CN204341411U - Carrier-borne aircraft deck electromagnetic deceleration band - Google Patents
Carrier-borne aircraft deck electromagnetic deceleration band Download PDFInfo
- Publication number
- CN204341411U CN204341411U CN201420816572.2U CN201420816572U CN204341411U CN 204341411 U CN204341411 U CN 204341411U CN 201420816572 U CN201420816572 U CN 201420816572U CN 204341411 U CN204341411 U CN 204341411U
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- China
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- carrier
- borne aircraft
- stator winding
- deck
- deceleration band
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- Expired - Fee Related
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Abstract
The utility model is specifically related to a kind of carrier-borne aircraft deck electromagnetic deceleration band, comprise the stator winding be installed in deck-landing runway and the rotor windings being installed in carrier-borne aircraft tail, described stator winding in landing runway linearly segment type be intervally arranged, described stator winding by organizing coil and silicon steel plate forms more; Described rotor windings is made up of coil and dull and stereotyped silicon steel.The electromagnetic eddy that carrier-borne aircraft deck of the present utility model electromagnetic deceleration band is formed provides a kind of anti-drag to carrier-borne aircraft fuselage, and make carrier-borne aircraft slow down in shorter distance and come to a complete stop, more traditional obstruction cable wire pins down method stability and safety is improved; Segment type stator winding makes the conduct successively of anti-drag, and retardance, without running through, effectively prevents fuselage sideslip and the generation of facing upward the accident of turning over.
Description
Technical field
The utility model relates to a kind of carrier-borne aircraft speed reduction gearing, particularly relates to a kind of carrier-borne aircraft deck electromagnetic deceleration band.
Background technology
Carrier-borne aircraft will land, come to a complete stop in short-range type aircraft carrier deck, the way all adopting elasticity obstruction cable wire to pin down is stopped in limited distance to force carrier-borne aircraft, but it exists following defect, one is that carrier-borne aircraft pintle is failed to hook and stopped cable wire and cause carrier-borne aircraft to stop; Two is need the transfer personnel in type aircraft carrier deck to be taken off from the pintle of carrier-borne aircraft by obstruction cable wire after carrier-borne aircraft comes to a complete stop, not only time-consuming but also inconvenient; Three is stop the risk that cable wire may exist fracture; Four is hook at pintle to stop moment of cable wire and there is mechanical collision, and produce concuss, poor stability, is prone to accidents.
Summary of the invention
The purpose of this utility model is to propose a kind of energy deck that is stable, that effectively carrier-borne aircraft is slowed down electromagnetic deceleration band.
The purpose of this utility model is achieved in that carrier-borne aircraft deck electromagnetic deceleration band, comprise the stator winding be installed in deck-landing runway and the rotor windings being installed in carrier-borne aircraft tail, described stator winding in landing runway linearly segment type be intervally arranged, described stator winding by organizing coil and silicon steel plate forms more; Described rotor windings is made up of coil and dull and stereotyped silicon steel.
Further, described rotor windings is connected with carrier-borne aircraft tail by adjustment member, to adjust the direction of rotor windings and stator winding.
Further, described adjustment member is roof jack.
Further, described stator winding is equidistantly arranged.
Further, be equiped with boosting electromagnetic belt in the deck in described landing runway boundary end front, described boosting electromagnetic belt is made up of the stator winding of arranging continuously, and its polarity is contrary with the polarity of described electromagnetic deceleration band stator winding.
The magnetic field eddy current that carrier-borne aircraft deck of the present utility model electromagnetic deceleration band is formed provides a kind of anti-drag to carrier-borne aircraft fuselage, and make carrier-borne aircraft slow down in shorter distance and come to a complete stop, more traditional obstruction cable wire pins down method stability and safety is improved; Segment type stator winding makes the conduct successively of anti-drag, and retardance, without running through, effectively prevents fuselage sideslip and the generation of facing upward the accident of turning over.
Accompanying drawing explanation
Concrete structure of the present utility model is provided by following drawings and Examples:
Fig. 1 is the structural representation of rotor windings;
Fig. 2 is the structural representation of stator winding.
Legend: 1. roof jack, 2. rotor winding coil, 3. rotor windings dull and stereotyped silicon steel, 4. stator winding silicon steel plate, 5. landing runway, 6. stator winding coil, 7. tag line.
Detailed description of the invention
The utility model by the restriction of following embodiment, can not determine concrete embodiment according to the technical solution of the utility model and actual conditions.
Embodiment 1: as shown in Figure 1-2, carrier-borne aircraft deck electromagnetic deceleration band, comprise the stator winding be installed in deck-landing runway 5 and the rotor windings being installed in carrier-borne aircraft tail, described stator winding in landing runway 5 linearly segment type be intervally arranged, described stator winding by organizing coil 6 and silicon steel plate 4 forms more; Described rotor windings is made up of coil 2 and dull and stereotyped silicon steel 3, and described rotor windings is connected with carrier-borne aircraft tail by adjustment member, and to adjust the direction of rotor windings and stator winding, described adjustment member is roof jack 1.
When carrier-borne aircraft lands above deck, segment type stator winding electrifying, stator winding coil 6 produces magnetic field eddy current, and the foreign field that this magnetic field eddy current and rotor windings are formed interacts, and can produce thrust or pulling force.Adjust rotor windings by roof jack 1, make rotor windings and stator winding keep elementary errors anomaly capable, when carrier-borne aircraft slides forward, rotor windings cutting magnetic line, namely produces anti-drag, thus retardance carrier-borne aircraft preshoot inertia.
The present embodiment adjusts rotor windings angle at any time by roof jack 1, and when rotor windings and stator winding keep elementary errors anomaly capable, cutting magnetic line is best, and anti-drag is maximum; The stator winding of segment type makes the conduct successively of anti-drag, and retardance process, without running through, can be prevented fuselage to face upward and turn over and sideslip.The preferably equidistantly arrangement in landing runway 5 of segment type stator winding.
Embodiment 2: consider that carrier-borne aircraft shuts down the failed possibility of existence first; described landing runway 5 is demarcated to hold in the deck in front and is equiped with boosting electromagnetic belt; described boosting electromagnetic belt is made up of the stator winding of arranging continuously, and its polarity is contrary with the polarity of described electromagnetic deceleration band stator winding.Because boosting electromagnetic belt is made up of stator winding, its structure compares electromagnetic deceleration band does not have special feature, and Gu Tuzhong does not draw.Boosting electromagnetic belt produces thrust, contributes to carrier-borne aircraft and goes around.
It should be noted that, in embodiment 1 and embodiment 2, in order to provide orientation reference to carrier-borne aircraft driver, rotor windings is made to be in the magnetic field eddy current of stator winding formation all the time, not easily cause anti-drag to reduce because departing from or lose, landing runway 5 is drawn tag line 7.
Above technical characteristic is only embodiment of the present utility model, can increase and decrease inessential technical characteristic according to actual needs, meet the needs of different situations.
Claims (5)
1. a carrier-borne aircraft deck electromagnetic deceleration band, comprise the stator winding be installed in deck-landing runway and the rotor windings being installed in carrier-borne aircraft tail, it is characterized in that: described stator winding in landing runway linearly segment type be intervally arranged, described stator winding by organizing coil and silicon steel plate forms more; Described rotor windings is made up of coil and dull and stereotyped silicon steel.
2. carrier-borne aircraft deck as claimed in claim 1 electromagnetic deceleration band, is characterized in that: described rotor windings is connected with carrier-borne aircraft tail by adjustment member, to adjust the direction of rotor windings and stator winding.
3. carrier-borne aircraft deck as claimed in claim 2 electromagnetic deceleration band, is characterized in that: described adjustment member is roof jack.
4. the carrier-borne aircraft deck electromagnetic deceleration band as described in claims 1 to 3 any one, is characterized in that: described stator winding is equidistantly arranged.
5. the carrier-borne aircraft deck electromagnetic deceleration band as described in claims 1 to 3 any one, it is characterized in that: in the deck in described landing runway boundary end front, be equiped with boosting electromagnetic belt, described boosting electromagnetic belt is made up of the stator winding of arranging continuously, and its polarity is contrary with the polarity of described electromagnetic deceleration band stator winding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420816572.2U CN204341411U (en) | 2014-12-22 | 2014-12-22 | Carrier-borne aircraft deck electromagnetic deceleration band |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420816572.2U CN204341411U (en) | 2014-12-22 | 2014-12-22 | Carrier-borne aircraft deck electromagnetic deceleration band |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204341411U true CN204341411U (en) | 2015-05-20 |
Family
ID=53224701
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420816572.2U Expired - Fee Related CN204341411U (en) | 2014-12-22 | 2014-12-22 | Carrier-borne aircraft deck electromagnetic deceleration band |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204341411U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106467173A (en) * | 2015-08-18 | 2017-03-01 | 吴进森 | Aircraft carrier electromagnetism landing technological innovation scheme |
| CN108100286A (en) * | 2018-02-10 | 2018-06-01 | 白景魁 | The method that a kind of high pressure gas beam relay boosting of aircraft carrier slides jump formula landing |
-
2014
- 2014-12-22 CN CN201420816572.2U patent/CN204341411U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106467173A (en) * | 2015-08-18 | 2017-03-01 | 吴进森 | Aircraft carrier electromagnetism landing technological innovation scheme |
| CN108100286A (en) * | 2018-02-10 | 2018-06-01 | 白景魁 | The method that a kind of high pressure gas beam relay boosting of aircraft carrier slides jump formula landing |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20160503 Address after: 830000, the Xinjiang Uygur Autonomous Region Urumqi hi tech Industrial Development Zone, science first street, No. 384, building 26, science and Technology Department, building 1 Patentee after: XINJIANG JIAHUI XINYUAN ENVIRONMENT PROTECTION TECHNOLOGY CO., LTD. Address before: Beijing road 830011 south the Xinjiang Uygur Autonomous Region fashion Tsui district of Urumqi City No. 3 Building 1 unit 201 room Patentee before: Tian Chaoyang |
|
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150520 Termination date: 20181222 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |