CN107600450A - A kind of aircraft carrier electromagnetic launch device - Google Patents
A kind of aircraft carrier electromagnetic launch device Download PDFInfo
- Publication number
- CN107600450A CN107600450A CN201710819541.0A CN201710819541A CN107600450A CN 107600450 A CN107600450 A CN 107600450A CN 201710819541 A CN201710819541 A CN 201710819541A CN 107600450 A CN107600450 A CN 107600450A
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- linear motor
- carrier
- platform
- pair
- electromagnet
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- Control Of Vehicles With Linear Motors And Vehicles That Are Magnetically Levitated (AREA)
- Non-Mechanical Conveyors (AREA)
Abstract
A kind of aircraft carrier electromagnetic launch device of the present invention is mainly used in aircraft carrier help-fly use, and its equipment is light and handy, and it is small to take aircraft carrier space；It mainly includes platform, linear motor stator electric and corresponding linear motor rotor, central shaft, base, connecting plate；Its operation principle is:Carrier-borne aircraft is parked on platform and clamps carrier-borne aircraft, start levitating electromagnet A and levitating electromagnet B power supply, levitating electromagnet A will jack up linear motor rotor and platform, start a pair of guiding electromagnets simultaneously again, make the connecting plate centre position in a pair of guiding electromagnets all the time, restart the positive power supply of two linear motor rotors, linear motor rotor travels forward along linear motor stator electric, and travelled forward with moving platform, carrier-borne aircraft is set to take off, after carrier-borne aircraft takes off, start the reverse electrical source of two linear motor rotors, linear motor rotor moves backward along linear motor stator electric, and moved backward with moving platform and make platform reset, next carrier-borne aircraft is waited to take off.
Description
Technical field
Present invention is mainly used for aircraft carrier help-fly use.
Background technology
The carrier-borne aircraft electromagnetic launch device that aircraft carrier uses at present does not all have magnetic suspension system, and catapult-launching gear resistance is big, equipment
Heaviness, take the problems such as aircraft carrier space is big.
The content of the invention
The present invention solves above mentioned problem, and its equipment is light and handy, and maintenance of equipment is simple, and it is small to take aircraft carrier space；It is mainly wrapped
Include platform（1）, two linear motor stator electrics being arranged symmetrically（2）And corresponding linear motor rotor（3）, central shaft（4）, base
（8）, connecting plate（9）；Platform（1）Lower end both sides symmetrically fix two connecting plates（9）, two connecting plates（9）Through left and right two
Individual linear motor stator electric（2）Opening（10）, connecting plate（9）Lower end and linear motor rotor（3）Upper end fix, straight-line electric
Motor-driven son（3）Inwall and central shaft（4）Outer wall fix, base（8）With linear motor stator electric（2）Fixed, linear electric motors are fixed
Son（2）Opening（10）Both sides are fixed with a pair of guiding electromagnets being arranged symmetrically（7）, a pair of guiding electromagnets（7）Magnet
Size and magnet attribute are completely the same and mutually exclusive, linear motor stator electric（2）Bottom have be arranged symmetrically with center line it is outstanding
Floating electromagnet A（5）, linear motor rotor（3）Bottom have the levitating electromagnet B being arranged symmetrically with center line（6）；Its work is former
Reason is:Carrier-borne aircraft is parked in platform（1）Upper and platform（1）On clamping device carrier-borne aircraft is clamped, start levitating electromagnet
A（5）And levitating electromagnet B（6）Power supply, levitating electromagnet A（5）Jack up linear motor rotor（3）And platform（1）, now directly
Line electric mover（3）, platform（1）And platform（1）On carrier-borne aircraft total force and levitating electromagnet A（5）Caused thrust is put down
Weighing apparatus and linear motor rotor（3）Vertical centerline overlapped with the vertical centerline of linear electric motors, then simultaneously start left and right two
Linear motor stator electric（2）A pair of guiding electromagnets（7）, due to a pair of guiding electromagnets（7）Magnet sizes and magnet attribute
It is completely the same and mutually exclusive, it is clipped in a pair of guiding electromagnets（7）Middle steel connecting plate（9）If offset to the left, the left side
Guiding electromagnet（7）Promotion magnetic force increase, the guiding electromagnet on the right（7）Promotion magnetic force reduce, a pair of guiding electromagnetism
Iron（7）By steel connecting plate（9）Push away to the right, similarly if steel connecting plate（9）Offset to the right, the guiding electromagnet on the left side
（7）Promotion magnetic force reduce, the guiding electromagnet on the right（7）Promotion magnetic force increase, a pair of guiding electromagnets（7）Steel is connected
Fishplate bar（9）Push away to the left, therefore a pair of guiding electromagnets（7）There is automatic deviation rectifying function, make connecting plate（9）All the time in a pair of guiding
Electromagnet（7）Centre position, equally make linear motor rotor（3）Cross central line and linear electric motors cross central line weight
Close, restart two linear motor rotors（3）Positive power supply, linear motor rotor（3）Along linear motor stator electric（2）Transport forward
It is dynamic, and with moving platform（1）Travel forward, carrier-borne aircraft is taken off, after carrier-borne aircraft takes off, start two linear motor rotors（3）'s
Reverse electrical source, linear motor rotor（3）Along linear motor stator electric（2）Move backward, and with moving platform（1）Motion makes platform backward
（1）Reset, wait next carrier-borne aircraft to take off；Need to illustrate：Linear electric motors are electric using the tubular linear of the short mover of long stator
Machine.
Brief description of the drawings
Description of reference numerals：1- platforms, 2- linear motor stator electrics, 3- linear motor rotors, 4- central shafts, 5- suspension electromagnetism
Iron A, 6- levitating electromagnet B, 7- guiding electromagnet, 8- bases, 9- connecting plates, 10- openings.
Fig. 1 is the vertical cross section schematic diagram of the present invention.
Fig. 2 is the local drawing of the present invention.
Fig. 3 is the schematic top plan view of the present invention.
Fig. 4 is the vertical cross section schematic diagram of linear electric motors.
Fig. 5 is the vertical cross section schematic diagram that platform is parked on linear motor stator electric.
Embodiment
The embodiment of the present invention has been described in detail in the content of the invention, is not repeated herein, needs to illustrate：The present invention's
For linear electric motors using the tubular linear motor of the short mover of long stator, the operation principle of this linear electric motors has been known skill
Art, it is not repeated herein, the control device that the linear electric motors of the present invention need to be necessary certainly.
Claims (1)
1. a kind of aircraft carrier electromagnetic launch device, it is characterized in that：It mainly includes platform（1）, two be arranged symmetrically it is straight
Line motor stator（2）And corresponding linear motor rotor（3）, central shaft（4）, base（8）, connecting plate（9）；Platform（1）Under
Two connecting plates are symmetrically fixed on end both sides（9）, two connecting plates（9）Through the linear motor stator electric of left and right two（2）Opening
（10）, connecting plate（9）Lower end and linear motor rotor（3）Upper end fix, linear motor rotor（3）Inwall and central shaft
（4）Outer wall fix, base（8）With linear motor stator electric（2）It is fixed, linear motor stator electric（2）Opening（10）Both sides are fixed
There are a pair of guiding electromagnets being arranged symmetrically（7）, a pair of guiding electromagnets（7）Magnet sizes and magnet attribute it is completely the same,
And mutually exclusive, linear motor stator electric（2）Bottom have the levitating electromagnet A being arranged symmetrically with center line（5）, straight-line electric is motor-driven
Son（3）Bottom have the levitating electromagnet B being arranged symmetrically with center line（6）；Its operation principle is:Carrier-borne aircraft is parked in platform
（1）Upper and platform（1）On clamping device carrier-borne aircraft is clamped, start levitating electromagnet A（5）And levitating electromagnet B（6）'s
Power supply, levitating electromagnet A（5）Jack up linear motor rotor（3）And platform（1）, now linear motor rotor（3）, platform（1）And
Platform（1）On carrier-borne aircraft total force and levitating electromagnet A（5）Caused thrust-balancing and linear motor rotor（3）It is perpendicular
Overlapped to center line with the vertical centerline of linear electric motors, then start two linear motor stator electrics in left and right simultaneously（2）Lead for a pair
To electromagnet（7）, due to a pair of guiding electromagnets（7）Magnet sizes and magnet attribute it is completely the same and mutually exclusive, be clipped in
A pair of guiding electromagnets（7）Middle steel connecting plate（9）If offset to the left, the guiding electromagnet on the left side（7）Promotion magnetic
Power increases, the guiding electromagnet on the right（7）Promotion magnetic force reduce, a pair of guiding electromagnets（7）By steel connecting plate（9）To the right
Push away, similarly if steel connecting plate（9）Offset to the right, the guiding electromagnet on the left side（7）Promotion magnetic force reduce, the right is led
To electromagnet（7）Promotion magnetic force increase, a pair of guiding electromagnets（7）By steel connecting plate（9）Push away to the left, therefore a pair of guiding
Electromagnet（7）There is automatic deviation rectifying function, make connecting plate（9）All the time a pair of guiding electromagnets are in（7）Centre position, equally make
Linear motor rotor（3）Cross central line overlapped with the cross central line of linear electric motors, restart two linear motor rotors
（3）Positive power supply, linear motor rotor（3）Along linear motor stator electric（2）Travel forward, and with moving platform（1）Travel forward,
Carrier-borne aircraft is taken off, after carrier-borne aircraft takes off, start two linear motor rotors（3）Reverse electrical source, linear motor rotor（3）Edge
Linear motor stator electric（2）Move backward, and with moving platform（1）Motion makes platform backward（1）Reset, wait next carrier-borne aircraft to rise
Fly；Need to illustrate：Linear electric motors using the short mover of long stator tubular linear motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710819541.0A CN107600450A (en) | 2017-09-12 | 2017-09-12 | A kind of aircraft carrier electromagnetic launch device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710819541.0A CN107600450A (en) | 2017-09-12 | 2017-09-12 | A kind of aircraft carrier electromagnetic launch device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107600450A true CN107600450A (en) | 2018-01-19 |
Family
ID=61063040
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710819541.0A Pending CN107600450A (en) | 2017-09-12 | 2017-09-12 | A kind of aircraft carrier electromagnetic launch device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107600450A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107472552A (en) * | 2017-09-14 | 2017-12-15 | 荆门创佳机械科技有限公司 | A kind of automatic deviation rectifying device of electromagnetic launch device |
| CN107554811A (en) * | 2017-09-13 | 2018-01-09 | 荆门创佳机械科技有限公司 | Aircraft carrier electromagnetic launch device with tilt function |
| CN115317014A (en) * | 2022-10-17 | 2022-11-11 | 有方（合肥）医疗科技有限公司 | Beam limiting device and X-ray shooting system |
Citations (6)
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|---|---|---|---|---|
| CN101741276A (en) * | 2009-12-31 | 2010-06-16 | 电子科技大学 | Hybrid high-temperature superconducting linear magnetic suspension synchronous motor |
| CN102457154A (en) * | 2010-10-19 | 2012-05-16 | 叶建国 | Linear motor device |
| CN102689694A (en) * | 2012-05-11 | 2012-09-26 | 田太康 | Permanent magnet suspension electromagnetic ejection platform for airplane |
| CN103057722A (en) * | 2013-01-08 | 2013-04-24 | 上海大学 | Active maglev electromagnetic catapult |
| CN103754384A (en) * | 2014-01-02 | 2014-04-30 | 上海大学 | Passive magnetic suspension type electromagnetic launcher |
| CN204297123U (en) * | 2014-11-25 | 2015-04-29 | 南京艾凌节能技术有限公司 | A kind of rail mounted permanent magnetism magnetic suspension launches help-fly system |
-
2017
- 2017-09-12 CN CN201710819541.0A patent/CN107600450A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101741276A (en) * | 2009-12-31 | 2010-06-16 | 电子科技大学 | Hybrid high-temperature superconducting linear magnetic suspension synchronous motor |
| CN102457154A (en) * | 2010-10-19 | 2012-05-16 | 叶建国 | Linear motor device |
| CN102689694A (en) * | 2012-05-11 | 2012-09-26 | 田太康 | Permanent magnet suspension electromagnetic ejection platform for airplane |
| CN103057722A (en) * | 2013-01-08 | 2013-04-24 | 上海大学 | Active maglev electromagnetic catapult |
| CN103754384A (en) * | 2014-01-02 | 2014-04-30 | 上海大学 | Passive magnetic suspension type electromagnetic launcher |
| CN204297123U (en) * | 2014-11-25 | 2015-04-29 | 南京艾凌节能技术有限公司 | A kind of rail mounted permanent magnetism magnetic suspension launches help-fly system |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107554811A (en) * | 2017-09-13 | 2018-01-09 | 荆门创佳机械科技有限公司 | Aircraft carrier electromagnetic launch device with tilt function |
| CN107472552A (en) * | 2017-09-14 | 2017-12-15 | 荆门创佳机械科技有限公司 | A kind of automatic deviation rectifying device of electromagnetic launch device |
| CN115317014A (en) * | 2022-10-17 | 2022-11-11 | 有方（合肥）医疗科技有限公司 | Beam limiting device and X-ray shooting system |
| CN115317014B (en) * | 2022-10-17 | 2023-01-20 | 有方（合肥）医疗科技有限公司 | Beam limiting device and X-ray shooting system |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20180208 Address after: 448000 Hubei province Jingmen city Jingmen high tech Zone and Duodao District Road No. 69 Applicant after: Hubei Zexin Energy Technology Co Ltd Address before: 448000 Hubei Province, Jingmen city Dongbao District Road No. 1 Building 6 401 aquamarine Applicant before: Jingmen Chuangjia Machinery Technology Co., Ltd. |
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| TA01 | Transfer of patent application right | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20180119 |
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| WD01 | Invention patent application deemed withdrawn after publication |