CN107554811A - Aircraft carrier electromagnetic launch device with tilt function - Google Patents
Aircraft carrier electromagnetic launch device with tilt function Download PDFInfo
- Publication number
- CN107554811A CN107554811A CN201710823067.9A CN201710823067A CN107554811A CN 107554811 A CN107554811 A CN 107554811A CN 201710823067 A CN201710823067 A CN 201710823067A CN 107554811 A CN107554811 A CN 107554811A
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- linear motor
- platform
- carrier
- guiding
- electromagnet
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Abstract
There is the present invention aircraft carrier electromagnetic launch device of tilt function to be mainly used in aircraft carrier help-fly use, and it has tilt function, require low to plant capacity；It is made up of platform, static ej ection device, movable ejector；Its operation principle is:Carrier-borne aircraft is parked on platform and is clamped, now platform is in the left end of static ej ection device, start levitating electromagnet A power supply, make platform suspension, restart the positive power supply of two linear motor rotors, linear motor rotor band moving platform accelerates to travel forward on static ej ection device, after platform moves to the left end of movable ejector, jacking hydraulic system jacks up the right-hand member of movable ejector, platform and carrier-borne aircraft are inclined upwardly an angle, 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 relevant aircraft carrier electromagnetic launch device applied or authorized at present is all horizontally disposed, is not all had
Tilt function, it is right if the carrier-borne aircraft that launch the large-tonnages such as fighter plane needs bigger ejection force and faster takeoff speed
Plant capacity requires high.
The content of the invention
The present invention solves above mentioned problem, and it has tilt function, requires low to plant capacity；It is by platform（1）, it is static
Ejector（11）, movable ejector（12）Composition；Static ej ection device（11）Mainly determine including two linear electric motors being arranged symmetrically
Son（2）And corresponding linear motor rotor（3）, central shaft（4）, base（8）, connecting plate（9）；Movable ejector（12）Main bag
Include two linear motor stator electrics being arranged symmetrically and corresponding linear motor rotor, central shaft, connecting plate, jacking hydraulic system
（13）；Movable ejector（12）With static ej ection device（11）Except movable ejector（12）Right-hand member add jacking hydraulic system
（13）Outside, both other parts are just the same, in jacking hydraulic system（13）Jacking effect under, movable ejector（12）The right side
End is jacked up, movable ejector（12）An angle is rotated around its left end；Platform（1）Lower end both sides symmetrically fix two connections
Plate（9）, two connecting plates（9）Through the linear motor stator electric of left and right two（2）Opening（10）, connecting plate（9）Lower end with it is straight
Line electric mover（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 with a pair of guiding electromagnetism being arranged symmetrically
Iron（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）, linear motor rotor（3）Bottom have with center line pair
Claim the levitating electromagnet B of arrangement（6）；Its operation principle is:Carrier-borne aircraft is parked in platform（1）Upper and platform（1）On clamping dress
Put and clamp carrier-borne aircraft, now platform（1）It is in static ej ection device（11）Left end, start levitating electromagnet A（5）And suspend
Electromagnet B（6）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 straight-line electric
Motor-driven son（3）Vertical centerline overlapped with the vertical centerline of linear electric motors, then simultaneously start left and right two linear electric motors determine
Son（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
It is mutually exclusive, it is clipped in a pair of guiding electromagnets（7）Middle steel connecting plate（9）If offset to the left, the guiding electromagnetism on the left side
Iron（7）Promotion magnetic force increase, the guiding electromagnet on the right（7）Promotion magnetic force reduce, a pair of guiding electromagnets（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）By steel connecting plate（9）To the left
Push away, therefore a pair of guiding electromagnets（7）There is automatic deviation rectifying function, make connecting plate（9）All the time a pair of guiding electromagnets are in（7）'s
Centre position, equally make linear motor rotor（3）Cross central line overlapped with the cross central line of linear electric motors, restart two
Individual linear motor rotor（3）Positive power supply, linear motor rotor（3）Along linear motor stator electric（2）Travel forward, and drive flat
Platform（1）In static ej ection device（11）Upper acceleration travels forward, and works as platform（1）Move to movable ejector（12）Left end after, top
Rise hydraulic system（13）By movable ejector（12）Right-hand member jack up, movable ejector（12）An angle is rotated around its left end,
Platform（1）And carrier-borne aircraft is inclined upwardly an angle, carrier-borne aircraft is taken off, after carrier-borne aircraft takes off, it is motor-driven to start two straight-line electrics
Son（3）Reverse electrical source, linear motor rotor（3）Along linear motor stator electric（2）Move backward, and with moving platform（1）Transport backward
It is dynamic to make platform（1）Reset, wait next carrier-borne aircraft to take off；Need to illustrate：Linear electric motors using the short mover of long stator pipe
Shape linear electric motors.
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, 11- static ej ection devices, 12- are movable
Ejector, 13- jacking hydraulic systems.
Fig. 1 is the elevational schematic view of the present invention.
Fig. 2 is the vertical cross section schematic diagram of ejector.
Fig. 3 is the local drawing of ejector.
Fig. 4 is the schematic top plan view of ejector.
Fig. 5 is the vertical cross section schematic diagram of linear motor stator electric.
Fig. 6 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；If launch the small ton such as fighter plane
The carrier-borne aircraft of position, movable ejector is in horizontality.
Claims (1)
1. the aircraft carrier electromagnetic launch device with tilt function, it is characterized in that：It is by platform（1）, static ej ection device
（11）, movable ejector（12）Composition；Static ej ection device（11）Mainly include two linear motor stator electrics being arranged symmetrically（2）And
Corresponding linear motor rotor（3）, central shaft（4）, base（8）, connecting plate（9）；Movable ejector（12）It is main to include two
The linear motor stator electric and corresponding linear motor rotor, central shaft, connecting plate, jacking hydraulic system being arranged symmetrically（13）；Can
Move emitter（12）With static ej ection device（11）Except movable ejector（12）Right-hand member add jacking hydraulic system（13）Outside, two
Person's other parts are just the same, in jacking hydraulic system（13）Jacking effect under, movable ejector（12）Right-hand member jacked up,
Movable ejector（12）An angle is rotated around its left end；Platform（1）Lower end both sides symmetrically fix two connecting plates（9）, two
Individual connecting plate（9）Through the linear motor stator electric of left and right two（2）Opening（10）, connecting plate（9）Lower end and straight-line electric it is motor-driven
Son（3）Upper end fix, linear motor rotor（3）Inwall and central shaft（4）Outer wall fix, base（8）With linear electric motors
Stator（2）It is fixed, linear motor stator electric（2）Opening（10）Both sides are fixed with a pair of guiding electromagnets being arranged symmetrically（7）, one
To guiding electromagnet（7）Magnet sizes and magnet attribute it is completely the same and mutually exclusive, linear motor stator electric（2）Bottom
There is the levitating electromagnet A being arranged symmetrically with center line（5）, linear motor rotor（3）Bottom have what is be arranged symmetrically with center line
Levitating electromagnet B（6）；Its operation principle is:Carrier-borne aircraft is parked in platform（1）Upper and platform（1）On clamping device will be carrier-borne
Machine clamps, now platform（1）It is in static ej ection device（11）Left end, 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 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）
Vertical centerline overlapped with the vertical centerline of linear electric motors, then simultaneously start left and right two linear motor stator electrics（2）One
To guiding electromagnet（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 guiding electromagnet on the left side（7）Push away
Dynamic magnetic force increase, the guiding electromagnet on the right（7）Promotion magnetic force reduce, a pair of guiding electromagnets（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 right
Guiding 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
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, together
Sample makes linear motor rotor（3）Cross central line overlapped with the cross central line of linear electric motors, restart two linear electric motors
Mover（3）Positive power supply, linear motor rotor（3）Along linear motor stator electric（2）Travel forward, and with moving platform（1）Quiet
Only ejector（11）Upper acceleration travels forward, and works as platform（1）Move to movable ejector（12）Left end after, jacking hydraulic system
（13）By movable ejector（12）Right-hand member jack up, movable ejector（12）An angle, platform are rotated around its left end（1）And warship
Carrier aircraft is inclined upwardly an angle, carrier-borne aircraft is taken off, and after carrier-borne aircraft takes off, starts two linear motor rotors（3）It is reverse
Power supply, 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 using the short mover of long stator tubular linear motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710823067.9A CN107554811A (en) | 2017-09-13 | 2017-09-13 | Aircraft carrier electromagnetic launch device with tilt function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710823067.9A CN107554811A (en) | 2017-09-13 | 2017-09-13 | Aircraft carrier electromagnetic launch device with tilt function |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107554811A true CN107554811A (en) | 2018-01-09 |
Family
ID=60980750
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710823067.9A Withdrawn CN107554811A (en) | 2017-09-13 | 2017-09-13 | Aircraft carrier electromagnetic launch device with tilt function |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107554811A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107585323A (en) * | 2017-09-17 | 2018-01-16 | 荆门创佳机械科技有限公司 | The electromagnetic launch device with tilt function based on wireless power transmission |
| CN107719687A (en) * | 2017-09-16 | 2018-02-23 | 荆门创佳机械科技有限公司 | Electromagnetic launch device based on wireless power transmission technology |
| CN108466703A (en) * | 2018-03-23 | 2018-08-31 | 青岛中邦防务智能装备有限公司 | A kind of unmanned boat-carrying unmanned plane take-off system and unmanned unit takeoff method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102107737A (en) * | 2010-09-19 | 2011-06-29 | 朱惠芬 | Front-pull rear-push aircraft carrier ejector and ejection method |
| CN102198865A (en) * | 2010-09-17 | 2011-09-28 | 朱惠芬 | Steam catapult for carrier-borne aircraft and catapulting method thereof |
| CN102951298A (en) * | 2012-11-28 | 2013-03-06 | 许守平 | Combustion-supporting type shipboard aircraft ejector |
| CN104787354A (en) * | 2015-03-11 | 2015-07-22 | 西北农林科技大学 | Linear accelerating ejecting-sliding combined ejector |
| CN107600450A (en) * | 2017-09-12 | 2018-01-19 | 荆门创佳机械科技有限公司 | A kind of aircraft carrier electromagnetic launch device |
-
2017
- 2017-09-13 CN CN201710823067.9A patent/CN107554811A/en not_active Withdrawn
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102198865A (en) * | 2010-09-17 | 2011-09-28 | 朱惠芬 | Steam catapult for carrier-borne aircraft and catapulting method thereof |
| CN102107737A (en) * | 2010-09-19 | 2011-06-29 | 朱惠芬 | Front-pull rear-push aircraft carrier ejector and ejection method |
| CN102951298A (en) * | 2012-11-28 | 2013-03-06 | 许守平 | Combustion-supporting type shipboard aircraft ejector |
| CN104787354A (en) * | 2015-03-11 | 2015-07-22 | 西北农林科技大学 | Linear accelerating ejecting-sliding combined ejector |
| CN107600450A (en) * | 2017-09-12 | 2018-01-19 | 荆门创佳机械科技有限公司 | A kind of aircraft carrier electromagnetic launch device |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107719687A (en) * | 2017-09-16 | 2018-02-23 | 荆门创佳机械科技有限公司 | Electromagnetic launch device based on wireless power transmission technology |
| CN107585323A (en) * | 2017-09-17 | 2018-01-16 | 荆门创佳机械科技有限公司 | The electromagnetic launch device with tilt function based on wireless power transmission |
| CN108466703A (en) * | 2018-03-23 | 2018-08-31 | 青岛中邦防务智能装备有限公司 | A kind of unmanned boat-carrying unmanned plane take-off system and unmanned unit takeoff method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 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: 20180211 Address after: 448000 Changning Avenue, Dongbao District, Jingmen, Hubei Province, No. 55 (Jin Kai mansion), 1 1 floors 103 Applicant after: Jingmen Si an machinery and Equipment 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 | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20180109 |
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| WW01 | Invention patent application withdrawn after publication |