CN110356553A - A kind of wheel rotor aircraft - Google Patents
A kind of wheel rotor aircraft Download PDFInfo
- Publication number
- CN110356553A CN110356553A CN201910808572.5A CN201910808572A CN110356553A CN 110356553 A CN110356553 A CN 110356553A CN 201910808572 A CN201910808572 A CN 201910808572A CN 110356553 A CN110356553 A CN 110356553A
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- China
- Prior art keywords
- magnet
- rotor
- end surface
- stator department
- operative end
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C19/00—Aircraft control not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/10—All-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
Abstract
The invention discloses a kind of wheel rotor aircrafts, belong to aircraft field, and the present invention includes: fuselage, and the fuselage includes: lower body, have operative end surface on the lower body；Stator department, the stator department are fixed in the operative end surface, and the axis of the stator department has the first magnet perpendicular to the operative end surface on the stator department；Rotor portions, the rotor portions are sheathed on the stator department, have the second magnet in the rotor portions, and have counterface in the rotor portions, and there are gaps between the counterface and the operative end surface；And rotor, the rotor are set in the rotor portions；Wherein, first magnet and second magnet repel each other arrangement, and form a toroidal cavity between first magnet and second magnet.The aircraft is separated the airfoil portion of rotation and shaft by magnetic suspension mode, to reduce flight energy consumption and abrasion.
Description
Technical field
The invention belongs to aircraft fields, and in particular to arrive a kind of wheel rotor aircraft.
Background technique
Include a kind of special aircraft, i.e. disc aircraft in aircraft field.
Existing disc aircraft includes firm banking, is formed with an annular groove on the fixed base, dish-shaped shell it is interior
Ring set enters in the annular groove, while traditional mechanical structure being provided with rotor on dish-shaped shell, passes through the height of rotor
Speed rotation drives disc-shaped flying craft integrally to fly after generating climbing power, but traditional mechanical structure is rubbed there are biggish
It wipes, so that a large amount of energy consumption can be not only lost in rotor system in high speed rotation, can also wear, shorten the service life.
Summary of the invention
In order to solve the above problems existing in the present technology, embodiments herein provides a kind of wheel rotor aircraft, should
Aircraft is separated the airfoil portion of rotation and shaft by magnetic suspension mode, to reduce flight energy consumption and abrasion.
In order to achieve the above object, technical solution used by embodiments herein is as follows:
In a first aspect, embodiments herein provides a kind of wheel rotor aircraft, comprising:
Fuselage, the fuselage include:
Lower body has operative end surface on the lower body；
Stator department, the stator department are fixed in the operative end surface, and the axis of the stator department is perpendicular to described
Operative end surface has the first magnet on the stator department；
Rotor portions, the rotor portions are sheathed on the stator department, have the second magnet, and described turn in the rotor portions
There is counterface, there are gaps between the counterface and the operative end surface in sub-portion；
And
Rotor, the rotor are set in the rotor portions；
Wherein, first magnet and second magnet repel each other arrangement, and first magnet and second magnet
Between form a toroidal cavity.
Optionally, first magnet is set as the ringshaped magnet that longitudinal section is c-type.
Optionally, first magnet is set as permanent magnet.
Optionally, second magnet is set as the ringshaped magnet that longitudinal section is c-type.
Optionally, second magnet is set as electromagnet.
It optionally, further include auxiliary accelerator, the auxiliary accelerator includes；
Ring shaped conductive slot, the ring shaped conductive slot are opened in the operative end surface, and the axis of the ring shaped conductive slot
With the axis collinear of the stator department；
Conduction acceleration ring, the conductive acceleration ring set are set in the ring shaped conductive slot, and the conductive acceleration ring has
Fixing end, the fixed end part protrude the ring shaped conductive slot, and the conductive acceleration ring passes through the fixing end and described turn
Sub-portion connection.
It optionally, further include rubber shock-absorbing protective layer, the rubber shock-absorbing protective layer is set in the operative end surface.
It optionally, further include magnetic energy levitation device, the magnetic energy levitation device includes:
Third magnet, the third magnet are fixed on the counterface；
4th magnet, the 4th magnet are fixed in the operative end surface；
Wherein, the third magnet and the 4th magnet repel each other arrangement.
Optionally, the third magnet is set as annular permanent magnet.
Optionally, the 4th magnet is set as ring electromagnet.
Compared with prior art, the upper fuselage where the rotor for the aircraft that embodiments herein provides, i.e. rotor portions
Be suspended on the operative end surface of lower body by magnetic suspension and rotor portions by magnetic suspension to be suspended in stator department diameter outside
Side, so that the upper fuselage of rotor portions and rotor composition is not with the shaft of high-speed rotation, i.e. stator department contact rubs, also not under
Body contact friction, to reduce energy loss, also avoids being rubbed when rotating at high speed to the negative of fuselage service life
It influences.
Referring to following description and accompanying drawings, only certain exemplary embodiments of this invention is disclosed in detail, specifies original of the invention
Reason can be in a manner of adopted.It should be understood that embodiments of the present invention are not so limited in range.In appended power
In the range of the spirit and terms that benefit requires, embodiments of the present invention include many changes, modifications and are equal.
The feature for describing and/or showing for a kind of embodiment can be in a manner of same or similar one or more
It uses in a other embodiment, is combined with the feature in other embodiment, or the feature in substitution other embodiment.
It should be emphasized that term "comprises/comprising" refers to the presence of feature, one integral piece, step or component when using herein, but simultaneously
It is not excluded for the presence or additional of one or more other features, one integral piece, step or component.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
Some embodiments of invention for those skilled in the art without any creative labor, can be with root
Other attached drawings are obtained according to these attached drawings.
Fig. 1 is the structural schematic diagram of one embodiment of the application.
In figure: the first magnet of 1-, the second magnet of 2-, 3- stator department, 4.1- third magnet, the 4th magnet of 4.2-, 5- are conductive
Accelerate ring, 6- lower body, 7- ring shaped conductive slot, 8- rubber shock-absorbing protective layer, 9- rotor portions, 10- rotor.
Specific embodiment
Technical solution in order to enable those skilled in the art to better understand the present invention, below in conjunction with of the invention real
The attached drawing in example is applied, technical scheme in the embodiment of the invention is clearly and completely described, it is clear that described implementation
Example is only a part of the embodiment of the present invention, instead of all the embodiments.Based on the embodiments of the present invention, this field is common
Technical staff's every other embodiment obtained without making creative work, all should belong to guarantor of the present invention
The range of shield.
It should be noted that it can directly on the other element when element is referred to as " being set to " another element
Or there may also be elements placed in the middle.When an element is considered as " connection " another element, it, which can be, is directly connected to
To another element or it may be simultaneously present centering elements.Term as used herein " vertical ", " horizontal ", " left side ",
" right side " and similar statement for illustrative purposes only, are not meant to be the only embodiment.
Unless otherwise defined, all technical and scientific terms used herein and belong to technical field of the invention
The normally understood meaning of technical staff is identical.Term as used herein in the specification of the present invention is intended merely to description tool
The purpose of the embodiment of body, it is not intended that in the limitation present invention.Term as used herein "and/or" includes one or more
Any and all combinations of relevant listed item.
In an exemplary embodiment, a kind of 10 aircraft of the wheel wing, comprising:
Fuselage, the fuselage include: lower body 6, have operative end surface on the lower body 6；Stator department 3, the stator
Portion 3 is fixed in the operative end surface, and the axis of the stator department 3 is perpendicular to the operative end surface, on the stator department 3
With the first magnet 1.
Specifically, fuselage is one using shell made of light metal material such as aluminium alloy or engineering plastic materials.In machine
The subsystem of the interconnections such as power supply device, transmitting device cooperation is installed inside body.Power supply device can be selected as high-energy electricity
Source, concretely the lithium-ions battery accumulation power supply of spacecraft.
Landing gear is installed in fuselage bottom, existing Sledge type, bikini or four-point landing can be selected in landing gear
Frame.Specifically, using ultra lightweighting landing gear.
Optionally, fuselage construction is dish or bowl-type.The top end face of such dish or bowl-type fuselage is described
Operative end surface.The operative end surface can be configured to a horizontal plane.Stator above-mentioned is configured at the longitudinal axis of the operative end surface
Portion 3.
Optionally, when aircraft provided in this embodiment is manned vehicle, the top of stator department 3 is provided with arc and drives
Sail cabin.
Specifically, stator department 3 is by riveting, welding, perhaps other equivalent ways are fixed on fuselage or stator department 3 is straight
It connected riveting or other equivalent ways is fixed on the keel bar of fuselage, the two is combined closely, to improve fuselage and stator
The structural strength in portion 3.
Stator department 3 is a cylindrical body extended along the normal direction of operative end surface.Magnetic levitation system is disposed on the cylindrical body
In stator, i.e. the first magnet 1.
It is arranged with rotor portions 9 on the stator department 3, there are the second magnet 2, and the rotor portions 9 in the rotor portions 9
Upper to have counterface, there are gaps between the counterface and the operative end surface.
And rotor 10, the rotor 10 are set in the rotor portions 9.
Wherein, first magnet 1 and second magnet 2 repel each other arrangement, and first magnet 1 and second magnetic
A toroidal cavity is formed between body 2.
Specifically, being configured with a through-hole on the central axes of rotor portions 9, rotor portions 9 are set in stator department 3 by the through-hole
On.Rotor 10 is arranged in rotor portions 9, is optionally integrally formed for rotor 10 and rotor portions 9, that is, the dish being buckled to, common structure
Upper fuselage or upper limb part at disc-shaped flying craft.Upper fuselage and lower body 6, which are combined together, just together constitutes dish-shaped fly
Row device.
The rotor being also accordingly disposed in rotor portions 9 in magnetic levitation system, i.e. the second magnet 2.First magnet 1 and the second magnetic
Body 2 repels each other arrangement.It is arranged to realize that 9 relative stator portion 3 of rotor portions suspends, the two does not contact.And rotor portions 9 and rotor 10 around
The high speed rotation of stator department 3 will drive aircraft integrally to fly.
Optionally, rotor portions 9 and rotor 10 can also use light metal material such as aluminium alloy or engineering plastic materials for one
Manufactured shell.To the liter generated by the pressure difference of the upper surface and lower aerofoil that are generated after the rotation of rotor portions 9 and rotor 10
Aircraft is integrally lifted away from ground by power, achievees the purpose that flight.
In some embodiments, rotor 10 is it is so structured that circumferential uniform or right on the radial outside wall of rotor portions 9
Claim at least two panels blade of arrangement.
In some embodiments, first magnet 1 is set as the ringshaped magnet that longitudinal section is c-type.It is corresponding, described
Two magnets 2 are set as the ringshaped magnet that longitudinal section is c-type.
Wherein, first magnet 1 is set as permanent magnet.Second magnet 2 is set as electromagnet.
Specifically, the first magnet 1 is c-type annular permanent magnet, it is set in by card slot or the fixation of other equivalent ways
On the radial outside wall of stator department 3, and the second magnet 2 is C-shaped ring shape electromagnet, solid by card slot or other equivalent ways
Surely it is set on the through-hole of rotor portions 9.
First magnet 1 and the second magnet 2 are made of several array of magnetic dipoles.The first magnet 1 is shown with reference to Fig. 1, Fig. 1
The relative position after installation with the second magnet 2.The internal diameter of second magnet 2 is greater than the outer diameter of the first magnet 1, thus the second magnet
2 are coated on the first magnet 1 inside of second magnet 2, form a toroidal cavity between the two.So as to pass through the second magnet
2 and the first magnetic force adjustment the first magnet 1 and the second magnet 2 between magnet 1 radial and axial position, i.e. 1 He of the first magnet
The relative position of second magnet 2, so as to adjust rotor portions 9, the especially inclined direction of rotor 10, to realize that control flies
The moving direction of row device.Specifically, the first magnet 1 and the second magnet 2 are on horizontal plane, and the first magnet 1 in hovering
It is coplanar with the plane of symmetry in the horizontal direction of the second magnet 2.When needing to adjust the heading of aircraft, pass through control second
Size of current on magnet 2, to realize the relative position of the second magnet 2 and the first magnet 1, i.e., the raw water of the second magnet 2 is flat
The plane of symmetry on direction and the plane of symmetry on the horizontal plane of the first magnet 1 are become intersecting from coplanar, the adjustment of the angle of the intersection
It is presented as the variation of the variation of the relative position of the first magnet 1 and the first magnet 1 namely the heading of aircraft.
Since the skyborne flight environment of vehicle of aircraft is more complicated and changeable, in order to enable aircraft meets bad working environments
Under flight, further include auxiliary accelerator on aircraft provided in this embodiment, the auxiliary accelerator includes:
Ring shaped conductive slot 7, the ring shaped conductive slot 7 are opened in the operative end surface, and 7 slot of ring shaped conductive slot
The axis collinear of axis and the stator department 3.
Conduction accelerates ring 5, and the conductive acceleration ring 5 is sheathed in the ring shaped conductive slot 7, and the conduction accelerates ring 5
With fixing end, the fixed end part protrudes the ring shaped conductive slot 7, it is described it is conductive accelerate ring 5 by the fixing end and
The rotor portions 9 connect.
Specifically, offering an annular groove in operative end surface, layer of conductive material is equipped on the side wall of the annular groove.
Alternatively, being arranged with the conductive shell that one layer of longitudinal section is horizontal c-type in the annular groove opened up in operative end surface
Body is configured with the annular compartment of a upper end opening in the conductive shell.
In this way, forming an electromagnetic field in the annular groove after being powered.
Correspondingly, it is conductive accelerate ring 5 to be powered after in the magnetic field by Ampere force under the action of rise.And conducting ring due to
It is fixed in rotor portions 9 by fixing end, so that rotor portions 9 be forced to rise, and rotor portions 9, rotor 10 is made to rotate more
Fastly, thus the skyborne horizontal velocity of more precise control aircraft and vertical speed.
Specifically, fixing end can be a ring-type element, the upper surface of the ring-type element by riveting or welding or
Other equivalent ways are fixed on counterface.And the lower end surface of the ring-type element is configured to a groove, fixing end is recessed by this
Slot accelerates ring 5 to be fixedly connected with conduction, and the mode of being fixedly connected can be welding, bonding or other equivalent ways.
Optionally, fixing end can be accelerates to upwardly extend several to be formed protrusion on ring 5 conductive so that structure by
Power is more stable, and convex block is evenly arranged.
Optionally, above-mentioned conductive acceleration ring 5 can be made of metal material or other conductive materials.
In some embodiments, the rubber shock-absorbing protective layer 8 is additionally provided in the operative end surface.The rubber shock-absorbing
Protective layer 8 is specifically chosen as circle, and a hole passed through for stator department 3 is offered on the longitudinal axis of the rubber shock-absorbing protective layer 8.
Then the rubber shock-absorbing protective layer 8 is fixed in operative end surface by bonding or riveting or other equivalent ways.
In some embodiments, the rubber shock-absorbing protective layer 8 may be configured to the rounded array in operative end surface
Several pieces of fan-shaped small rubber shock-absorbing protecting layers, the axis collinear of the array axis of the circular array and stator department 3.
In some embodiments, the rubber shock-absorbing protective layer 8 may be configured in operative end surface with stator department 3
Axis is the several layers annular small rubber shock-absorbing protecting layer that the center of circle arranges from inside to outside.
The power that gap and rotor portions 9 between operative end surface and counterface rotate can be suspended by magnetic energy and be filled
Realization is set, the magnetic energy levitation device includes:
Third magnet 4.1, the third magnet 4.1 are fixed on the counterface.
And the 4th magnet 4.2, the 4th magnet 4.2 are fixed in the operative end surface.Wherein, the third magnetic
Iron and the 4th magnet 4.2 repel each other arrangement.
Specifically, the power supply device of fuselage interior starts, third magnet 4.1 forms phase with the 4th magnet 4.2 after powered up
The magnetic field of reprimand, so that rotor portions 9, rotor 10 rise, and opposite fuselage suspends.At this point, the first magnet 1 is also with respect to the second magnet 2
It suspending, i.e., rotor portions 9 and rotor 10 do not contact with stator department 3 and fuselage, thus reduce friction bring energy loss,
Avoid the negative effect to be rubbed when rotating at high speed to service life.
In some embodiments, in order to enable rotor portions 9 and rotor 10 are more regular with respect to the posture of fuselage, control response
Faster, accurately, the third magnet 4.1 is set as annular permanent magnet.Correspondingly, the 4th magnet 4.2 setting may also set up
For ring electromagnet.
The flying speed of aircraft flight depends on the velocity of rotation of rotor portions 9, rotor 10 relative to fuselage, and rotor portions
9, the propulsive force that rotor 10 rotates is controlled by the size of current of ring electromagnet.
First magnet 1, the second magnet 2, third magnet 4.1 and the 4th magnet 4.2 above-mentioned can by superconductor or
The other conventional superconductor production of person.
In a specific embodiment.Working principle is as follows:
Lower body 6 is stopped on the ground by landing gear, and then the power supply device starting in lower body 6, is the second magnet
2, the 4th magnet 4.2 is powered, the magnetic field that the second magnet 2 and the 4th magnet 4.2 generate after being powered and corresponding first magnet 1, the
The magnetic field of three magnets 4.1 is repelled each other, so that rotor 10, rotor portions 9 are lifted suspension from rubber shock-absorbing protective layer 8.And third magnet
4.1, the magnetic field of the 4th magnet 4.2 starts turning rotor portions 9, rotor 10, when the lift that rotor 10, rotor portions 9 generate
Greater than aircraft itself gravity when, aircraft starts to go up to the air.
When in the sky, in order to adjust the heading of aircraft, the size of current in the second magnet 2 can control, thus
So that the relative position of the second magnet 2 and the first magnet 1 changes, i.e. 2 opposite working ends face of the second magnet offset, to control
The heading of aircraft processed.
When encountering complicated flight progress in the sky, for example atmospheric density becomes smaller, and in order to increase lift, starting auxiliary accelerates dress
It sets, i.e., it is conductive to accelerate ring and ring shaped conductive slot, rotor portions 9 are increased by the conductive Ampere force accelerated between ring and ring shaped conductive slot
The velocity of rotation in gap and rotor portions 9 between lower fuselage 6.
All articles and reference disclosed, including patent application and publication, for various purposes by quoting knot
Together in this.Describing combined term " substantially by ... constitute " should include identified element, ingredient, component or step and reality
Other elements, ingredient, component or the step of the basic novel feature of the combination are not influenced in matter.Using term "comprising" or
" comprising " describes the combination of element here, ingredient, component or step it is also contemplated that substantially by these elements, ingredient, component
Or the embodiment that step is constituted.Here by using term " can with ", it is intended to illustrate that " can with " includes described any
Attribute is all optional.
Multiple element, ingredient, component or step can be provided by single integrated component, ingredient, component or step.Optionally
Ground, single integrated component, ingredient, component or step can be divided into multiple element, ingredient, component or the step of separation.It is used to
The open "a" or "an" for describing element, ingredient, component or step is not said to exclude other elements, ingredient, component
Or step.
It should be understood that above description is to illustrate rather than to be limited.By reading above-mentioned retouch
It states, many embodiments and many applications except provided example all will be aobvious and easy for a person skilled in the art
See.Therefore, the range of this introduction should not be determined referring to foregoing description, but should referring to appended claims and this
The full scope of the equivalent that a little claims are possessed determines.For comprehensive purpose, all articles and with reference to including special
The disclosure of benefit application and bulletin is all by reference to being incorporated herein.Theme disclosed herein is omitted in preceding claims
Any aspect is not intended to abandon the body matter, also should not be considered as inventor the theme is not thought of as it is disclosed
A part of subject matter.
Claims (10)
1. a kind of wheel rotor aircraft characterized by comprising
Fuselage, the fuselage include:
Lower body has operative end surface on the lower body；
Stator department, the stator department are fixed in the operative end surface, and the axis of the stator department is perpendicular to the work
End face has the first magnet on the stator department；Rotor portions, the rotor portions are sheathed on the stator department, the rotor portions
It is upper that there is the second magnet, and there is counterface in the rotor portions, exist between the counterface and the operative end surface
Gap；And
Rotor, the rotor are set in the rotor portions；Wherein, first magnet and second magnet repel each other arrangement,
And a toroidal cavity is formed between first magnet and second magnet.
2. a kind of wheel rotor aircraft according to claim 1, and it is characterized by: first magnet is set as vertical section
Face is the ringshaped magnet of c-type.
3. a kind of wheel rotor aircraft according to claim 1 or 2, it is characterised in that: first magnet is set as forever
Magnet.
4. a kind of wheel rotor aircraft according to claim 2, it is characterised in that: second magnet is set as longitudinal section
For the ringshaped magnet of c-type.
5. a kind of wheel rotor aircraft according to claim 4, it is characterised in that: second magnet is set as electromagnetism
Iron.
6. a kind of wheel rotor aircraft according to claim 1, it is characterised in that: it further include auxiliary accelerator, it is described
Auxiliary accelerator include:
Ring shaped conductive slot, the ring shaped conductive slot are opened in the operative end surface, and the axis of the ring shaped conductive slot and institute
State the axis collinear of stator department；
Conduction acceleration ring, the conductive acceleration ring set are set in the ring shaped conductive slot, and the conductive acceleration ring has fixation
End, the fixed end part protrude the ring shaped conductive slot, and the conductive acceleration ring passes through the fixing end and the rotor portions
Connection.
7. a kind of wheel rotor aircraft according to claim 1, it is characterised in that: further include rubber shock-absorbing protective layer, institute
Rubber shock-absorbing protective layer is stated in the operative end surface.
8. a kind of wheel rotor aircraft according to claim 1, it is characterised in that: it further include magnetic energy levitation device, it is described
Magnetic energy levitation device includes:
Third magnet, the third magnet are fixed on the counterface；
4th magnet, the 4th magnet are fixed in the operative end surface；
Wherein, the third magnet and the 4th magnet repel each other arrangement.
9. a kind of wheel rotor aircraft according to claim 8, it is characterised in that: the third magnet is set as annular forever
Magnet.
10. a kind of wheel rotor aircraft according to claim 9, it is characterised in that: the 4th magnet is set as annular
Electromagnet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910808572.5A CN110356553B (en) | 2019-08-29 | 2019-08-29 | Full rotor craft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910808572.5A CN110356553B (en) | 2019-08-29 | 2019-08-29 | Full rotor craft |
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| CN110356553A true CN110356553A (en) | 2019-10-22 |
| CN110356553B CN110356553B (en) | 2023-06-20 |
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| 王雪: "基于双旋翼和磁悬浮的远程实验室的建设", 《自动化与仪器仪表》 * |
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