CN204527664U - The carrier-based aircraft ejection system that magnetic suspension force and power difference formula microscope carrier accelerate - Google Patents
The carrier-based aircraft ejection system that magnetic suspension force and power difference formula microscope carrier accelerate Download PDFInfo
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- CN204527664U CN204527664U CN201520209235.1U CN201520209235U CN204527664U CN 204527664 U CN204527664 U CN 204527664U CN 201520209235 U CN201520209235 U CN 201520209235U CN 204527664 U CN204527664 U CN 204527664U
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- magnetic suspension
- carrier
- aircraft
- buoyancy
- deck
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Abstract
The utility model magnetic suspension force and the power carrier-based aircraft ejection system that formula microscope carrier accelerates respectively belongs to the carrier-based aircraft ejection system accelerated with aircraft microscope carrier with two slideway.Comprise upper platform deck and the lower tween deck of aircraft carrier, takeoff runway is provided with two parallel runway seams, and on lower tween deck, correspondence is provided with two magnetic suspension buoyancy tracks; Be provided with two pieces above carrier aircraft platform and accelerate slurcam; Be provided with stay bearing plate below carrier aircraft platform and be positioned among runway seam, being connected with weight support frame and magnetic suspension buoyancy plate below stay bearing plate, between magnetic suspension buoyancy plate and magnetic suspension buoyancy track, having fixed interval distance.Advantage: aircraft can not by up-down vibration on magnetic suspension dynamical type microscope carrier, and the energy pulsation-free impelling of magnetic suspension dynamical type microscope carrier and cataplane take off.Magnetic suspension dynamical type microscope carrier matches with aircraft-carrier-deck structure, has fixing impelling track, structure simple, good reliability.
Description
Technical field
The utility model belongs to the magnetic levitation electromagnetic catapult on a kind of aircraft carrier, particularly with the carrier-based aircraft ejection system accelerated with aircraft microscope carrier of two slideway.
Background technology
Chinese patent 201110153945.3 " steam ejection boosting device for taking off of airplane " disclose comprise flight deck, slide pipeline, steam ejection booster, aircraft adaptor union, be provided with deceleration reset attachment sliding pipeline front portion, be provided with heating arrangement sliding pipeline rear portion; Described steam ejection booster is by the uncovered warhead shape housing in rear portion, to be located in housing and to make the dividing plate that housing front portion forms high-temperature bearing water pot, housing rear portion forms high-temperature steam generation chamber, be covered with the heat vapourizer excessively in high-temperature steam generation chamber vertically, be located at housing afterbody and form with the water jet standpipe launching control cock with being located on high-temperature bearing water pot through the coolant inlet pipe with boiler check valve that high-temperature steam generation chamber communicates with high-temperature bearing water pot; It is anterior that the water injector of water jet standpipe is positioned at high-temperature steam generation chamber, is provided with Sewage treatment pipeline sliding below pipeline.The shortcoming of this patent is complex structure, and reliability is bad.
Summary of the invention
The purpose of this utility model is to provide the carrier aircraft platform that magnetic suspension buoyancy and magnetic suspension power act on respectively, and this carrier aircraft platform matches with aircraft-carrier-deck structure, has fixing impelling track, structure simple, the carrier-based aircraft ejection system of good reliability.
Structure of the present utility model is:
The carrier-based aircraft ejection system that magnetic suspension force and power difference formula microscope carrier accelerate, comprise upper platform deck 1 and the lower tween deck 2 of aircraft carrier, it is characterized in that: take off on runway on upper platform deck 1, be provided with two runways with runway equal length and parallel and stitch 3,1 two, upper platform deck runway stitches on the lower tween deck 2 of 3 correspondences, is provided with and stitches 3 equal length and parallel two magnetic suspension buoyancy tracks 4 with runway;
Also comprise magnetic suspension dynamical type microscope carrier 5, this magnetic suspension dynamical type microscope carrier 5 comprises again carrier aircraft platform 6, longitudinal bearing plate 8, weight support frame 9 and magnetic suspension buoyancy plate 10;
Be provided with two pieces of longitudinal bearing plates, 8, two pieces of longitudinal bearing plates 8 below carrier aircraft platform 6 to be parallel to each other, these two pieces longitudinal bearing plates 8 lay respectively among two runway seams 3 on upper platform deck 1, and each longitudinal bearing plate 8 is connected with weight support frame 9 below; With the weight support frame 9 of magnetic suspension buoyancy track 4 correspondence position below the magnetic suspension buoyancy plate 10 be provided with below magnetic suspension buoyancy plate 10, two weight support framves 9 lay respectively at above two magnetic suspension buoyancy tracks 4;
The weight support frame 9 of each longitudinal bearing plate 8 both sides is provided with magnetic suspension power plate 15, and each magnetic suspension power plate 15 upper position is provided with magnetic suspension power rail 16, and magnetic suspension power rail 16 is connected with the lower surface on upper platform deck 1;
Often organize the clearance space distance having magnetic suspension force to need between magnetic suspension buoyancy track 4 and magnetic suspension buoyancy plate 10;
Often organize the clearance space distance having magnetic suspension force to need between magnetic suspension power plate 15 and magnetic suspension power rail 16.Weight support frame 9 is circular or triangle.
Carrier aircraft platform 6 is supported by two pieces of longitudinal bearing plates 8, weight support frame 9 below the longitudinal bearing plate 8 of every block provides magnetic suspension force to support by one group of magnetic suspension buoyancy track 4 and magnetic suspension buoyancy plate 10, weight support frame 9 below the longitudinal bearing plate 8 of every block provides magnetcisuspension power, carrier aircraft platform 6 with magnetcisuspension power driven by two groups of magnetic suspension power plates 15 and magnetic suspension power rail 16.
Two groups of magnetic suspension power plates 15 of each weight support frame 9 both sides and magnetic suspension power rail 16 symmetrically, provide identical power, the promotion weight support frame 9 of balance.Two weight support framves, 9 points of other two groups of magnetic suspension power plates 15 are identical with the magnetic suspension power of magnetic suspension power rail 16, make carrier aircraft platform 6 be balanced driving.
Advantage of the present utility model: the relative position up and down of magnetic suspension dynamical type microscope carrier and upper platform deck, lower tween deck and magnetic suspension buoyancy track is stablized, aircraft can not by up-down vibration on the carrier aircraft platform of magnetic suspension dynamical type microscope carrier, and the energy pulsation-free impelling of magnetic suspension dynamical type microscope carrier and cataplane take off.
Two groups of magnetic suspension power plates of each weight support frame both sides and magnetic suspension power rail symmetrically, provide identical power, the promotion weight support frame of balance.Two weight support framves divide other two groups of magnetic suspension power plates identical with the magnetic suspension power of magnetic suspension power rail, make carrier aircraft platform be balanced driving.
Magnetic suspension dynamical type microscope carrier matches with aircraft-carrier-deck structure, has fixing impelling track, structure simple, good reliability.
The waterproofing design of weight support frame, stitches from runway the water flowed down and can not flow to magnetic suspension buoyancy plate, impelling can normally be worked.
Accompanying drawing explanation
Fig. 1 is vertical section structure schematic diagram of the present invention;
Fig. 2 is weight support frame is circular cross section structure schematic diagram of the present invention;
Fig. 3 is the leg-of-mutton cross section structure schematic diagram of the present invention of weight support frame;
In figure, 1 be upper platform deck, 2 are lower tween deck, 3 are runway seams, 4 are magnetic suspension buoyancy tracks, 5 are magnetic suspension dynamical type microscope carriers, 6 are carrier aircraft platforms, 8 are longitudinal bearing plates, 9 are weight support framves, 10 are magnetic suspension buoyancy plates, 15 are magnetic suspension power plates, 16 is magnetic suspension power rails.
Detailed description of the invention
The carrier-based aircraft ejection system that embodiment 1, magnetic suspension force and power difference formula microscope carrier accelerates
As Fig. 1,2,3, comprise upper platform deck 1 and the lower tween deck 2 of aircraft carrier, take off on runway on upper platform deck 1, be provided with two runways with runway equal length and parallel and stitch 3,1 two, upper platform deck runway stitches on the lower tween deck 2 of 3 correspondences, is provided with and stitches 3 equal length and parallel two magnetic suspension buoyancy tracks 4 with runway;
Also comprise magnetic suspension dynamical type microscope carrier 5, this magnetic suspension dynamical type microscope carrier 5 comprises again carrier aircraft platform 6, longitudinal bearing plate 8, weight support frame 9 and magnetic suspension buoyancy plate 10;
Be provided with two pieces of longitudinal bearing plates, 8, two pieces of longitudinal bearing plates 8 below carrier aircraft platform 6 to be parallel to each other, these two pieces longitudinal bearing plates 8 lay respectively among two runway seams 3 on upper platform deck 1, and each longitudinal bearing plate 8 is connected with weight support frame 9 below; With the weight support frame 9 of magnetic suspension buoyancy track 4 correspondence position below the magnetic suspension buoyancy plate 10 be provided with below magnetic suspension buoyancy plate 10, two weight support framves 9 lay respectively at above two magnetic suspension buoyancy tracks 4;
The weight support frame 9 of each longitudinal bearing plate 8 both sides is provided with magnetic suspension power plate 15, and each magnetic suspension power plate 15 upper position is provided with magnetic suspension power rail 16, and magnetic suspension power rail 16 is connected with the lower surface on upper platform deck 1;
Often organize the clearance space distance having magnetic suspension force to need between magnetic suspension buoyancy track 4 and magnetic suspension buoyancy plate 10;
Often organize the clearance space distance having magnetic suspension force to need between magnetic suspension power plate 15 and magnetic suspension power rail 16.
The lower tween deck 2 of magnetic suspension buoyancy track 4 periphery has ditch or water suction mat.Weight support frame 9 is circular or triangle.
Claims (3)
1. the carrier-based aircraft ejection system of magnetic suspension force and the acceleration of power difference formula microscope carrier, comprise upper platform deck (1) and the lower tween deck (2) of aircraft carrier, it is characterized in that: take off on runway in upper platform deck (1), be provided with two runways with runway equal length and parallel to stitch (3), on the lower tween deck (2) that (1) two, upper platform deck runway seam (3) is corresponding, be provided with and stitch (3) equal length and parallel two magnetic suspension buoyancy tracks (4) with runway;
Also comprise magnetic suspension dynamical type microscope carrier (5), this magnetic suspension dynamical type microscope carrier (5) comprises again carrier aircraft platform (6), longitudinal bearing plate (8), weight support frame (9) and magnetic suspension buoyancy plate (10);
Two pieces of longitudinal bearing plates (8) are provided with below carrier aircraft platform (6), two pieces of longitudinal bearing plates (8) are parallel to each other, these two pieces of longitudinal bearing plates (8) lay respectively among two runways seam (3) on upper platform deck (1), and each longitudinal bearing plate (8) is connected with weight support frame (9) below; With the weight support frame (9) of magnetic suspension buoyancy track (4) correspondence position below be provided with magnetic suspension buoyancy plate (10), the magnetic suspension buoyancy plate (10) below two weight support framves (9) lays respectively at above two magnetic suspension buoyancy tracks (4);
The weight support frame (9) of each longitudinal bearing plate (8) both sides is provided with magnetic suspension power plate (15), each magnetic suspension power plate (15) upper position is provided with magnetic suspension power rail (16), and magnetic suspension power rail (16) is connected with the lower surface of upper platform deck (1);
Often organize the clearance space distance having magnetic suspension force to need between magnetic suspension buoyancy track (4) and magnetic suspension buoyancy plate (10);
Often organize the clearance space distance having magnetic suspension force to need between magnetic suspension power plate (15) and magnetic suspension power rail (16).
2. the carrier-based aircraft ejection system of magnetic suspension force according to claim 1 and the acceleration of power difference formula microscope carrier, is characterized in that: the lower tween deck (2) of magnetic suspension buoyancy track (4) periphery has ditch or water suction mat.
3. the carrier-based aircraft ejection system of magnetic suspension force according to claim 2 and the acceleration of power difference formula microscope carrier, is characterized in that: weight support frame (9) is circular or triangle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520209235.1U CN204527664U (en) | 2015-04-02 | 2015-04-02 | The carrier-based aircraft ejection system that magnetic suspension force and power difference formula microscope carrier accelerate |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520209235.1U CN204527664U (en) | 2015-04-02 | 2015-04-02 | The carrier-based aircraft ejection system that magnetic suspension force and power difference formula microscope carrier accelerate |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204527664U true CN204527664U (en) | 2015-08-05 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520209235.1U Expired - Fee Related CN204527664U (en) | 2015-04-02 | 2015-04-02 | The carrier-based aircraft ejection system that magnetic suspension force and power difference formula microscope carrier accelerate |
Country Status (1)
| Country | Link |
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| CN (1) | CN204527664U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105775154A (en) * | 2016-05-12 | 2016-07-20 | 孙立民 | General launching platform for unmanned aerial vehicle |
| CN109878753A (en) * | 2019-01-30 | 2019-06-14 | 北京交通大学 | Aircraft magnetic suspension boosting and acquisition equipment |
| WO2020140178A1 (en) * | 2018-12-30 | 2020-07-09 | 中国科学院沈阳自动化研究所 | On-orbit launching apparatus |
-
2015
- 2015-04-02 CN CN201520209235.1U patent/CN204527664U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105775154A (en) * | 2016-05-12 | 2016-07-20 | 孙立民 | General launching platform for unmanned aerial vehicle |
| WO2020140178A1 (en) * | 2018-12-30 | 2020-07-09 | 中国科学院沈阳自动化研究所 | On-orbit launching apparatus |
| CN109878753A (en) * | 2019-01-30 | 2019-06-14 | 北京交通大学 | Aircraft magnetic suspension boosting and acquisition equipment |
| CN109878753B (en) * | 2019-01-30 | 2020-09-18 | 北京交通大学 | Magnetic suspension boosting and capturing device for aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150805 Termination date: 20160402 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |