CN1530288A - Circular magnetic suspension flying device - Google Patents
Circular magnetic suspension flying device Download PDFInfo
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- CN1530288A CN1530288A CNA031194338A CN03119433A CN1530288A CN 1530288 A CN1530288 A CN 1530288A CN A031194338 A CNA031194338 A CN A031194338A CN 03119433 A CN03119433 A CN 03119433A CN 1530288 A CN1530288 A CN 1530288A
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- cabin
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- cabin body
- fan
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Abstract
A magnetic levitation type ring-shaped flying vehicle with amphibious function is composed of ring-shaped cabin body, internal and external fan rings and fan cover. Said internal and external fan rings are respectively installed to the internal and external ring tracks on the internal and external peripheral surfaces of cabin body. When the high-power coils at inner and outer sides of cabin body are doing work, the internal and external fan rings are driven by strong magnetic levitation force to rotate at high speed along said tracks, so generating strong lifting force. Controlling the rotation speed and direction of fan ring, gravitation center, and flying attitude can control the flying of said flying vehicle.
Description
Invention field
The present invention relates to a kind of aircraft, be specially a kind of annular magnetic hovering flight device.It is a kind of aircraft that utilizes the magnetic field transferring power to reach air objective.Not only can aloft fly, also can in water, travel.
Background technology
Existing takeoff and landing need very big place, and when flight, raising rapidly and turning to all needs long motion of translation track; And the kinematic velocity of autogyro is slower.Though the empty amphibian of water is arranged at present, do not have the function of diving, this is because the flight dynamic devices of aircraft needs air-breathing.
Summary of the invention
But purpose of the present invention just provides a kind of vertical takeoff and landing, and lift is big, promotes soon, moves flexibly, and good airproof performance can high-altitude flight and diving, the empty amphibious annular magnetic hovering flight device of water.
Technical scheme of the present invention is: comprise the annular cabin body, outer sector circular, fan cover, interior wing ring, on the inside and outside side face of cabin body, be equipped with circular orbit, inside and outside fan ring is loaded on respectively on the described track, and and track between leave the gap; Interior outer sector circular is formed by ring body and a plurality of uniform flabellum that is connected the one side, is embedded with uniform permanent magnet at the adjacent surface of ring body and track, and the diameter of axle of flabellum is in being connected in the outer sector circular on the cooresponding fan blade angles controller; Be equipped with the fan cover at exterior wing, this fan cover is connected with the external side in cabin; In the outside of cabin body a plurality of flight attitude adjusters that are uniformly distributed along the circumference are housed, alighting gear are housed in the bottom side of cabin body; Magnet coil all is equipped with at inner and outer circumferential surfaces place in the body of cabin, is provided with engine installation and control system in the body of cabin, and the control signal of control system is connected with the control end of flight attitude adjuster, engine installation, fan blade angles controller respectively.
Described flight attitude adjuster is made of telescopic baffle and controller, and controller is loaded in the body of cabin, and it has expansion link to be connected with the inner of telescopic baffle, and the cooresponding slit of external side, cabin is stretched out in the outer end of telescopic baffle.
Described cabin body is divided into driving compartment, accommodation, deposit cabin, piggyback pod, six zones of survival capsule.
Described driving compartment is three-dimensional compass structure, and its control end is connected with described control system.
When the inside and outside both sides of annular compartment body in-to-in of the present invention annular large-power coil does work, inside and outside fan ring is driven by powerful magnetic levitation, make it along osed top circular orbit high speed revolution, when flabellum plane and plane of rotation maintenance certain included angle, flabellum acts on air, produce powerful thrust thus, overcome aircraft from gravity, aircraft is taken off in air, and by the control of hand of rotation and the center of gravity control and the flight attitude adjuster of the rotative speed of fan ring, interior outer sector circular, aircraft flight freely.Because its power transmits by magnetic field, thus the cabin body good seal of aircraft, can be withstand voltage, anticorrosion, aircraft also can navigate by water in water, has water, empty amphibious function.
Description of drawings
Fig. 1 is a perspective view of the present invention;
Fig. 2 is the A-A cutaway view of Fig. 1;
Fig. 3 is a cabin of the present invention body subregion scheme drawing;
Fig. 4 is flabellum of the present invention and magnet ring connection diagram, and wherein b figure is the left view of a figure;
Fig. 5 is the scheme drawing of mode of operation of the present invention, wherein:
A figure is the present invention's state of flight that makes progress;
B figure is static or slow state when mobile;
C figure is the state that flies downwards;
D figure is another kind of static or slow state when mobile;
The specific embodiment
Referring to Fig. 1-Fig. 4, comprise cabin body 1, outer sector circular 2, fan cover 3, the interior wing ring 4 of annular, on cabin body 1 inside and outside side face, be equipped with circular orbit 5, inside and outside fan ring 2,4 is loaded on respectively on the described track 5, and and track between leave the gap; Interior outer sector circular is formed by ring body 21 and a plurality of uniform flabellum 22 that is connected the one side, is embedded with uniform permanent magnet 23 at the adjacent surface of ring body and track, in the axle 24 of flabellum 22 radially is connected on the interior cooresponding fan blade angles controller 25 of outer sector circular; Being provided with fan cover 6 at outer sector circular 2 is connected with the outside of cabin body 1; In the outside of cabin body 1 a plurality of flight attitude adjusters 7 that are uniformly distributed along the circumference are housed, alighting gear 8 are housed in the bottom side of cabin body 1; Magnet coil 9 all is equipped with at inner and outer circumferential surfaces place in cabin body 1, in the body of cabin, be provided with engine installation and control system, the control signal of control system is connected with the control end of flight attitude adjuster, engine installation, fan blade angles controller respectively, is used for controlling the work of these devices.
Described flight attitude adjuster is made of telescopic baffle 71 and controller 72, and controller 72 is loaded in the cabin body 1, and it has expansion link 73 to be connected with the inner of telescopic baffle 71, and cooresponding slit, cabin body 1 outside is stretched out in the outer end of telescopic baffle 71.
Described cabin body 1 is divided into driving compartment 11, accommodation 12, deposit cabin 13, piggyback pod 14, bunker 15,16 6 zones of survival capsule.
Described driving compartment 11 is three-dimensional compass structure, and its control end is connected with described control system.
Referring to Fig. 5, the magnetic field that the present invention produces by the coil in the cabin body 19 to the fan ring 4 and 2 in the interior outside, promotes it along track 5 rotations with transmission of power.
Flabellum 22 on interior outer sector circular 4,2 can be regulated its in-plane by angle controller 25, promptly regulates flabellum 22 planes and the size of fanning the angle that encircles plane of rotation and positive and negative.If the flabellum plane has angle can produce axial power with fan ring plane of rotation.Inclination angle by the flabellum plane like this, the combination different with the rotation direction of interior outer sector circular just can produce the power of different directions, is respectively described below:
In Fig. 5 a, under the situation that the acting of interior outer sector circular equates, the flabellum reverse inclination of interior outer sector circular, and opposite rotation direction, and the flabellum direction of tilt is identical with rotation direction, the cabin body can not rotate, aircraft fly vertically (making progress).
In Fig. 5 b, under the situation that interior outer sector circular acting equates, make the flabellum inclined in opposite directions of interior wing ring, other is identical with a figure, and then interior outer sector circular produces opposite axial force, and the cabin body can not rotate, and aircraft is in static or slow shifting state.
In Fig. 5 c, with the equal inclined in opposite directions of flabellum on the interior outer sector circular among a figure, rotation direction is constant, then produces axially downward power, makes aircraft descending.
Situation in Fig. 5 d and b figure is similar, being contrary among the direction of tilt of rotation direction and flabellum and the b figure just, so it comes to the same thing, aircraft is static or moves slowly.
From above-mentioned structural analysis as can be known the present invention following advantage is arranged:
1, VTOL, lift is big, and speed-raising is fast.
2, turning radius is little, mobile flexibly, static in the air.
3, take off and the place restriction of landing little.
4, use electric power, noise is little.
5, can in fluid, walk (water and air).
6, because the acting fan blade area is big, so much bigger apart from aspect ratio than other aviation aircrafts.
7, can directly enter the earth low orbit operation as installing rocket engine additional.
8, can the little ring of big ring sleeve, female ring set subring, safety escape or subtasking.
9, good reliability occurs separately when intentional at interior wing or exterior wing, and aircraft still can move landing.
10, weight bearing power is big.
Claims (4)
1, a kind of annular magnetic hovering flight device is characterized in that: comprise the annular cabin body, outer sector circular, fan cover, interior wing ring, on the inside and outside side face of cabin body, be equipped with circular orbit, inside and outside fan ring is loaded on respectively on the described track, and and track between leave the gap; Interior outer sector circular is formed by ring body and a plurality of uniform flabellum that is connected the one side, is embedded with uniform permanent magnet at the adjacent surface of ring body and track, and the diameter of axle of flabellum is in being connected in the outer sector circular on the cooresponding fan blade angles controller; Be equipped with the fan cover at exterior wing, this fan cover is connected with the external side in cabin; In the outside of cabin body a plurality of flight attitude adjusters that are uniformly distributed along the circumference are housed, alighting gear are housed in the bottom side of cabin body; Magnet coil all is equipped with at inner and outer circumferential surfaces place in the body of cabin, is provided with engine installation and control system in the body of cabin, and the control signal of control system is connected with the control end of flight attitude adjuster, engine installation, fan blade angles controller respectively.
2, annular magnetic hovering flight device according to claim 1, it is characterized in that: described flight attitude adjuster is made of telescopic baffle and controller, controller is loaded in the body of cabin, it has expansion link to be connected with the inner of telescopic baffle, and the cooresponding slit of external side, cabin is stretched out in the outer end of telescopic baffle.
3, annular magnetic hovering flight device according to claim 1 is characterized in that: described cabin body is divided into driving compartment, accommodation, deposit cabin, piggyback pod, six zones of survival capsule.
4, annular magnetic hovering flight device according to claim 4 is characterized in that: described driving compartment is three-dimensional compass structure, and its control end is connected with described control system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA031194338A CN1530288A (en) | 2003-03-12 | 2003-03-12 | Circular magnetic suspension flying device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA031194338A CN1530288A (en) | 2003-03-12 | 2003-03-12 | Circular magnetic suspension flying device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1530288A true CN1530288A (en) | 2004-09-22 |
Family
ID=34285100
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA031194338A Pending CN1530288A (en) | 2003-03-12 | 2003-03-12 | Circular magnetic suspension flying device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1530288A (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102224071A (en) * | 2008-11-25 | 2011-10-19 | 空中客车操作有限公司 | A method of controlling the centre of gravity of an aircraft |
| CN102358424A (en) * | 2011-08-17 | 2012-02-22 | 梁锡球 | Flying saucer aircraft |
| CN102756625A (en) * | 2011-03-29 | 2012-10-31 | 郑鹏 | Slurry and flood current overhead-hoisting rescue method and amphibious medical ambulance |
| CN101765540B (en) * | 2007-04-18 | 2013-03-27 | 移动科学有限公司 | Annular airborne vehicle |
| CN103158880A (en) * | 2013-03-04 | 2013-06-19 | 陆建收 | Aerospace motor-driven helicopter |
| WO2014036818A1 (en) * | 2012-09-06 | 2014-03-13 | 力保企业有限公司 | Electrodynamic dish-shaped flying generator |
| CN106892106A (en) * | 2017-04-06 | 2017-06-27 | 重庆鸿动翼科技有限公司 | Electromagnetic Drive tandem wing aerodynamic vehicle |
| CN110037477A (en) * | 2019-05-08 | 2019-07-23 | 徐春凤 | A kind of intelligent rotating bed |
| CN110356553A (en) * | 2019-08-29 | 2019-10-22 | 吕福瑞 | A kind of wheel rotor aircraft |
| CN111477065A (en) * | 2020-04-08 | 2020-07-31 | 杭州幻行科技有限公司 | Dynamic simulator of acceleration based on magnetic suspension |
| CN112078830A (en) * | 2020-08-04 | 2020-12-15 | 北京空间技术研制试验中心 | Aircraft track control method and tail skirt |
-
2003
- 2003-03-12 CN CNA031194338A patent/CN1530288A/en active Pending
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101765540B (en) * | 2007-04-18 | 2013-03-27 | 移动科学有限公司 | Annular airborne vehicle |
| CN102224071B (en) * | 2008-11-25 | 2014-04-09 | 空中客车操作有限公司 | Method of controlling centre of gravity of aircraft |
| CN102224071A (en) * | 2008-11-25 | 2011-10-19 | 空中客车操作有限公司 | A method of controlling the centre of gravity of an aircraft |
| CN102756625B (en) * | 2011-03-29 | 2018-02-23 | 郑鹏 | Mud stream flies to hang the amphibious ambulance of rescue and its control method |
| CN102756625A (en) * | 2011-03-29 | 2012-10-31 | 郑鹏 | Slurry and flood current overhead-hoisting rescue method and amphibious medical ambulance |
| CN102358424A (en) * | 2011-08-17 | 2012-02-22 | 梁锡球 | Flying saucer aircraft |
| WO2014036818A1 (en) * | 2012-09-06 | 2014-03-13 | 力保企业有限公司 | Electrodynamic dish-shaped flying generator |
| CN103158880A (en) * | 2013-03-04 | 2013-06-19 | 陆建收 | Aerospace motor-driven helicopter |
| CN103158880B (en) * | 2013-03-04 | 2015-12-23 | 陆建收 | Empty sky electric helicopter |
| CN106892106A (en) * | 2017-04-06 | 2017-06-27 | 重庆鸿动翼科技有限公司 | Electromagnetic Drive tandem wing aerodynamic vehicle |
| CN110037477A (en) * | 2019-05-08 | 2019-07-23 | 徐春凤 | A kind of intelligent rotating bed |
| CN110037477B (en) * | 2019-05-08 | 2021-07-09 | 赣州市南康区福林木业有限公司 | Intelligent rotating bed |
| CN110356553A (en) * | 2019-08-29 | 2019-10-22 | 吕福瑞 | A kind of wheel rotor aircraft |
| CN110356553B (en) * | 2019-08-29 | 2023-06-20 | 吕福瑞 | Full rotor craft |
| CN111477065A (en) * | 2020-04-08 | 2020-07-31 | 杭州幻行科技有限公司 | Dynamic simulator of acceleration based on magnetic suspension |
| CN112078830A (en) * | 2020-08-04 | 2020-12-15 | 北京空间技术研制试验中心 | Aircraft track control method and tail skirt |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |