CN107719687A - Electromagnetic launch device based on wireless power transmission technology - Google Patents
Electromagnetic launch device based on wireless power transmission technology Download PDFInfo
- Publication number
- CN107719687A CN107719687A CN201710836442.3A CN201710836442A CN107719687A CN 107719687 A CN107719687 A CN 107719687A CN 201710836442 A CN201710836442 A CN 201710836442A CN 107719687 A CN107719687 A CN 107719687A
- Authority
- CN
- China
- Prior art keywords
- linear motor
- platform
- motor rotor
- carrier
- pair
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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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—Launching or towing gear
- B64F1/06—Launching or towing gear using catapults
Abstract
The electromagnetic launch device based on wireless power transmission technology of the invention is mainly used in aircraft carrier and taken off use；It mainly includes platform, linear motor stator electric and linear motor rotor；Its operation principle is:Carrier-borne aircraft is clamped on platform, start levitating electromagnet A and levitating electromagnet B power supply, levitating electromagnet A jacks 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, in whole ejection process, electric energy is transferred to linear motor rotor by the primary winding of linear motor stator electric by wireless power transmission technology.
Description
Technical field
Taken off use present invention is mainly used for aircraft carrier.
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）, linear electric motors
Stator（2）Primary winding is installed at a certain distance（11）, linear motor rotor（3）Secondary line is installed at a certain distance
Circle（12）；Its operation principle is:Carrier-borne aircraft is parked in platform（1）Upper and platform（1）On clamping device carrier-borne aircraft is clamped
Firmly, levitating electromagnet A is started（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 together
Two linear motor stator electrics of Shi Qidong or so（2）A pair of guiding electromagnets（7）, due to a pair of guiding electromagnets（7）Magnet
Size and magnet attribute are completely the same and mutually exclusive, are clipped in a pair of guiding electromagnets（7）Middle steel connecting plate（9）Such as
Fruit offsets to the left, the guiding electromagnet on the left side（7）Promotion magnetic force increase, the guiding electromagnet on the right（7）Promotion magnetic force subtract
It is small, 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, it is left
The guiding electromagnet on side（7）Promotion magnetic force reduce, the guiding electromagnet on the right（7）Promotion magnetic force increase, a pair be oriented to electricity
Magnet（7）By steel connecting plate（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 a pair of guiding electromagnets are in（7）Centre position, equally make linear motor rotor（3）Cross central line and straight-line electric
The cross central line of machine overlaps, and restarts two linear motor rotors（3）Positive power supply, linear motor rotor（3）Along straight line
Motor stator（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 rotor（3）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；In whole ejection process, linear motor stator electric
（2）Primary winding（11）Powered by aircraft carrier, primary winding（11）With linear motor rotor（3）Secondary coil（12）Pass through nothing
Electric energy is transferred to linear motor rotor by line electric energy transmission technology（3）And other sports equipments；Need to illustrate：What linear electric motors used
It is the tubular linear motor of the short mover of long stator.
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- primary windings, 12- secondary lines
Circle.
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 A-A diagrammatic cross-sections of the present invention.
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；Radio energy of the present invention passes
Transferring technology has been known technology, and I will not elaborate.
Claims (1)
1. the electromagnetic launch device based on wireless power transmission technology, it is characterized in that：It mainly includes platform（1）, two it is symmetrical
The linear motor stator electric of arrangement（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 the linear motor stator electric of left and right two（2）'s
Opening（10）, connecting plate（9）Lower end and linear motor rotor（3）Upper end fix, linear motor rotor（3）Inwall with
Mandrel（4）Outer wall fix, base（8）With linear motor stator electric（2）It is fixed, linear motor stator electric（2）Opening（10）Both sides
It is fixed with a pair of guiding electromagnets being arranged symmetrically（7）, a pair of guiding electromagnets（7）Magnet sizes and magnet attribute complete one
Cause, and mutually exclusive, linear motor stator electric（2）Bottom have the levitating electromagnet A being arranged symmetrically with center line（5）, straight-line electric
Motor-driven son（3）Bottom have the levitating electromagnet B being arranged symmetrically with center line（6）, linear motor stator electric（2）At a certain distance
Primary winding is installed（11）, linear motor rotor（3）Secondary coil is installed at a certain distance（12）；Its operation principle
It 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 straight line
Electric mover（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 to start left and right two simultaneously straight
Line motor stator（2）A pair of guiding electromagnets（7）, due to a pair of guiding electromagnets（7）Magnet sizes and magnet attribute it is complete
It is complete consistent 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 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）Steel is connected
Plate（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 it is oriented to electricity in a pair
Magnet（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；In whole ejection process, linear motor stator electric（2）Primary winding（11）By
Aircraft carrier is powered, primary winding（11）With linear motor rotor（3）Secondary coil（12）By wireless power transmission technology by electricity
Linear motor rotor can be transferred to（3）And other sports equipments；Need to illustrate：Linear electric motors using the short mover of long stator pipe
Shape linear electric motors.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710836442.3A CN107719687A (en) | 2017-09-16 | 2017-09-16 | Electromagnetic launch device based on wireless power transmission technology |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710836442.3A CN107719687A (en) | 2017-09-16 | 2017-09-16 | Electromagnetic launch device based on wireless power transmission technology |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107719687A true CN107719687A (en) | 2018-02-23 |
Family
ID=61207540
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710836442.3A Withdrawn CN107719687A (en) | 2017-09-16 | 2017-09-16 | Electromagnetic launch device based on wireless power transmission technology |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107719687A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20230055815A1 (en) * | 2021-08-23 | 2023-02-23 | Jimmy Wagner | Interplanetary transportation system |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102201179A (en) * | 2010-03-23 | 2011-09-28 | 上海外国语大学附属大境中学 | A plurality of direct current coils based electromagnetic ejector of carrier-based aircraft |
| CN102320380A (en) * | 2011-06-30 | 2012-01-18 | 吴春俐 | Ejector capable of directly releasing energy by using superconducting magnet |
| CN102457154A (en) * | 2010-10-19 | 2012-05-16 | 叶建国 | Linear motor device |
| CN103368355A (en) * | 2013-06-28 | 2013-10-23 | 柳峰 | DC (Direct Current) automatic accelerated catapult |
| CN205429917U (en) * | 2015-11-03 | 2016-08-03 | 西南交通大学 | Pole change is apart from growing elementary bilateral linear induction motor |
| 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 |
-
2017
- 2017-09-16 CN CN201710836442.3A patent/CN107719687A/en not_active Withdrawn
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102201179A (en) * | 2010-03-23 | 2011-09-28 | 上海外国语大学附属大境中学 | A plurality of direct current coils based electromagnetic ejector of carrier-based aircraft |
| CN102457154A (en) * | 2010-10-19 | 2012-05-16 | 叶建国 | Linear motor device |
| CN102320380A (en) * | 2011-06-30 | 2012-01-18 | 吴春俐 | Ejector capable of directly releasing energy by using superconducting magnet |
| CN103368355A (en) * | 2013-06-28 | 2013-10-23 | 柳峰 | DC (Direct Current) automatic accelerated catapult |
| CN205429917U (en) * | 2015-11-03 | 2016-08-03 | 西南交通大学 | Pole change is apart from growing elementary bilateral linear induction motor |
| 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 |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20230055815A1 (en) * | 2021-08-23 | 2023-02-23 | Jimmy Wagner | Interplanetary transportation system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| 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. |
|
| TA01 | Transfer of patent application right | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20180223 |
|
| WW01 | Invention patent application withdrawn after publication |