner space vacuum demand.
The workflow of the flywheel of superconducting magnetic levita shown in Fig. 4 pulse power is: the pulse power need to first carry out stored energy, by outside input current to impulse compensation motor stator 25, produce travelling-magnetic-field, drive impulse compensation electric mover 26 and flywheel rotor 22,23 and 24 to rotate, thereby the mechanical energy when electric energy conversion of external world's input is flywheel rotor High Rotation Speed is stored.In the time having mission need, now in figure, the 25 and 26 impulse compensation motors that form proceed to power generation mode, i.e. pulsed discharge pattern, and the inductance cyclically-varying that relies on the particular configuration of impulse compensation motor stator 25 windings to bring realizes the release of pulse electric energy.Because stator structure and the implementation method of conventional impulse compensation motor are more, and be current techique, therefore not shown its concrete structure of the present embodiment.After energy has discharged, now the rotating speed of flywheel rotor can be reduced to certain level, and now in figure, the 25 and 26 impulse compensation motors that form proceed to electric model, is rotated with flywheel driven by external world's input electric energy, repeats the mode of operation of energy storage phase.Due to the free suspended state of flywheel under vacuum environment, without any mechanical friction and air drag, and impulse compensation motor stator is by superconductor coiling, there is no ohmic loss and iron core magnetic hystersis loss, therefore whole system does not almost have ability loss and heat generation in charge and discharge process, therefore without forcing heat radiation, can discharge and recharge fast, for continuous Electromagnetic Launching provides pulse electric energy.

Claims (4)

1. the fast continuous emission system of superconducting magnetic, comprises that high-temperature superconducting magnetic levitation subsystem, superconducting magnetic advance subsystem and superconducting magnetic levita flywheel pulse power subsystem, is characterized in that:
Described high-temperature superconducting magnetic levitation subsystem comprises floating unit and external magnetic driving source, described floating unit by low-temperature (low temperature) vessel with superconduction block material be wherein installed formed, its be launched body or carrying platform links together; Described external source is permanent magnetic guideway, and it is installed on ground or fixed pedestal conventionally, plays support suspension carrier and the effect that is launched body;
Described superconducting magnetic advances subsystem to comprise stator body, is launched body, refrigeration plant, Cryo Heat Insulation equipment and basic platform; Described propulsion system stator body, by superconducting wire or band coiling, coordinates iron-core-free design, utilizes the high current density of superconductor and non-resistance characteristic to realize high thrust propelling, possesses fast emissivities continuously;
Described superconducting magnetic levita flywheel pulse power subsystem comprises super-conductive magnetic suspension flywheel, impulse compensation motor, utilize the flywheel of super-conductive magnetic suspension bearings to carry out energy storage, using superconduction impulse compensation motor as pulse electric energy releasing device, and in frame for movement, carry out integrated design with fly wheel system, make described superconducting magnetic levita flywheel pulse power subsystem realize high impulse power stage, discharge and recharge the time short, recycle number of times high.
2. the fast continuous emission system of superconducting magnetic according to claim 1, is characterized in that, known whole I classes and II class superconductor before described superconductor feeling the pulse with the finger-tip, comprises the various preparation forms such as bulk, wire rod and band.
3. the fast continuous emission system of superconducting magnetic according to claim 1, it is characterized in that, described superconduction advances the stator coil of subsystem can produce higher electromagnetic induction power in the time producing strong pulsed magnetic field, need the special mechanical mechanism of design to bear this electromagnetism concentrated stress, this mechanical mechanism has been avoided wedge angle, acute angle etc., concentrated to prevent stress.
4. an implementation method for the fast continuous emission system of superconducting magnetic as described in claim 1,2 or 3, is characterized in that, comprises the following steps:
(1) be launched before body transmitting, high-temperature superconducting magnetic levitation subsystem is introduced into duty in advance, ensures to be launched the stable suspersion of body in accelerator, avoids frictional dissipation and ablation phenomen to produce;
(2) the superconducting magnetic levita fly wheel system in superconducting magnetic levita flywheel pulse power subsystem relies on impulse compensation motor that institute's store mechanical can be converted into pulse electric energy and supplies with superconducting magnetic propelling subsystem, produce strong travelling-magnetic-field, and with the electromagnetic thrust that is launched body effect and produces high force density, obtain high acceleration, in short distance, reach emission rate;
(3) in emission process, according to superconducting magnetic levita flywheel energy storage number and single emission energy requirement, can realize multiple pulses energy output, coordinate to advance subsystem without the superconducting magnetic of heat radiation, realizing repeatedly can repeat its transmission;
(4) after having launched, superconducting magnetic levita flywheel pulse power subsystem is connected with outside energy supplying system immediately, carries out stored energy, prepares transmitting next time.
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CN105444614A (en) * 2015-12-07 2016-03-30 华南理工大学 Circulating cooling system for railgun rail and cooling method
CN109297356A (en) * 2018-11-02 2019-02-01 中国运载火箭技术研究院 A kind of carrier rocket Electro-magnetic Launcher System and method
CN110411276A (en) * 2018-04-27 2019-11-05 中国航天科工飞航技术研究院(中国航天海鹰机电技术研究院) A kind of carrier rocket emission system based on magnetic suspension electromagnetic booster
CN110406697A (en) * 2018-04-27 2019-11-05 中国航天科工飞航技术研究院(中国航天海鹰机电技术研究院) A kind of vehicle launch system based on magnetic suspension electromagnetic booster
CN110406688A (en) * 2018-04-26 2019-11-05 中国航天科工飞航技术研究院(中国航天海鹰机电技术研究院) For accelerating the magnetic suspension electromagnetic propulsion integration of aircraft to deliver sledge vehicle
CN111846285A (en) * 2019-04-24 2020-10-30 中国航天科工飞航技术研究院(中国航天海鹰机电技术研究院) Supersonic transmitting system based on electric and pinning hybrid magnetic suspension

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CN105444614A (en) * 2015-12-07 2016-03-30 华南理工大学 Circulating cooling system for railgun rail and cooling method
CN110406688A (en) * 2018-04-26 2019-11-05 中国航天科工飞航技术研究院(中国航天海鹰机电技术研究院) For accelerating the magnetic suspension electromagnetic propulsion integration of aircraft to deliver sledge vehicle
CN110406688B (en) * 2018-04-26 2020-12-08 中国航天科工飞航技术研究院(中国航天海鹰机电技术研究院) Magnetic suspension electromagnetic propulsion integrated carrying sledge for accelerating aircraft
CN110411276A (en) * 2018-04-27 2019-11-05 中国航天科工飞航技术研究院(中国航天海鹰机电技术研究院) A kind of carrier rocket emission system based on magnetic suspension electromagnetic booster
CN110406697A (en) * 2018-04-27 2019-11-05 中国航天科工飞航技术研究院(中国航天海鹰机电技术研究院) A kind of vehicle launch system based on magnetic suspension electromagnetic booster
CN109297356A (en) * 2018-11-02 2019-02-01 中国运载火箭技术研究院 A kind of carrier rocket Electro-magnetic Launcher System and method
CN109297356B (en) * 2018-11-02 2021-02-09 中国运载火箭技术研究院 Carrier rocket electromagnetic launching system and method
CN111846285A (en) * 2019-04-24 2020-10-30 中国航天科工飞航技术研究院(中国航天海鹰机电技术研究院) Supersonic transmitting system based on electric and pinning hybrid magnetic suspension

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