CN106697318A - Electromagnetic catapult for carrier aircraft - Google Patents
Electromagnetic catapult for carrier aircraft Download PDFInfo
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- CN106697318A CN106697318A CN201611121603.2A CN201611121603A CN106697318A CN 106697318 A CN106697318 A CN 106697318A CN 201611121603 A CN201611121603 A CN 201611121603A CN 106697318 A CN106697318 A CN 106697318A
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- rotor
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- 238000004146 energy storage Methods 0.000 claims abstract description 147
- 238000001816 cooling Methods 0.000 claims abstract description 51
- 238000006243 chemical reaction Methods 0.000 claims description 53
- ZZUFCTLCJUWOSV-UHFFFAOYSA-N furosemide Chemical compound C1=C(Cl)C(S(=O)(=O)N)=CC(C(O)=O)=C1NCC1=CC=CO1 ZZUFCTLCJUWOSV-UHFFFAOYSA-N 0.000 claims description 37
- 238000005339 levitation Methods 0.000 claims description 18
- 230000001360 synchronised effect Effects 0.000 claims description 17
- 230000005540 biological transmission Effects 0.000 claims description 15
- 239000000725 suspension Substances 0.000 claims description 13
- 239000002826 coolant Substances 0.000 claims description 12
- 229910000639 Spring steel Inorganic materials 0.000 claims description 9
- 238000009434 installation Methods 0.000 claims description 7
- 239000012530 fluid Substances 0.000 claims description 6
- 230000033001 locomotion Effects 0.000 claims description 6
- 238000001514 detection method Methods 0.000 claims description 4
- 230000007704 transition Effects 0.000 claims description 4
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- 230000005611 electricity Effects 0.000 claims description 2
- 238000012544 monitoring process Methods 0.000 claims description 2
- 230000001737 promoting effect Effects 0.000 claims description 2
- 238000010586 diagram Methods 0.000 description 4
- 230000007246 mechanism Effects 0.000 description 4
- 238000013016 damping Methods 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 239000000969 carrier Substances 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000007667 floating Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000002834 transmittance Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
- B64F1/06—Ground or aircraft-carrier-deck installations for launching aircraft using catapults
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The invention discloses an electromagnetic catapult for a carrier aircraft. The electromagnetic catapult comprises a power supply, a flywheel energy storage system, a rectifier, two parallel guide rails, an armature and a control system. The flywheel energy storage system is electrically connected with the power supply to form a charging circuit; the armature makes contact with the parallel guide rails and can move along with the parallel guide rails, the flywheel energy storage system, the rectifier and the parallel guide rails are electrically connected with the armature to form a power supply circuit, the flywheel energy storage system comprises an energy storage device, a vacuumizing device which is connected with a suction hole of a shell of the energy storage device and can vacuumize a closed space formed by the shell in an enclosing mode and a cooling device for cooling the energy storage device; the control system is connected with the flywheel energy storage system, the rectifier and the parallel guide rails. The electromagnetic catapult for the carrier aircraft is used for solving the technical problems that due to the fact that an energy storage device of an existing electromagnetic catapult for the carrier aircraft is not stable enough in structure, low in energy storage density and low in stored energy, the instantaneous output power is low, and by adopting the flywheel energy storage system as the energy storage device, the aircraft can obtain greater propelling force when the aircraft takes off.
Description
Technical field
Electromagnetic force be the present invention relates to the use of for aircraft accelerates.Specially a kind of aircraft carrier Electromagnetical ejector.
Background technology
Aircraft on aircraft carrier is when especially heavy airplane takes off, it is necessary to make aircraft in very short distance using aircraft catapult
Takeoff speed is inside accelerated to, so as to shorten the length of slideway on the limited aircraft carrier in space.Generally make to fly using Electromagnetical ejector
Machine takes off, its principle for using electromagnetic force for aircraft provides boosting power.The energy of current Electromagnetical ejector uses common energy storage
Device, its energy storage density is low, energy storage capacity is small causes moment power output low, and the bottle of bigger boosting power is obtained as restriction aircraft
Neck.
The content of the invention
Present invention solves the technical problem that being to overcome existing aircraft carrier Electromagnetical ejector energy storage device moment to export
Power ratio is relatively low, the small technical problem of the boosting power for causing aircraft to obtain, there is provided a kind of aircraft carrier Electromagnetical ejector, using winged
Wheel energy-storage system makes aircraft obtain bigger boosting power as energy storage device.
Aircraft carrier Electromagnetical ejector of the invention, including：
Power supply,
Flywheel energy storage system, the flywheel energy storage system constitutes charging circuit with power electric connection,
Rectifier, the rectifier electrically connects the electric current provided the flywheel energy storage system with the flywheel energy storage system
Carry out rectification,
Closed slide, electrically connects with the rectifier,
Armature, the armature and the closed slide conductive contact, the flywheel energy storage system, rectifier, closed slide
It is electrically connected to form power supply circuit with armature, when power supply circuit is powered, the armature is moved along the closed slide, while promoting
The aircraft movement,
Control system, the control system be connected with the flywheel energy storage system can control the flywheel energy storage system according to
The parameter operation of setting, the control system is connected the parameter fortune that can control the rectifier according to setting with the rectifier
OK, the control system is connected the current parameters after can monitoring rectification with the closed slide；
The flywheel energy storage system includes energy storage device, and the energy storage device includes housing, flywheel energy storage rotor, magnetic suspension
Device and energy conversion device,
Upper end cover and consolidate with the side wall that the housing is fixed and be tightly connected including cylindrical lateral wall and the side wall
Bottom end cover that is fixed and being tightly connected, the housing is provided with aspirating hole,
The flywheel energy storage rotor is located in the housing, and the flywheel energy storage rotor includes,
Rotary shaft, is the solid steel shaft being vertically arranged,
First wheel, the first wheel is made up of spring steel, and being enclosed within the rotary shaft can be in the band of the rotary shaft
With the rotary shaft synchronous rotary under dynamic, the outer rim that the first wheel has discoid body, the discoid body is rolled over to one lateral bending
Abutting part is formed, the position that the abutting part is connected with the discoid body is provided with stress and slows down groove, the plate-like of the first wheel
Body is inclined to edge from middle part relative to the vertical plane perpendicular to the rotary shaft, and direction forms the side of the abutting part
Incline,
Foreign steamer, the foreign steamer is tubbiness, is enclosed within the first wheel, and its inwall is outer with the first wheel abutting part
Wall is engaged；
The magnetic levitation system is located in the housing for supporting the upper end of the rotary shaft of the flywheel and allowing described
Rotary shaft rotates relative to the magnetic levitation system,
The energy conversion device is located in the housing and positioned at the lower section of the flywheel, the energy conversion device bag
Include the stator formed by magnetic pole circuit coiling, the rotor that can be rotated relative to the stator and the biography that be rotated by the rotor
Moving axis, the power transmission shaft is fixedly connected and synchronous rotary with the rotating shaft coaxle of the flywheel, and the energy conversion device is also wrapped
Include cooling duct；
The flywheel energy storage system also includes,
Vacuum extractor, the vacuum extractor is connected with the aspirating hole of the housing of the energy storage device can be to the housing
The closing space for surrounding is vacuumized；
Cooling device, the cooling device includes that the fluid reservoir and the fluid reservoir of storage coolant and the energy turn
Connecting tube and make the coolant logical in the cooling for the coolant provides power that the cooling duct of changing device connects
The cooling pump of road interior circulation.
Preferably, the flywheel energy storage system also includes：
Vacuum control unit, is connected to control the operation of the vacuum extractor with the vacuum extractor；
Cooling controller, is connected to control the cooling device with the cooling device；
Energy conversion control device, is connected with the energy conversion device, can control the energy conversion device and is in and fills
Electricity or power supply state, when the magnetic pole circuit and charging circuit are connected to be disconnected with the power supply circuit simultaneously, the energy
The rotor of conversion equipment is rotated under the magneticaction of stator so as to drive the flywheel energy storage rotor to revolve by the power transmission shaft
Turn, the energy conversion device is stored as the rotating mechanical energy that motor converts electrical energy into the flywheel energy storage rotor
Come, the energy conversion device is in charged state, when the magnetic pole circuit and the charging circuit disconnect simultaneously with the confession
When circuit is connected, the flywheel energy storage rotor by the power transmission shaft drive the rotor of the energy conversion device to rotate so as to
The magnetic pole circuit is set to produce electric current, the energy conversion device is as generator by the rotating machinery of the flywheel energy storage rotor
Electric energy can be converted into and supply the power supply circuit, the energy conversion device is in power supply state.
Preferably, each described energy storage device of the flywheel energy storage system sets detection energy conversion device temperature
Temperature sensor, the temperature sensor is also connected with the cooling controller and is transmitted with by the temperature of the temperature sensor
To the cooling controller, the cooling controller makes according to the operation of the Temperature numerical control cooling device for receiving
The temperature control of the energy storage device is within the temperature range of setting.
Preferably, each energy storage device of the flywheel energy storage system is provided for detecting the air pressure of enclosure interior air pressure
Sensor, the baroceptor is also connected with the vacuum control unit and sends institute to by the data of the baroceptor
Vacuum control unit is stated, the vacuum control unit makes institute according to the operation of the Temperature numerical control vacuum extractor for receiving
The air pressure stated in the housing of energy storage device is controlled in the air pressure range of setting.
Preferably, by round-corner transition between the abutting part and the discoid body, the stress slows down groove positioned at institute
State on the outer wall of fillet.
Preferably, the inwall of the foreign steamer is provided with the position that the outer wall with the first wheel abutting part is engaged
The first fitting projection circumferentially, in a state where mounting is completed, the abutting part of the first wheel is matched somebody with somebody with described first
Raised tight fit is closed, at least one end of first fitting projection is provided with the guiding first wheel in the foreign steamer along axis
The installation guiding slope of relative motion, at least one end of the first fitting projection is one end that the abutting part is first contacted when installing.
Preferably, the first wheel also includes that be enclosed within the rotary shaft can be with the peace of the rotary shaft synchronous axial system
Dress axle sleeve, the discoid body is located at the outside of the mounting sleeve and is integrally formed with the mounting sleeve.
Preferably, the flywheel also includes the second wheel hub above the first wheel, second wheel hub by
Spring steel is made, and is enclosed within the rotary shaft, and can under the drive of the rotary shaft with the rotary shaft synchronous rotary, it is described
The planform of the second wheel hub is identical with the planform of the first wheel, and in the state of assembling is completed, described first
The discoid body of wheel hub is identical with the incline direction of the discoid body of second wheel hub, the abutting part of second wheel hub be arranged on
The second fitting projection tight fit on foreign steamer inwall, the flywheel also includes positioning shaft sleeve, and the positioning shaft sleeve is enclosed within the rotation
In rotating shaft, and between the first wheel and the second wheel hub, the lower end of the rotary shaft has to be used for the first round
The shaft shoulder that the lower end of hub is positioned.
Preferably, the magnetic levitation system includes at least one magnetic suspension bearing, each magnetic suspension bearing includes fixing
In the rotary shaft and can with the rotor magnet of the rotary shaft synchronous rotary and with the relatively-stationary stator magnet of the housing
Body, the rotor magnet is relative up and down with the stator magnet, and the rotor magnet face relative with the stator magnet is
Heteropole.
Preferably, the rotor magnet is embedded on rotor carrier, the rotor carrier is fixed in the rotary shaft,
The stator magnet is embedded on stator carrier, and the stator carrier is fixed on the mounting bracket fixed with the housing, described
The rotor carrier of magnetic suspension bearing is threadedly secured in the rotary shaft.
Aircraft carrier Electromagnetical ejector of the invention compared with prior art, has the advantages that：
1st, the flywheel energy storage rotor of the flywheel energy storage system of aircraft carrier Electromagnetical ejector of the invention, its first wheel
The outer rim of discoid body is bent to form abutting part to one side, and abutting part offsets in the presence of pretightning force with the inwall of foreign steamer.The
The discoid body of one wheel hub from middle part to edge relative to the vertical planar tilt perpendicular to rotary shaft, and towards forming the one of abutting part
Roll oblique.When first wheel and foreign steamer rotate at a high speed, foreign steamer can produce outside expansion, the first round under the influence of centrifugal force
Although the centrifugal force that hub is subject to is less than the centrifugal force that foreign steamer is subject to, because the outer rim of first wheel has been bent into abutting part, and
Discoid body inclined design, discoid body and abutting part produce the dilatating and deformable of radial direction after by centrifugal force.So as to finally produce with
The consistent radial deformation of foreign steamer, abutting part can be adjacent to the inwall of foreign steamer, keep the pretightning force with foreign steamer.By keeping higher
Pretightning force improves the rated speed of flywheel, improves the energy storage density and energy storage capacity of flywheel energy storage system so as to improve its wink
Between power output, aircraft is obtained bigger boosting power.The abutting part of flywheel energy storage rotor is provided with the junction of discoid body should
Power slows down groove, and stress slows down groove and can reduce stress, prevents from being damaged because stress is too big herein.Meanwhile, flywheel energy storage system is also
Vacuum extractor and cooling device are provided with, vacuum extractor is vacuumized to the space that the housing of energy accumulation device for fly wheel is surrounded so that
Flywheel energy storage rotor rotates in vacuum environment, reduces the resistance of rotation, so as to improve the kinetic energy of flywheel storage.Cooling dress
Put and energy storage device is cooled down, the temperature of the energy conversion device of energy storage device is reduced, to ensure its normal operation.
2nd, the flywheel energy storage system of aircraft carrier Electromagnetical ejector of the invention also includes vacuumizing control device, cooling control
Device processed and energy conversion control device, realize vacuumize, cool down and energy conversion automatically control so that flywheel energy storage system
The operation of system is more intelligent and more accurate.
Brief description of the drawings
Fig. 1 is the composition schematic diagram of the aircraft carrier Electromagnetical ejector of one embodiment of the invention.
Fig. 2 is the structural representation of the flywheel energy storage system of the aircraft carrier Electromagnetical ejector of one embodiment of the invention.
Fig. 3 is cutd open for the energy storage device of the flywheel energy storage system of the aircraft carrier Electromagnetical ejector of one embodiment of the invention
Depending on structural representation.
Fig. 4 is the cross section structure diagram of the flywheel energy storage rotor of the energy storage device shown in Fig. 3.
Fig. 5 is the enlarged diagram of part A in Fig. 4.
Fig. 6 is the magnetic levitation system and the enlarged diagram of axial direction positioning device of the energy storage device in Fig. 4.
Reference
1 power supply；
2 flywheel energy storage systems,
21 energy storage devices,
211 flywheel energy storage rotors, 2111 rotary shafts, 21,111 first shaft shoulders, 21,112 second shaft shoulders, 2112 first wheels,
21121 discoid bodies, 21122 abutting parts, 21123 mounting sleeves, 21124 stress slow down groove, 2113 foreign steamers, 21,131 first cooperations
Projection, 21132 installation guiding slopes, 21133 fillets, 21,134 second fitting projections, 2,114 second wheel hubs, 21141 discoid bodies,
21142 abutting parts, 21143 mounting sleeves, 2115 vertical planes, 2116 positioning shaft sleeves,
212 housings, 2121 side walls, 2122 upper end covers, 2123 bottom end covers, 2124 aspirating holes,
213 magnetic levitation systems, 2131 magnetic suspension bearings, 21311 rotor magnets, 21312 stator magnets, 21313 rotors are carried
Body, 21314 stator carriers, 21315 mounting brackets, 2132 safety bearings, 2133 axial direction positioning devices, 21331 thimbles,
214 energy conversion devices, 2141 power transmission shafts,
215 damping mechanisms,
22 vacuum extractors,
23 vacuum control units,
24 cooling devices,
25 cooling controllers,
26 energy conversion control devices；
3 guide rails；
4 armatures；
5 rectifiers；
6 control systems；
7 aircrafts.
Specific embodiment
Fig. 1 is the structural representation of the aircraft carrier Electromagnetical ejector of one embodiment of the invention, as shown in figure 1, aircraft carrier
Aircraft Electromagnetical ejector includes power supply 1, flywheel energy storage system 2, rectifier 5, closed slide 3, armature 4 and control system 6.Its
In, power supply 1 is the power supply on aircraft carrier, can obtain electric energy using various generation modes.The flywheel energy storage system 2 and power supply 1
Be electrically connected to form charging circuit.
Rectifier carries out rectification to the electric current that flywheel energy storage system 2 is provided, and parallel by being supplied to through the electric current of over commutation
Guide rail 3.Closed slide is two parallel guide rails 3, one end of the armature 4 and wherein one guide rail conductive contact, armature 4
The other end and another guide rail conductive contact, and armature can move along the closed slide.The flywheel energy storage system 2, rectification
Device 5, closed slide 3 and armature 4 are electrically connected to form power supply circuit.When charging circuit is powered and power supply circuit disconnects, power supply 1
Charged to flywheel energy storage system 2.When charging circuit is disconnected, and power supply circuit is connected, the moment in the presence of Lorentz force of armature 4
Speed very high is accelerated to so as to for the aircraft 7 provides huge boosting power, be allowed to accelerated to along the closed slide 3
Rapidly spend.
Fig. 2 is the structural representation of the flywheel energy storage system of the aircraft carrier Electromagnetical ejector of one embodiment of the invention,
As shown in Fig. 2 flywheel energy storage system 2 includes energy storage device 21, vacuum extractor 22 and cooling device 24, wherein energy storage device 21
Electric energy for storing the offer of power supply 1, the flywheel energy storage system 2 preferably comprises the 2-16 energy storage device 21, at this
In embodiment, flywheel energy storage system 2 includes 12 energy storage devices 21, and energy storage device 21 can be embedded in underground.Vacuum extractor
22 are used to vacuumize energy storage device 21, and cooling device 24 is used to cool down energy storage device 21.
The structure of the energy storage device 21 is as shown in figure 3, including housing 212, flywheel energy storage rotor 211, magnetic levitation system
213 and energy conversion device 214.The housing 212 includes that cylindrical lateral wall 2121 and the side wall 2121 are fixed and seal company
The bottom end cover 2123 that the upper end cover 2122 and the side wall 121 for connecing are fixed and be tightly connected, the housing 212 is provided with aspirating hole
2124.In the present embodiment, aspirating hole 2124 is located on bottom end cover 2123.In the state of the operation of energy storage device 21, housing 212
It is inside vacuum, prevents the rotation of the flywheel energy storage 211 that air is pointed in the housing 212 from producing resistance, so that flywheel
Energy storage rotor 211 obtains rotating speed as high as possible.
As shown in figure 4, flywheel energy storage rotor 211 includes rotary shaft 2111, first wheel 2112 and foreign steamer 2113.Wherein,
Rotary shaft 2111 is the solid steel shaft being vertically arranged.The first wheel 2112 is made up of spring steel, is enclosed within the rotary shaft
On 2111, the first wheel 2112 can under the drive of the rotary shaft 2111 with the synchronous rotary of the rotary shaft 2111.Institute
First wheel 2112 is stated with discoid body 21121, the outer rim of the discoid body 21121 is bent to form abutting part to one side
21122, the inwall of the outer wall of abutting part 21122 with foreign steamer 2113 in the presence of pretightning force offsets.As shown in figure 5, in bending
Place is to set stress at position that abutting part 21122 is connected with discoid body 21121 to slow down groove 21124, and stress slows down groove 21124 can
Reduce stress, prevent from being damaged because stress is too big herein.
The discoid body 21121 of first wheel 2112 is from middle part to edge relative to the vertical plane perpendicular to rotary shaft 2111
Incline, and inclined towards the side for forming abutting part 21122, it is tapered.The inclined design of discoid body 21121 is not compared to inclining
Situation, can more play the resiliency characteristics of spring steel.In the state of assembling or at a high speed rotation, if without inclined design, bullet
The discoid body that spring steel is made only does flexible motion, and can not play the advantage of the anti-surrender of its elastic force.Preferably, the plate-like
Body 21121 is 5 ° -15 ° relative to the inclined angle of vertical plane 2115 perpendicular to the rotary shaft 2111.In the present embodiment
In, discoid body 21121 is 10 ° relative to the inclined angle of vertical plane 2115 perpendicular to the rotary shaft 2111.
When first wheel 2112 and foreign steamer 2113 rotate at a high speed, foreign steamer 2113 can be produced outwards under the influence of centrifugal force
Displacement, although the centrifugal force that first wheel 2112 is subject to is less than the centrifugal force that foreign steamer 2113 is subject to, due to first wheel
2112 outer rim has been bent into abutting part, and discoid body inclined design, and discoid body and abutting part produce footpath after by centrifugal force
To dilatating and deformable, so as to finally produce the radial deformation consistent with foreign steamer, abutting part 21122 can be with the inwall of foreign steamer 2113 patch
Tightly, the pretightning force with foreign steamer 2113 is kept.
Compared to existing aircraft carrier ejector, the flywheel of the energy storage device of aircraft carrier Electromagnetical ejector of the invention is stored up
The wheel hub of energy rotor 211 increases the adhesion with foreign steamer 2113, makes the moment of torsion of transmission bigger.What first wheel 2112 was set supports
The material i.e. spring steel that socket part and first wheel 2112 are used supports the change of the radial direction of the generation of first wheel 2112 well
Shape, it is achieved thereby that under the rotation of high speed, big pretightning force can be still kept between first wheel 2112 and foreign steamer 2113, prevents
Revolving force is decayed from wheel hub into the transmittance process of foreign steamer 2113, and prevents first wheel 2112 with foreign steamer 2113 in rotating speed high
When produce sliding or come off, the synchronism of first wheel 2112 and foreign steamer 2113 motion is improve, so as to improve the steady of structure
Qualitative and security.Flywheel energy storage rotor of the invention can ensure when rotating speed reaches 10000 revs/min, still its wheel hub with it is outer
Pretightning force between wheel 2113 so that the rated speed of flywheel flywheel energy storage rotor 211 can further improve.The raising of rotating speed can
Energy storage density, the energy storage capacity of flywheel energy storage rotor are improved, so as to improve its moment power output, aircraft 7 is obtained when taking off
Bigger boosting power.
As shown in figure 3, magnetic levitation system 213 is located in the housing 212 and positioned at the upper end of flywheel energy storage rotor 211,
For supporting the upper end of the rotary shaft 2111 of the flywheel energy storage rotor 211 and allowing the rotary shaft 2111 relative to the magnetic
Levitation device 213 rotates.Magnetic levitation system 213 can use various existing bearings, can hereafter be discussed in detail in the present embodiment and adopt
The structure of magnetic levitation system 213.
Energy conversion device 214 is located in the housing 212 and positioned at the lower section of the flywheel energy storage rotor 211, described
Energy conversion device 214 includes the stator (not shown) formed by magnetic pole circuit coiling, can be rotated relative to the stator
Rotor (not shown) and the power transmission shaft 2141 that is rotated by the rotor, the power transmission shaft 2141 and the flywheel are stored up
The rotating shaft coaxle of energy rotor 211 is fixedly connected and synchronous rotary, and the energy conversion device 214 also includes cooling duct (figure
Not shown in), there is coolant to circulate in cooling duct, energy conversion device can be cooled down.
The vacuum extractor 22 is connected with the aspirating hole 2124 of the housing 212 of the energy storage device 21 can be to the housing
212 closing spaces for surrounding are vacuumized, so that flywheel energy storage rotor 211 rotates in the environment of vacuum, reduce air
The resistance for causing is rotated to flywheel energy storage rotor 211, so as to reduce the waste of the energy.In the present embodiment, vacuum extractor 2
It is vavuum pump, vacuum extractor 2 can be with the housing 212 of multiple energy storage devices 21 by exhaust tube (not shown)
Aspirating hole 2124 is connected so as to be vacuumized to multiple energy storage devices 21 simultaneously.
The rotor rotation of energy conversion device is inevitably generated heat energy, causes energy conversion device temperature to raise, cold
But device reduces the temperature of energy conversion device, so as to ensure that the normal operation of energy conversion device.The cooling device
The cooling duct of the 24 fluid reservoir (not shown)s for including storage coolant and the fluid reservoir and the energy conversion device
The connecting tube (not shown) of connection and make the coolant in the cooling duct for the coolant provides power
The cooling pump (not shown) of circulation, coolant can be water.Cooling device 4 can be connected with multiple energy storage devices 1 with
Multiple energy storage devices 21 are cooled down.
Used as preferred scheme, flywheel energy storage system also includes vacuum control unit 23, cooling controller 25 and energy
Conversion control device 26.Wherein, vacuum control 23 is connected to control the vacuum extractor 22 with the vacuum extractor 22
Operation.Cooling controller 25 is connected to control the cooling device 4 with the cooling device 24.
Energy conversion control device 26 is connected with the energy conversion device 214 of the energy storage device 21, can control the energy
Measure the magnetic pole circuit and charging circuit and the on off operating mode of power supply circuit of device 26 of walking around.When the magnetic pole circuit and the charging
Circuit is connected, while when being disconnected with the power supply circuit, i.e., charge switch is closed, while when power switch disconnects, the energy
The rotor of conversion equipment 214 is rotated under the magneticaction of stator so as to drive the flywheel energy storage rotor by the power transmission shaft
211 rotations.Now, the energy conversion device 214 converts electrical energy into the rotation of the flywheel energy storage rotor 211 as motor
Turn mechanical energy to store.When the magnetic pole circuit and the charging circuit disconnect to be connected with the power supply circuit simultaneously, i.e.,
The charge switch disconnects, while when power switch is closed, the flywheel energy storage rotor 211 is driven by the power transmission shaft 2141
The rotor rotation of the energy conversion device 214 is so that the magnetic pole circuit produces electric current.The now energy conversion device
The rotating mechanical energy of the flywheel energy storage rotor 211 is converted into electric energy by 214 as generator supplies the power supply circuit.
In the present embodiment, the flywheel energy storage system also includes the TEMP of the detection temperature of energy conversion device 214
Device (not shown), the temperature sensor is also connected with by the temperature of the temperature sensor with the cooling controller 25
Degree sends the cooling controller 25 to, and the cooling controller 25 is according to the Temperature numerical control cooling dress for receiving
Putting 24 operation makes the temperature control of the energy storage device within the temperature range of setting.Temperature sensor can detect that energy turns
The temperature of the coolant in the cooling duct of changing device 214, and using this temperature as the temperature of energy conversion device 214.
In the present embodiment, the flywheel energy storage system is also included inside the housing 212 of the detection energy storage device 21
The baroceptor (not shown) of air pressure, the baroceptor is also connected with by described in the vacuum control unit 23
The data of baroceptor send the vacuum control unit 23 to, and the vacuum control unit 23 is according to the Temperature numerical for receiving
Controlling the operation of the vacuum extractor 22 makes the air pressure in the housing 212 of the energy storage device 21 control the air pressure model in setting
In enclosing.
As preferred scheme, in the present embodiment, as shown in figure 5, the abutting part 21122 and the discoid body
By the transition of fillet 21133 between 21121, fillet 21133 can make the stress distribution of generation evenly, prevent stress concentration.
In the present embodiment, stress slows down groove 21124 and is arranged on fillet 21133 and its neighbouring outer wall, and surround outer wall one week.
As shown in Figure 4 and Figure 5, the foreign steamer 2113 is tubbiness, and the material that foreign steamer 2113 is used is more tough and tensile than wheel hub, can
Resistance centrifugal force, without being torn.2 foreign steamers 113 are enclosed within the first wheel 2112, its inwall with the first wheel
The first cooperation prominent raised 21131 circumferentially is provided with the position that the outer wall of 2112 abutting parts 21122 coordinates.Complete to pacify
In the state of dress, the outer wall of the abutting part 21122 of the first wheel 2112 coordinates raised 21131 close-fitting of dashing forward with described first
Close.First coordinates what prominent raised 21131 abutting parts 21122 that increased first wheel 2112 coordinated in the inwall with foreign steamer 2113
When the deflection that produces so that the tight fit between foreign steamer 2113 and first wheel 2112 is relatively reliable.
First coordinates prominent raised 21131 around circumferentially extending one week, and described first coordinates prominent raised 21131 at least one end to set
There is the installation for guiding the axially opposed motion in the foreign steamer 2113 of first wheel 2112 to guide slope 21132, installation is drawn
Lead slope 21132 i.e. first and coordinate the transition structure dashed forward between raised 21131 and the inwall of foreign steamer 2113.First coordinates prominent projection
21131 at least one end is one end that the abutting part is first contacted when installing.Guiding slope 21132 is installed and may be such that first wheel
2112 are easily installed in foreign steamer 2113, and realize coordinating prominent raised 21131 tight fit with first.In the present embodiment, institute
State close-fitting and be combined into interference fit, as shown in figure 5, first coordinates prominent raised 21131 upper and lower ends to be respectively provided with installation guiding slope
21132。
As preferred scheme, as shown in figure 4, the first wheel 2112 also include being enclosed within can in the rotary shaft 2111
With the mounting sleeve 21123 of the synchronous axial system of the rotary shaft 2111, the discoid body 21121 is positioned at the mounting sleeve 21123
Outside and be integrally formed with the mounting sleeve 21123.Mounting sleeve 21123 is more than discoid body in the size of above-below direction
21121 size in the vertical direction, mounting sleeve 21123 is bigger with the contact area of rotary shaft 2111, can prevent the first round
Hub 2112 is produced and rocked.
In the present embodiment, the flywheel energy storage rotor 211 also includes second positioned at the top of the first wheel 2112
Wheel hub 2114, second wheel hub 2114 is made up of spring steel, is enclosed within the rotary shaft 2111, and can be in the rotary shaft
With the synchronous rotary of the rotary shaft 2111 under 2111 drive, planform and the first wheel of second wheel hub 2114
2112 planform is identical, and in the state of assembling is completed, the discoid body 21121 of the first wheel 2112 and described the
The incline direction of the discoid body 21141 of two wheel hubs 2114 is identical, and the abutting part 21142 of second wheel hub 2114 is with setting outside
Take turns the tight fit of the second fitting projection 21134 on 2113 inwalls.This provides condition, the foreign steamer of lengthening for the lengthening of foreign steamer 2113
2113 improve quality, that is, increase the rotary inertia J of flywheel, so as to improve the energy storage capacity of flywheel.
Used as preferred scheme, second wheel hub 2114 also includes that be enclosed within the rotary shaft 2111 can be with the rotation
The mounting sleeve 211143 of the synchronous axial system of axle 2111, the discoid body 21141 be located at the mounting sleeve 211143 outside and
It is integrally formed with the mounting sleeve 211143.Mounting sleeve 211143 exists in the size of above-below direction more than discoid body 21141
Size on above-below direction, mounting sleeve 211143 is bigger with the contact area of rotary shaft 2111, can prevent the second wheel hub 2114
Generation is rocked.
As further preferably, the flywheel energy storage rotor 211 also includes positioning shaft sleeve 2116, the positioning shaft sleeve
2116 are enclosed within the rotary shaft 2111, and between the wheel hub 2114 of the first wheel 2112 and second so that the first round
It is spaced a distance between the wheel hub 2114 of hub 2112 and second, this provides condition for the further lengthening of foreign steamer 2113.
In the present embodiment, the positioning shaft sleeve 2116 is made up of 40Cr.The lower end of positioning shaft sleeve 2116 and the installation of first wheel 2112
The upper end of axle sleeve 21123 offsets, the lower end phase of the upper end of positioning shaft sleeve 2116 and the mounting sleeve 211143 of the second wheel hub 2114
Support.In the present embodiment, positioning shaft sleeve 2 can synchronous rotary with the rotary shaft 2111.
The lower end of the rotary shaft 2111 has the first axle positioned for the lower end to the first wheel 2112
Shoulder 21111.In the present embodiment, the first axle of the lower surface of the mounting sleeve 21123 of first wheel 2112 and rotary shaft 2111
The upper surface of shoulder 21111 offsets and realizes positioning.
Preferably, the magnetic levitation system 213 of the energy storage device of flywheel energy storage system of the invention includes an at least magnetcisuspension
Floating axle holds 2131.As shown in fig. 6, each magnetic suspension bearing 2131 includes being fixed in the rotary shaft 2111 and can be with the rotation
The rotor magnet 21311 of the synchronous rotary of rotating shaft 2111, and with the relatively-stationary stator magnet 21312 of the housing 212, described turn
Sub- magnet 21311 is relative about 21312 with the stator magnet, and the rotor magnet 21311 and the stator magnet 21312
Relative face is heteropole.Rotor magnet 21311 is the permanent magnet of annular with stator magnet 21312.Rotor magnet 21311 with it is fixed
The relative face of sub- magnet 21312 is heteropole, the power that generation attracts each other so that flywheel obtains suction up, offsets flywheel storage
The energy most gravity of rotor 211, so as to reach the effect of off-load, mitigates the pressure of damper mechanism 26.Due to rotor magnet
It is not in contact between 21311 and stator magnet 21312, the power loss brought so as to avoid friction.
As shown in fig. 6, the rotor magnet 21311 is embedded on rotor carrier 21313, the rotor carrier 21313 is consolidated
It is scheduled in the rotary shaft 2111, the stator magnet 21312 is embedded on stator carrier 21314, the stator carrier 21314
It is fixed on the mounting bracket 21315 fixed with the housing 212.In the present embodiment, rotor carrier 21313 and stator carrier
21314 are also annular, and mounting bracket 21315 is cylindrical shape.As shown in fig. 6, the magnetic levitation system 213 includes three magnetic
Suspension bearing 2131, the rotor carrier 21313 of each magnetic suspension bearing 2131 is threadedly secured to the rotary shaft
On 2111.The upper end axle journal part of rotary shaft 2111 is provided with least three second shaft shoulders 21112, with respectively to three magnetic suspension shafts
The rotor carrier 21313 for holding 2131 is positioned.
In the present embodiment, the magnetic levitation system 213 also includes safety bearing 2132, and the safety bearing 2132 is machine
Tool bearing.Mechanical bearing with rotary shaft 2111 by way of contacting for rotary shaft 2111 provides support force, such as rolling bearing.Peace
Holoaxial holds 2132 and can provide support force to rotary shaft 2111 when magnetic suspension bearing 2131 goes wrong.
The magnetic levitation system 213 also includes the axial direction positioning device fixed with the housing 212 or mounting bracket 21315
2133, the axial direction positioning device 2133 is mutually pushed up with the upper end of the rotary shaft 2111 in the axial direction of the rotary shaft 2111.
In the present embodiment, as shown in fig. 6, axial direction positioning device 2133 is bolted with mounting bracket 21315, axial direction positioning device
2133 thimble 21331 being fixedly arranged in the middle of towards rotary shaft 2111, thimble 21331 is matched somebody with somebody with the depression of the upper end of rotary shaft 2111
Close, axial power is applied to rotary shaft 2111, so as to be positioned to rotary shaft 2111.
The energy storage device of flywheel energy storage system of the invention also includes the damping mechanism 2156 in the housing 212,
The lower end of the power transmission shaft 2141 of the energy conversion device 214 is connected to absorb the power transmission shaft with the damping mechanism 2156
2141 vibrations.
Above example is only exemplary embodiment of the invention, is not used in the limitation present invention, protection scope of the present invention
It is defined by the claims.Those skilled in the art are in essence of the invention and protection domain, and what the present invention was made is various
Modification or equivalent are also within the scope of the present invention.
Claims (10)
1. a kind of aircraft carrier Electromagnetical ejector, it is characterised in that including：
Power supply,
Flywheel energy storage system, the flywheel energy storage system constitutes charging circuit with power electric connection,
Rectifier, the rectifier is electrically connected with the flywheel energy storage system to be carried out to the electric current that the flywheel energy storage system is provided
Rectification,
Closed slide, electrically connects with the rectifier,
Armature, the armature and the closed slide conductive contact, the flywheel energy storage system, rectifier, closed slide and electricity
Pivot is electrically connected to form power supply circuit, and when power supply circuit is powered, the armature is moved along the closed slide, while promoting described
Aircraft is moved,
Control system, the control system is connected with the flywheel energy storage system and can control the flywheel energy storage system according to setting
Parameter operation, the control system be connected with the rectifier can control the rectifier according to setting parameter operation, institute
State control system and the current parameters after can monitoring rectification are connected with the closed slide；
The flywheel energy storage system includes energy storage device, and the energy storage device includes housing, flywheel energy storage rotor, magnetic levitation system
And energy conversion device,
The housing include cylindrical lateral wall and the side wall upper end cover fixing and be tightly connected and fixed with the side wall and
The bottom end cover being tightly connected, the housing is provided with aspirating hole,
The flywheel energy storage rotor is located in the housing, and the flywheel energy storage rotor includes,
Rotary shaft, is the solid steel shaft being vertically arranged,
First wheel, the first wheel is made up of spring steel, and being enclosed within the rotary shaft can be under the drive of the rotary shaft
With the rotary shaft synchronous rotary, the outer rim that the first wheel has discoid body, the discoid body is bent to form to one side
Abutting part, the position that the abutting part is connected with the discoid body is provided with stress and slows down groove, and the discoid body of the first wheel is certainly
Middle part inclines to edge relative to the vertical plane perpendicular to the rotary shaft, and direction forms an inclination of the abutting part
Tiltedly,
Foreign steamer, the foreign steamer is tubbiness, is enclosed within the first wheel, the outer wall phase of its inwall and the first wheel abutting part
Coordinate；
The magnetic levitation system is located in the housing for supporting the upper end of the rotary shaft of the flywheel and allowing the rotation
Axle rotates relative to the magnetic levitation system,
The energy conversion device is located in the housing and positioned at the lower section of the flywheel, the energy conversion device include by
Stator, the rotor that can be rotated relative to the stator and the transmission being rotated by the rotor that the coiling of magnetic pole circuit is formed
Axle, the power transmission shaft is fixedly connected and synchronous rotary with the rotating shaft coaxle of the flywheel, and the energy conversion device also includes
Cooling duct；
The flywheel energy storage system also includes,
Vacuum extractor, the vacuum extractor is connected with the aspirating hole of the housing of the energy storage device can be surrounded to the housing
Closing space vacuumize；
Cooling device, the cooling device includes the fluid reservoir and the fluid reservoir and the energy converting means of storage coolant
The connecting tube of the cooling duct connection put and make the coolant in the cooling duct for the coolant provides power
The cooling pump of circulation.
2. aircraft carrier Electromagnetical ejector according to claim 1, it is characterised in that the flywheel energy storage system is also wrapped
Include：
Vacuum control unit, is connected to control the operation of the vacuum extractor with the vacuum extractor；
Cooling controller, is connected to control the cooling device with the cooling device；
Energy conversion control device, is connected with the energy conversion device, can control the energy conversion device be in charge or
Person's power supply state, when the magnetic pole circuit and charging circuit are connected to be disconnected with the power supply circuit simultaneously, the energy conversion
The rotor of device is rotated under the magneticaction of stator so as to drive the flywheel energy storage rotor to rotate by the power transmission shaft, institute
Energy conversion device is stated to be stored as the rotating mechanical energy that motor converts electrical energy into the flywheel energy storage rotor, it is described
Energy conversion device is in charged state, is connect with the power supply circuit simultaneously when the magnetic pole circuit disconnects with the charging circuit
When logical, the flywheel energy storage rotor drives the rotor of the energy conversion device to rotate so that the magnetic by the power transmission shaft
Polar circuit produces electric current, the energy conversion device to be converted into the rotating mechanical energy of the flywheel energy storage rotor as generator
Electric energy supplies the power supply circuit, and the energy conversion device is in power supply state.
3. aircraft carrier Electromagnetical ejector according to claim 2, it is characterised in that each of the flywheel energy storage system
The energy storage device sets the temperature sensor of detection energy conversion device temperature, and the temperature sensor is also controlled with the cooling
Device processed connection sends the cooling controller to by the temperature of the temperature sensor, the cooling controller according to
The operation of the Temperature numerical control cooling device for receiving makes the temperature control of the energy storage device in the temperature range of setting
It is interior.
4. aircraft carrier Electromagnetical ejector according to claim 2, it is characterised in that each of the flywheel energy storage system
Energy storage device is provided for detecting the baroceptor of enclosure interior air pressure, and the baroceptor is also filled with the vacuum control
Put connection and send the vacuum control unit to by the data of the baroceptor, the vacuum control unit is according to receiving
Temperature numerical control the operation of the vacuum extractor air pressure in the housing of the energy storage device is controlled in the gas for setting
In the range of pressure.
5. aircraft carrier Electromagnetical ejector according to claim 1, it is characterised in that the abutting part and the discoid body
Between by round-corner transition, the stress slows down groove on the outer wall of the fillet.
6. aircraft carrier Electromagnetical ejector according to claim 1, it is characterised in that the inwall of the foreign steamer with it is described
The first fitting projection circumferentially is provided with the position that the outer wall of first wheel abutting part is engaged, in the shape for completing to install
Under state, the abutting part of the first wheel and the first fitting projection tight fit, at least one end of first fitting projection
It is provided with the guiding first wheel and guides slope along the installation of axis relative motion in the foreign steamer, the first fitting projection is at least
One end is one end that the abutting part is first contacted when installing.
7. aircraft carrier Electromagnetical ejector according to claim 1, it is characterised in that the first wheel also includes being enclosed within
The outside of the mounting sleeve can be located in the rotary shaft with the mounting sleeve of the rotary shaft synchronous axial system, the discoid body
And be integrally formed with the mounting sleeve.
8. the aircraft carrier Electromagnetical ejector according to any one of claim 7, it is characterised in that the flywheel also includes
The second wheel hub above the first wheel, second wheel hub is made up of spring steel, is enclosed within the rotary shaft, and can
With the rotary shaft synchronous rotary under the drive of the rotary shaft, planform and the first wheel of second wheel hub
Planform it is identical, and in the state of assembling is completed, the plate-like of the discoid body of the first wheel and second wheel hub
The incline direction of body is identical, the abutting part of second wheel hub and the second fitting projection tight fit being arranged on foreign steamer inwall,
The flywheel also includes positioning shaft sleeve, and the positioning shaft sleeve is enclosed within the rotary shaft, and positioned at the first wheel and second
Between wheel hub, the lower end of the rotary shaft has the shaft shoulder positioned for the lower end to the first wheel.
9. aircraft carrier Electromagnetical ejector according to claim 1, it is characterised in that the magnetic levitation system is included at least
One magnetic suspension bearing, each magnetic suspension bearing includes being fixed in the rotary shaft and can be with the rotary shaft synchronous rotary
Rotor magnet and with the relatively-stationary stator magnet of the housing, the rotor magnet is relative up and down with the stator magnet, and
The rotor magnet face relative with the stator magnet is heteropole.
10. aircraft carrier Electromagnetical ejector according to claim 9, it is characterised in that the rotor magnet is embedded in and turns
On subcarrier, the rotor carrier is fixed in the rotary shaft, and the stator magnet is embedded on stator carrier, the stator
Carrier is fixed on the mounting bracket fixed with the housing, and the rotor carrier of the magnetic suspension bearing is threadedly secured to described
In rotary shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611121603.2A CN106697318A (en) | 2016-12-08 | 2016-12-08 | Electromagnetic catapult for carrier aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611121603.2A CN106697318A (en) | 2016-12-08 | 2016-12-08 | Electromagnetic catapult for carrier aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106697318A true CN106697318A (en) | 2017-05-24 |
Family
ID=58936182
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611121603.2A Pending CN106697318A (en) | 2016-12-08 | 2016-12-08 | Electromagnetic catapult for carrier aircraft |
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| CN (1) | CN106697318A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109698578A (en) * | 2018-12-21 | 2019-04-30 | 苏州腾冉电气设备股份有限公司 | A kind of magnetic-suspension flywheel energy-storage cell |
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Application publication date: 20170524 |