CN201419797Y - Flying saucer - Google Patents
Flying saucer Download PDFInfo
- Publication number
- CN201419797Y CN201419797Y CN2009200422046U CN200920042204U CN201419797Y CN 201419797 Y CN201419797 Y CN 201419797Y CN 2009200422046 U CN2009200422046 U CN 2009200422046U CN 200920042204 U CN200920042204 U CN 200920042204U CN 201419797 Y CN201419797 Y CN 201419797Y
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- CN
- China
- Prior art keywords
- magnetic pole
- suspension
- driven
- air
- inlet cavity
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- Expired - Fee Related
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Abstract
The utility model relates to a flying saucer, which comprises a driving force ring, a driven force ring, an air inlet cavity, a cavity cover, a loading bin, a direction adjusting mechanism and a generator, wherein the air inlet cavity is respectively provided with the driving force ring and the driven force ring which rotate in the opposite directions; an inner cavity of the air inlet cavity is provided with the loading bin; the cavity cover is arranged on the loading bin; the direction adjusting mechanism is arranged between the loading bin and the air inlet cavity; the generator is arrangedat the air outlet end of the air inlet cavity; the driving force ring and the driven force ring have an end face magnetic suspension structure; the driving force ring and the air inlet cavity have andend face and side magnetic suspension structure; and the driven force ring and the air inlet cavity have an end face and side magnetic suspension structure. As the contact surface of mutual movementis of the magnetic suspension structure, the overall operation is in frictionless state; as the air flow in rotating enters an interlayer between the air inlet cavity and the loading bin, the takeoffis fast, the power generation processing is carried out, and the energy is provided for the operation; and the direction adjusting mechanism is arranged and can conveniently adjust the flying direction.
Description
Technical field
The utility model relates to a kind of flight instruments, a kind of specifically disc aircraft.
Background technology
Relevant by retrieval patent documentation does not retrieve the disc aircraft identical with the utility model structure at present as yet.Existing disc aircraft kind is more, differ from one another, general rotating shaft interlock driven rotary by rotor that rotates and body, and because its friction drag is bigger, mechanicalness noise is big, so limited the lift-off speed of aircraft, makes its energy consumption bigger simultaneously, so be necessary aircraft is improved, to apply to space motion better.
Summary of the invention
The purpose of this utility model is that a kind of employing magnetic suspension structure will be provided, and can make full use of the rotational force that relative motion brings, and has the disc aircraft that rotational resistance is little, noise is little and can make full use of energy.
To achieve these goals, the utility model is by the following technical solutions:
Disc aircraft comprises the active force ring, from dynamic ring, air-inlet cavity, chamber lid, load storehouse, direction adjustment organization, electrical generator, on air-inlet cavity, be respectively equipped with in opposite directions the active force ring of rotation, from dynamic ring, in the inner chamber of air-inlet cavity, be provided with the load storehouse, on the load storehouse, be provided with the chamber lid, be provided with direction adjustment organization between load storehouse and air-inlet cavity, electrical generator is arranged on the outlet air end of air-inlet cavity; The main commentaries on classics hub of described active force ring is the end face magnetic suspension structure with the driven commentaries on classics hub from dynamic ring; The main commentaries on classics hub and the air-inlet cavity of described active force ring are end face and side direction magnetic suspension structure; Described driven commentaries on classics hub and air-inlet cavity from dynamic ring is end face and side direction magnetic suspension structure; The main ring of described active force ring encloses with enclosing from the driven torus of dynamic ring and is the end face magnetic suspension structure.
Described active force ring by primary blades, main change that hub, main ring enclose, main suspension magnetic pole I, main suspension magnetic pole II, main suspension side magnetic pole, main drive electrode, main ring enclose the suspension magnetic pole and form, primary blades is packed in main the commentaries on classics on the hub respectively, the end of blade of primary blades encloses with main ring and is connected, and is respectively equipped with array master suspend magnetic pole I, main suspension magnetic pole II, main suspension side magnetic pole, main drive electrode on the hub main the commentaries on classics; Main ring encloses the suspension magnetic pole and is arranged on main ring and places.
Described from dynamic ring by passive blade, driven commentaries on classics hub, driven torus enclose, driven suspension magnetic pole I, driven suspension magnetic pole II, driven suspension side magnetic pole, driven driving magnetic pole, driven torus enclose the suspension magnetic pole and form, passive blade is packed in respectively on the driven commentaries on classics hub, the end of blade of passive blade encloses with driven torus and is connected, and is respectively equipped with the driven suspension magnetic pole of array I, driven suspension magnetic pole II, driven suspension side magnetic pole, driven driving magnetic pole on driven commentaries on classics hub; Driven torus encloses the suspension magnetic pole and is arranged on driven torus and places.
Described air-inlet cavity is made up of cavity, air-inlet cavity suspension side magnetic pole, air-inlet cavity suspension end face magnetic pole I, air-inlet cavity suspension end face magnetic pole II, air-inlet cavity suspension side magnetic pole is arranged on the cavity, air-inlet cavity suspension end face magnetic pole I, air-inlet cavity suspension end face magnetic pole II are separately positioned on the two ends of cavity, be provided with several air intake vents on cavity, the end on cavity is provided with the end face that confluxes.
Described direction adjustment organization is at least four hydraulic mechanism devices.
Described electrical generator is an aerogenerator.
During work, start the power control mechanism that is provided with in the load storehouse, make the main drive electrode energising in the active force ring, and with driven driving magnetic pole mutual action from dynamic ring, this moment is main change the suspension magnetic pole that is provided with on the hub respectively with air-inlet cavity on the suspension magnetic pole, it is right that suspension magnetic pole effect from dynamic ring forms magnetic suspension, simultaneously the main ring of active force ring is placed the magnetic pole that is provided with to form magnetic suspension right with place the magnetic pole effect that is provided with from the driven torus of dynamic ring, under the effect of electric power, the active force ring with rotate in opposite directions from dynamic ring, under the effect of blade, make whole come-up, and reach air objective.The direction adjustment organization that is provided with between air-inlet cavity and the load storehouse its objective is that the angle in order to regulate between load storehouse and the air-inlet cavity is provided with, by regulating the height of direction adjustment organization, make load storehouse and air-inlet cavity form certain angle of inclination, thereby regulate the direction of travel of aircraft.
The utility model has the advantages that: because mutually the motion contact surface is a magnetic suspension structure, thereby make the single-piece operation be in no Frotteurism, make that resistance is little, energy consumption is low; Owing on air-inlet cavity, be provided with air intake vent, and the air-flow that forms in the rotation is entered in the interlayer between air-inlet cavity and the load storehouse, float thereby when taking off, promote the load storehouse, make and take off rapidly, air-flow with rotation compiles simultaneously, the processing of generating electricity, and operation provides energy to single-piece; Owing to be provided with direction adjustment organization, thereby can regulate the heading of aircraft easily; Enclose the suspension magnetic pole and enclose suspension magnetic pole mutual action because active force is equipped with main ring, make it carry out spacing operation, thereby operating vibrations and noise are little, stable, safety with driven torus from dynamic ring; Because simple and reasonable for structure, energy consumption is low, flying speed is fast, and direction to control is flexible, and stable and reliable operation has wide range of applications, so have very big practicality and exploitation to be worth.
Description of drawings
Below with reference to accompanying drawing the utility model is further described:
Accompanying drawing 1 is the structural representation of the utility model disc aircraft;
Accompanying drawing 2 is birds-eye vieies of accompanying drawing 1;
Accompanying drawing 3 is distribution graphs of main drive electrode of the active force ring of disc aircraft;
Accompanying drawing 4 is distribution graphs from the driven driving magnetic pole of dynamic ring of disc aircraft.
The specific embodiment
With reference to accompanying drawing 1, accompanying drawing 2, accompanying drawing 3, accompanying drawing 4, disc aircraft of the present utility model comprises active force ring 1, from dynamic ring 2, air-inlet cavity 3, chamber lid 4, load storehouse 5, direction adjustment organization 6, electrical generator 7, on air-inlet cavity 3, be respectively equipped with in opposite directions the active force ring 1 of rotation, from dynamic ring 2, in the inner chamber of air-inlet cavity 3, be provided with load storehouse 5, on load storehouse 5, be provided with chamber lid 4, between load storehouse 5 and air-inlet cavity 3, be provided with direction adjustment organization 6, direction adjustment organization 6 is at least four hydraulic mechanism devices, and present embodiment is four hydraulic mechanism devices; Electrical generator 7 is arranged on the outlet air end of air-inlet cavity 3, and described electrical generator 7 is an aerogenerator; Described active force ring 1 by primary blades 11, main change that hub 12, main ring enclose 13, main suspension magnetic pole I 14, main suspension magnetic pole II 15, main suspension side magnetic pole 16, main drive electrode 17, main ring enclose suspension magnetic pole 18 and form, primary blades 11 is packed in main the commentaries on classics on the hub 12 respectively, the end of blade of primary blades 11 encloses 13 with main ring and is connected, and is respectively equipped with array master suspend magnetic pole I 14, main suspension magnetic pole II 15, main suspension side magnetic pole 16, main drive electrode 17 on the hub 12 main the commentaries on classics; Main ring encloses suspension magnetic pole 18 and is arranged on main ring and encloses on 13; The main commentaries on classics hub 12 of described active force ring 1 is the end face magnetic suspension structure with the driven commentaries on classics hub 22 from dynamic ring 2; The main hub 12 that changes of active force ring 1 is end face and side direction magnetic suspension structure with air-inlet cavity 3, described air-inlet cavity 3 is by cavity 31, air-inlet cavity suspension side magnetic pole 32, air-inlet cavity suspension end face magnetic pole I 33, air-inlet cavity suspension end face magnetic pole II 34 forms, air-inlet cavity suspension side magnetic pole 32 is arranged on the cavity 31, on cavity 31, be provided with several air intake vents 31a, end on cavity 31 is provided with the end face 31b that confluxes, air-inlet cavity suspension side magnetic pole 32 is arranged on the cavity 31, air-inlet cavity suspension end face magnetic pole I 33, air-inlet cavity suspension end face magnetic pole II 34 is separately positioned on the two ends of cavity 31, be provided with several air intake vents 31a on cavity 31, the end on cavity 31 is provided with the end face 31b that confluxes; Is end face and side direction magnetic suspension structure from the driven commentaries on classics hub 22 of dynamic ring 2 with air-inlet cavity 3; The main ring of described active force ring 1 enclose 13 with enclose 23 from the driven torus of dynamic ring 2 and be the end face magnetic suspension structure; From dynamic ring 2 by passive blade 21, driven commentaries on classics hub 22, driven torus enclose 23, driven suspension magnetic pole I 24, driven suspension magnetic pole II 25, driven suspension side magnetic pole 26, driven driving magnetic pole 27, driven torus enclose suspension magnetic pole 28 and form, passive blade 21 is packed in respectively on the driven commentaries on classics hub 22, the end of blade of passive blade 21 encloses 23 with driven torus and is connected, and is respectively equipped with the driven suspension magnetic pole of array I 24, driven suspension magnetic pole II 25, driven suspension side magnetic pole 26, driven driving magnetic pole 27 on driven commentaries on classics hub 22; Driven torus encloses suspension magnetic pole 28 and is arranged on driven torus and encloses on 23.
Claims (6)
1. disc aircraft comprises active force ring (1), covers (4), load storehouse (5), direction adjustment organization (6), electrical generator (7) from dynamic ring (2), air-inlet cavity (3), chamber, it is characterized in that: on air-inlet cavity (3), be respectively equipped with in opposite directions the active force ring (1) of rotation, from dynamic ring (2), in the inner chamber of air-inlet cavity (3), be provided with load storehouse (5), on load storehouse (5), be provided with chamber lid (4), be provided with direction adjustment organization (6) between load storehouse (5) and air-inlet cavity (3), electrical generator (7) is arranged on the outlet air end of air-inlet cavity (3); The main commentaries on classics hub (12) of described active force ring (1) is the end face magnetic suspension structure with the driven commentaries on classics hub (22) from dynamic ring (2); The main hub (12) that changes of described active force ring (1) is end face and side direction magnetic suspension structure with air-inlet cavity (3); Described driven commentaries on classics hub (22) from dynamic ring (2) is end face and side direction magnetic suspension structure with air-inlet cavity (3); The main ring of described active force ring (1) encloses (13) and encloses (23) from the driven torus of dynamic ring (2) and be the end face magnetic suspension structure.
2. disc aircraft according to claim 1, it is characterized in that: described active force ring (1) is by primary blades (11), the main hub (12) that changes, main ring encloses (13), main suspension magnetic pole I (14), main suspension magnetic pole II (15), main suspension side magnetic pole (16), main drive electrode (17), main ring encloses suspension magnetic pole (18) and forms, primary blades (11) is packed in main the commentaries on classics on the hub (12) respectively, the end of blade of primary blades (11) encloses (13) and is connected with main ring, be respectively equipped with the array master magnetic pole I (14) that suspends on the hub (12) main the commentaries on classics, main suspension magnetic pole II (15), main suspension side magnetic pole (16), main drive electrode (17); Main ring encloses suspension magnetic pole (18) and is arranged on main ring and encloses on (13).
3. disc aircraft according to claim 1, it is characterized in that: described from dynamic ring (2) by passive blade (21), driven commentaries on classics hub (22), driven torus encloses (23), driven suspension magnetic pole I (24), driven suspension magnetic pole II (25), driven suspension side magnetic pole (26), driven driving magnetic pole (27), driven torus encloses suspension magnetic pole (28) and forms, passive blade (21) is packed in respectively on the driven commentaries on classics hub (22), the end of blade of passive blade (21) encloses (23) and is connected with driven torus, be respectively equipped with the driven suspension magnetic pole of array I (24) on driven commentaries on classics hub (22), driven suspension magnetic pole II (25), driven suspension side magnetic pole (26), driven driving magnetic pole (27); Driven torus encloses suspension magnetic pole (28) and is arranged on driven torus and encloses on (23).
4. disc aircraft according to claim 1, it is characterized in that: described air-inlet cavity (3) is made up of cavity (31), air-inlet cavity suspension side magnetic pole (32), air-inlet cavity suspension end face magnetic pole I (33), air-inlet cavity suspension end face magnetic pole II (34), air-inlet cavity suspension side magnetic pole (32) is arranged on the cavity (31), air-inlet cavity suspension end face magnetic pole I (33), air-inlet cavity suspension end face magnetic pole II (34) are separately positioned on the two ends of cavity (31), be provided with several air intake vents (31a) on cavity (31), the end on cavity (31) is provided with the end face that confluxes (31b).
5. disc aircraft according to claim 1 is characterized in that: described direction adjustment organization (6) is at least four hydraulic mechanism devices.
6. disc aircraft according to claim 1 is characterized in that: described electrical generator (7) is an aerogenerator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009200422046U CN201419797Y (en) | 2009-03-19 | 2009-03-19 | Flying saucer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009200422046U CN201419797Y (en) | 2009-03-19 | 2009-03-19 | Flying saucer |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201419797Y true CN201419797Y (en) | 2010-03-10 |
Family
ID=41806448
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009200422046U Expired - Fee Related CN201419797Y (en) | 2009-03-19 | 2009-03-19 | Flying saucer |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201419797Y (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101837832A (en) * | 2009-03-19 | 2010-09-22 | 蔡窿 | Saucer-like air vehicle |
| CN101612994B (en) * | 2009-07-24 | 2013-03-27 | 北京工业大学 | Magnetic suspension rotary wing type flying disk |
| CN103253371A (en) * | 2012-02-16 | 2013-08-21 | 王元知 | Flying saucer aircraft apparatus |
| CN103895859A (en) * | 2012-12-25 | 2014-07-02 | 徐珑洋 | Apparatus for acquiring air lift through idling |
| CN108163165A (en) * | 2017-12-23 | 2018-06-15 | 左立亮 | A kind of revolution diving apparatus |
| CN112319812A (en) * | 2019-08-05 | 2021-02-05 | 李越标 | Magnetic suspension disk-shaped aircraft |
-
2009
- 2009-03-19 CN CN2009200422046U patent/CN201419797Y/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101837832A (en) * | 2009-03-19 | 2010-09-22 | 蔡窿 | Saucer-like air vehicle |
| CN101612994B (en) * | 2009-07-24 | 2013-03-27 | 北京工业大学 | Magnetic suspension rotary wing type flying disk |
| CN103253371A (en) * | 2012-02-16 | 2013-08-21 | 王元知 | Flying saucer aircraft apparatus |
| CN103895859A (en) * | 2012-12-25 | 2014-07-02 | 徐珑洋 | Apparatus for acquiring air lift through idling |
| CN103895859B (en) * | 2012-12-25 | 2016-01-20 | 徐珑洋 | A kind of device being obtained air lift force by idle running |
| CN108163165A (en) * | 2017-12-23 | 2018-06-15 | 左立亮 | A kind of revolution diving apparatus |
| CN108163165B (en) * | 2017-12-23 | 2020-09-01 | 左立亮 | Rotary body diving equipment |
| CN112319812A (en) * | 2019-08-05 | 2021-02-05 | 李越标 | Magnetic suspension disk-shaped aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20100310 Termination date: 20140319 |