CN107472552A - A kind of automatic deviation rectifying device of electromagnetic launch device - Google Patents
A kind of automatic deviation rectifying device of electromagnetic launch device Download PDFInfo
- Publication number
- CN107472552A CN107472552A CN201710825834.XA CN201710825834A CN107472552A CN 107472552 A CN107472552 A CN 107472552A CN 201710825834 A CN201710825834 A CN 201710825834A CN 107472552 A CN107472552 A CN 107472552A
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- CN
- China
- Prior art keywords
- connecting plate
- guiding
- electromagnet
- guiding electromagnet
- 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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Links
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 12
- 239000010959 steel Substances 0.000 claims abstract description 12
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 10
- 229910052742 iron Inorganic materials 0.000 claims description 5
- 235000013399 edible fruits Nutrition 0.000 claims 1
- 230000005484 gravity Effects 0.000 claims 1
- 238000010586 diagram Methods 0.000 description 4
- 239000000725 suspension Substances 0.000 description 2
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—Ground or aircraft-carrier-deck installations for launching aircraft
- B64F1/06—Ground or aircraft-carrier-deck installations for launching aircraft using catapults
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Non-Mechanical Conveyors (AREA)
- Control Of Vehicles With Linear Motors And Vehicles That Are Magnetically Levitated (AREA)
Abstract
A kind of automatic deviation rectifying device of electromagnetic launch device of the present invention is mainly used in aircraft carrier help-fly use, and it mainly includes platform, connecting plate, a pair of guiding electromagnet A and guiding electromagnet B；After a pair of guiding electromagnet A and guiding electromagnet B are started simultaneously, if steel connecting plate is offset to the left, guiding electromagnet A promotion magnetic force increase, guiding electromagnet B promotion magnetic force reduces, and a pair of guiding electromagnets push away to the right steel connecting plate, and vice versa；If connecting plate deflects an angle clockwise, upper end distance of the upper end of connecting plate away from guiding electromagnet B is minimum, repulsive force is maximum, similarly lower end distance of the lower end of connecting plate away from guiding electromagnet A is minimum, repulsive force is maximum, guiding electromagnet A and guiding electromagnet B provides a pair of opposing torques, prevents connecting plate that deflection clockwise occurs；Same principle, if one angle of deflection counterclockwise occurs for connecting plate, guiding electromagnet A and guiding electromagnet B prevent connecting plate that deflection counterclockwise occurs.
Description
Technical field
Present invention is mainly used for aircraft carrier help-fly use.
Background technology
A kind of aircraft carrier electromagnetic launch device of patent of invention applied, application number：2017108195410, it is necessary to
A kind of automatic deviation rectifying device, is properly positioned to platform and linear motor rotor, is allowed to not deviate.
The content of the invention
The present invention is exactly this automatic deviation rectifying device, and it mainly includes platform（1）, connecting plate（9）, a pair of guiding electromagnets
A（7）With guiding electromagnet B（13）；Platform（1）Lower end and steel connecting plate（9）Upper end fix, connecting plate（9）Through straight
Line motor stator（2）Opening（10）, connecting plate（9）Lower end and linear motor rotor（3）Upper end fix, linear electric motors are fixed
Son（2）Opening（10）A pair of guiding electromagnet A being arranged symmetrically are fixed in both sides respectively（7）With guiding electromagnet B（13）, it is oriented to
Electromagnet A（7）Magnet sizes and magnet attribute and guiding electromagnet B（13）Magnet sizes and magnet attribute it is completely the same,
It is and mutually exclusive；Its operation principle is:Carrier-borne aircraft is parked in platform（1）Upper and platform（1）On clamping device carrier-borne aircraft is pressed from both sides
Handle, 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 suspension electromagnetism
Iron A（5）Caused thrust-balancing and linear motor rotor（3）Vertical centerline overlapped with the vertical centerline of linear electric motors,
Start two linear motor stator electrics in left and right simultaneously again（2）A pair of guiding electromagnet A（7）With guiding electromagnet B（13）, due to leading
To electromagnet A（7）Magnet sizes and magnet attribute and guiding electromagnet B（13）Magnet sizes and magnet attribute complete one
Cause, and mutually exclusive, the steel connecting plate being clipped among a pair of guiding electromagnets（9）If offset to the left, guiding electromagnet A
（7）Promotion magnetic force increase, guiding electromagnet B（13）Promotion magnetic force reduce, a pair of guiding electromagnets are by steel connecting plate（9）
Push away to the right, similarly if steel connecting plate（9）Offset to the right, guiding electromagnet A（7）Promotion magnetic force reduce, be oriented to electromagnetism
Iron B（13）The increase of promotion magnetic force, a pair of guiding electromagnets are by steel connecting plate（9）Push away to the left, therefore a pair of guiding electromagnets
There is automatic deviation rectifying function, make connecting plate（9）All the time the centre position in a pair of guiding electromagnets, equally makes linear motor rotor
（3）Vertical centerline overlapped with the vertical centerline of linear electric motors；If connecting plate（9）The vertical misalignment in occurred level face,
That is connecting plate longitudinal centre line（12）With linear electric motors longitudinal centre line（11）It is misaligned, in intersection, if connecting plate
（9）One angle of deflection clockwise, connecting plate occurs（9）Upper end away from guiding electromagnet B（13）Upper end distance it is minimum, herein
Guiding electromagnet B（13）Repulsive force it is maximum and this repulsive force linearly increases, similarly connecting plate（9）Lower end away from leading
To electromagnet A（7）Lower end distance it is minimum, guiding electromagnet A herein（7）Repulsive force it is maximum and this repulsive force is linearly to increase
Big, guiding electromagnet A（7）With guiding electromagnet B（13）A pair of opposing torques are provided, prevent connecting plate（9）Occur clockwise
Deflection；Same principle, if connecting plate（9）One angle of deflection counterclockwise, guiding electromagnet A occurs（7）With guiding electromagnetism
Iron B（13）A pair of opposing torques are provided, prevent connecting plate（9）Deflection counterclockwise occurs.
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 A, 8- base, 9- connecting plates, 10- openings, 11- linear electric motors longitudinal center
Line, 12- connecting plate longitudinal centre lines, 13- guiding electromagnets B.
Fig. 1 is the drawing of the present invention.
Fig. 2 is the vertical cross section schematic diagram of electromagnetic launch device.
Fig. 3 is the schematic top plan view of electromagnetic launch device.
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.
Fig. 6 is the schematic diagram that connecting plate occurs longitudinally to deflect.
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：Connecting plate 9
Repulsive force is produced to guiding electromagnet A and guiding electromagnet B.
Claims (1)
1. a kind of automatic deviation rectifying device of electromagnetic launch device, it is characterized in that：It mainly includes platform（1）, connecting plate（9）, one
To guiding electromagnet A（7）With guiding electromagnet B（13）；Platform（1）Lower end and steel connecting plate（9）Upper end fix, connect
Plate（9）Through linear motor stator electric（2）Opening（10）, connecting plate（9）Lower end and linear motor rotor（3）Upper end consolidate
It is fixed, linear motor stator electric（2）Opening（10）A pair of guiding electromagnet A being arranged symmetrically are fixed in both sides respectively（7）It is electric with being oriented to
Magnet B（13）, guiding electromagnet A（7）Magnet sizes and magnet attribute and guiding electromagnet B（13）Magnet sizes and magnet
Attribute is completely the same, and mutually exclusive；Its operation principle is:Carrier-borne aircraft is parked in platform（1）Upper and platform（1）On clamping
Device clamps carrier-borne aircraft, starts levitating electromagnet A（5）And levitating electromagnet B（6）Power supply, levitating electromagnet A（5）Top
Play linear motor rotor（3）And platform（1）, now linear motor rotor（3）, platform（1）And platform（1）On carrier-borne aircraft it is total
Gravity and levitating electromagnet A（5）Caused thrust-balancing and linear motor rotor（3）Vertical centerline and linear electric motors it is perpendicular
Overlapped to center line, then start two linear motor stator electrics in left and right simultaneously（2）A pair of guiding electromagnet A（7）With guiding electromagnetism
Iron B（13）, due to guiding electromagnet A（7）Magnet sizes and magnet attribute and guiding electromagnet B（13）Magnet sizes and magnetic
Body attribute is completely the same, and mutually exclusive, the steel connecting plate being clipped among a pair of guiding electromagnets（9）If offset to the left,
Guiding electromagnet A（7）Promotion magnetic force increase, guiding electromagnet B（13）Promotion magnetic force reduce, a pair of guiding electromagnets are by steel
Connecting plate processed（9）Push away to the right, similarly if steel connecting plate（9）Offset to the right, guiding electromagnet A（7）Promotion magnetic force subtract
It is small, guiding electromagnet B（13）The increase of promotion magnetic force, a pair of guiding electromagnets are by steel connecting plate（9）Push away to the left, therefore a pair
Guiding electromagnet has automatic deviation rectifying function, makes connecting plate（9）All the time the centre position in a pair of guiding electromagnets, equally make straight
Line electric mover（3）Vertical centerline overlapped with the vertical centerline of linear electric motors；If connecting plate（9）Occurred level face
Vertical misalignment, i.e. connecting plate longitudinal centre line（12）With linear electric motors longitudinal centre line（11）It is misaligned, in intersection, such as
Fruit connecting plate（9）One angle of deflection clockwise, connecting plate occurs（9）Upper end away from guiding electromagnet B（13）Upper end distance
Minimum, herein guiding electromagnet B（13）Repulsive force it is maximum and this repulsive force linearly increases, similarly connecting plate（9）
Lower end away from guiding electromagnet A（7）Lower end distance it is minimum, guiding electromagnet A herein（7）Repulsive force is maximum and this repulsion
Power linearly increases, guiding electromagnet A（7）With guiding electromagnet B（13）A pair of opposing torques are provided, prevent connecting plate（9）
Deflection clockwise occurs；Same principle, if connecting plate（9）One angle of deflection counterclockwise, guiding electromagnet A occurs（7）
With guiding electromagnet B（13）A pair of opposing torques are provided, prevent connecting plate（9）Deflection counterclockwise occurs.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710825834.XA CN107472552A (en) | 2017-09-14 | 2017-09-14 | A kind of automatic deviation rectifying device of electromagnetic launch device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710825834.XA CN107472552A (en) | 2017-09-14 | 2017-09-14 | A kind of automatic deviation rectifying device of electromagnetic launch device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107472552A true CN107472552A (en) | 2017-12-15 |
Family
ID=60585282
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710825834.XA Withdrawn CN107472552A (en) | 2017-09-14 | 2017-09-14 | A kind of automatic deviation rectifying device of electromagnetic launch device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107472552A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110131295A (en) * | 2018-02-09 | 2019-08-16 | 卡尔蔡司医疗技术股份公司 | Balancing device for rotary equipment |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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
- 2017-09-14 CN CN201710825834.XA patent/CN107472552A/en not_active Withdrawn
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110131295A (en) * | 2018-02-09 | 2019-08-16 | 卡尔蔡司医疗技术股份公司 | Balancing device for rotary equipment |
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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 | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20171215 |
|
| WW01 | Invention patent application withdrawn after publication |