CN102398683A - Electromagnetic ejector - Google Patents
Electromagnetic ejector Download PDFInfo
- Publication number
- CN102398683A CN102398683A CN2011100569714A CN201110056971A CN102398683A CN 102398683 A CN102398683 A CN 102398683A CN 2011100569714 A CN2011100569714 A CN 2011100569714A CN 201110056971 A CN201110056971 A CN 201110056971A CN 102398683 A CN102398683 A CN 102398683A
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- China
- Prior art keywords
- wheel
- coaster
- cover
- aircraft
- fake
- 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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Abstract
The invention relates to an electromagnetic ejector. Magnetic suspension is utilized to avoid friction between a block and a way slot to reduce resistance. As a short-distance work applying mode is adopted by the ejector, a power source does not need to be shifted along with motion, and additional power is provided for an airplane through a cable block, so that the airplane reaches the take-off required speed to smoothly take off; driving motors do not brake so as to ensure the ejector to have enough power when being started; pusher seats or pusher piles are used according to the airplane when the ejector works; and the motors of corresponding number are started according to the size of the airplane so as to ensure the conditions that the ejection power is enough, and the airplane smoothly takes off.
Description
Technical field
Armament; Carrier-borne aircraft accelerated take-off system
Background technology
At present for the aircraft carrier machine ejector that is using, we know has only the name notion, and other contents of divulging a secret possibly be non-existent at all deceptive information, utilize high-tech thought to confuse us, just very simple in fact equipment.Purpose is exactly to guide others into the successful wrong road of possibility never.
Summary of the invention
The present invention provides a cover magnetic suspension electronic drag-line ejector, major equipment; The magnetic suspension matching component, wire block one cover, 2 to 4 of main service meters, one of carriage return electrical motor, operation vang wheel. fake is taken turns a cover, carriage return vang wheel. and fake wheel one cover reaches some of braking vanes.At the airstrip line of centers coaster runway groove is set, as also the cold air applicator device being set in the needs groove.
Embodiment
On the bottom surface of coaster runway groove, the magnetic suspension corollary equipment is installed with the bottom surface of coaster; Braking vane is installed at runway groove two; Deck, runway groove two ends is installed vang wheel and fake wheel down; Cable wire is connected with the fake wheel through vang wheel, mainly moves cable wire and carriage return and moves cable wire and will design the carrying quality with load separately.1 to 2 motor is respectively installed in main operation fake wheel both sides, and motor provides fake wheel power through joining fast case, requires the corresponding gear of speed combination based on aircraft, opens corresponding afterburning motor based on the aircraft size.
The concrete specification of coaster can be according to best observed data design, and coaster preferably uses light weight. and firm. high temperature resistant. the made of rub resistance.The center design and installation is carried support or is pushed away the machine stake on coaster, carries support and slightly exceeds the deck, and flivver can be to carry single front-wheel on the support; The preceding big aircraft utilization of two-wheel pushes away the machine stake; It is preset wide 15 to 25 centimetres to push away the machine stake, and long 50 centimetres, coca is according to the aircraft nose wheel beam design; Above design garden mouth be lower than below the crossbeam, do not need the jack-up front-wheel liftoff.
Coaster runway groove is suitable for reading need not to be provided with cover plate; Because of aircraft tail gas be straight parallel blow and also the time compole short, can not cause too big influence to coaster runway groove, like needs the high-pressure fog facility can be set in the runway groove; To offset aircraft tail gas scattering high temperature, safeguard at ordinary times and can add a cover the cover plate maintenance.
Claims (1)
1. electromagnetic launch device
The present invention provides a cover magnetic suspension electronic drag-line ejector, major equipment, magnetic suspension matching component; Wire block one cover, 2 to 4 in main operation motor, one of carriage return electrical motor; Operation vang wheel. fake is taken turns a cover, carriage return vang wheel. and fake wheel one cover reaches some of braking vanes; At the airstrip line of centers coaster runway groove is set, as also the cold air applicator device being set in the needs groove.
The magnetic suspension corollary equipment is installed in bottom surface at coaster runway groove; Braking vane is installed at runway groove two; The vang wheel is installed on deck, runway groove two ends down. the fake wheel; Cable wire is connected with the fake wheel through the vang wheel; Main operation cable wire and carriage return cable wire will be with load design carrying quality separately, and 1 to 2 motor is respectively installed in main service meter both sides, and motor provides fake to take turns power through joining fast case; Require the corresponding gear of speed combination based on aircraft, open corresponding afterburning motor based on the aircraft size.
The concrete specification of coaster can be according to the design of experiment optimum data, and coaster preferably uses light weight. and firm. high temperature resistant. the made of rub resistance, carry support or push away the machine stake in the face center design and installation of hindering of coaster; Carry support and slightly exceed the deck, flivver can be stated from single front-wheel on the support, and the big aircraft utilization of preceding two-wheel pushes away the machine stake; Push away the machine stake according to the aircraft nose wheel spatial design, above design garden mouth be lower than below the crossbeam, do not need the jack-up front-wheel liftoff; Coaster runway groove is suitable for reading need not to be provided with cover plate; Because of aircraft tail gas be straight parallel blow and also the time compole short, can not cause too big threat to coaster runway groove, like needs the high-pressure fog facility can be set in the runway groove; To offset aircraft tail gas scattering high temperature, safeguard at ordinary times and can add a cover the cover plate maintenance.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100569714A CN102398683A (en) | 2011-03-01 | 2011-03-01 | Electromagnetic ejector |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100569714A CN102398683A (en) | 2011-03-01 | 2011-03-01 | Electromagnetic ejector |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102398683A true CN102398683A (en) | 2012-04-04 |
Family
ID=45881431
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011100569714A Pending CN102398683A (en) | 2011-03-01 | 2011-03-01 | Electromagnetic ejector |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102398683A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103057719A (en) * | 2012-05-05 | 2013-04-24 | 叶锋 | Magnetic levitation hinder removal type electromagnetic catapult |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101100223A (en) * | 2007-08-10 | 2008-01-09 | 霍方华 | Stream catapult for aircraft carrier based airplane |
| CN201172483Y (en) * | 2008-01-01 | 2008-12-31 | 宣建民 | Electromagnetical ejector |
| US20090100829A1 (en) * | 2005-04-28 | 2009-04-23 | Bosch Rexroth Ag | Hydraulic catapult drive |
-
2011
- 2011-03-01 CN CN2011100569714A patent/CN102398683A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090100829A1 (en) * | 2005-04-28 | 2009-04-23 | Bosch Rexroth Ag | Hydraulic catapult drive |
| CN101100223A (en) * | 2007-08-10 | 2008-01-09 | 霍方华 | Stream catapult for aircraft carrier based airplane |
| CN201172483Y (en) * | 2008-01-01 | 2008-12-31 | 宣建民 | Electromagnetical ejector |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103057719A (en) * | 2012-05-05 | 2013-04-24 | 叶锋 | Magnetic levitation hinder removal type electromagnetic catapult |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| DD01 | Delivery of document by public notice |
Addressee: Liu Weifeng Document name: the First Notification of an Office Action |
|
| DD01 | Delivery of document by public notice |
Addressee: Liu Weifeng Document name: Notification that Application Deemed to be Withdrawn |
|
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20120404 |