CN108945404A - A kind of magnetic suspension rotor structure and the aircraft with it - Google Patents
A kind of magnetic suspension rotor structure and the aircraft with it Download PDFInfo
- Publication number
- CN108945404A CN108945404A CN201810677921.XA CN201810677921A CN108945404A CN 108945404 A CN108945404 A CN 108945404A CN 201810677921 A CN201810677921 A CN 201810677921A CN 108945404 A CN108945404 A CN 108945404A
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- Prior art keywords
- rotor
- stator
- support
- electromagnet
- gap
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/001—Vibration damping devices
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/001—Vibration damping devices
- B64C2027/005—Vibration damping devices using suspended masses
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Magnetic Bearings And Hydrostatic Bearings (AREA)
Abstract
The present invention relates to a kind of magnetic suspension rotor structures, it belongs to Aircraft structural design technical field, the magnetic suspension rotor structure includes rotor, rotor stator, rotor rotor, rotation drive module, axial supporting module, by the electromagnetic excitation stator and electromagnetic excitation rotor to drive the rotor rotational；By the support component supported with rotor rotor contact and permanent magnet array and reaction rail with the contactless support of rotor rotor, it is supported respectively under rotor low speed and fast state, completes the support of rotor.Magnetic suspension rotor structure of the invention contactless, the high-revolving advantage using magnetic levitation technology solves the problems, such as that large scale rotor can not be supported using mechanical bearing on the outside, and can effectively reduce the vibration noise of aircraft and improve its Stealth Fighter.
Description
Technical Field
The invention relates to the technical field of aircraft structure design, in particular to a magnetic suspension rotor wing structure.
Background
When the rotor wing of the unmanned aerial vehicle adopts outer edge support, if the rotor wing is required to be large in size and high in rotating speed, the conventional mechanical bearing cannot meet the requirement; if the rotor adopts the central axis support, this is similar with traditional unmanned aerial vehicle structure, and advantage in stealthy, aerodynamics does not play. Therefore, the magnetic suspension technology is applied to the support of the rotor wing of the unmanned aerial vehicle, and the advantages of non-contact and high rotating speed of the magnetic suspension technology can be fully exerted; the disc type permanent magnet brushless direct current motor is small in size, light in weight and high in efficiency, and the structure of the rotor wing is more compact. The combination of the two can not only improve the rotating speed of the rotor ring, but also play an important role in reducing the vibration noise of the rotor ring and improving the stealth performance of the rotor ring.
Disclosure of Invention
The invention aims to design a magnetic suspension rotor wing structure, which is used for solving or relieving the defects of the rotor wing structure in the prior art so as to improve the aerodynamic force of the rotor wing structure and reduce vibration.
In order to solve the problems, the technical scheme of the invention is as follows: a magnetic suspension rotor wing structure comprises a rotor wing, a rotor wing stator, a rotor wing rotor, a rotation driving module and an axial supporting module; wherein,
the rotor stator comprises an upper rotor stator and a lower rotor stator which are oppositely arranged so as to form an accommodating part for placing the rotor;
the rotary driving module comprises an electromagnetic excitation stator and an electromagnetic excitation rotor, the electromagnetic excitation stator is fixedly arranged on the upper rotor stator or the lower rotor stator, the electromagnetic excitation rotor is fixed on the rotor, and the rotor is driven to rotate by the electromagnetic excitation stator and the electromagnetic excitation rotor;
the rotor wing rotor is fixedly arranged on the electromagnetic excitation rotor along the radial direction of the rotor wing;
the axial supports the module and includes the permanent magnetism array that supports with rotor non-contact and responds to the rail and support assembly who supports with rotor contact, respond to the rail set up in rotor is last, just the permanent magnetism array set up in go up the rotor stator and down on the rotor stator, support assembly set up respectively in go up the rotor stator and down the rotor stator supports with the contact rotor.
Advantageously, the rotor comprises a rotor stator and a rotor stator, and the rotor stator is provided with a rotor end and a rotor stator end, and the rotor stator end is provided with a rotor stator and a rotor stator end, and the rotor stator.
Advantageously, the radial support module further comprises a displacement sensor arranged on the electromagnet at a position opposite to the armature ring along the radial direction of the rotor.
Advantageously, the electro-magnet includes along the radial first electro-magnet that sets up of rotor and along rotor axial setting's second electro-magnet and third electro-magnet, first electro-magnet, second electro-magnet and third electro-magnet all install in the rotor stator.
Advantageously, gaps are provided between the armature ring and the displacement sensor and between the armature ring and the electromagnet, and the gap between the armature ring and the displacement sensor is smaller than the gap between the armature ring and the electromagnet.
Advantageously, the radial support modules are a plurality of and are uniformly distributed along the axial direction of the rotor.
Advantageously, the support assembly comprises a support ball for supporting the rotor and a cage for limiting the radial movement of the support ball along the rotor, the cage being fixed to the stator of the rotor.
Advantageously, there is a gap a between the support ball and the rotor, and the induction rail and the permanent magnet array also have a gap B, and the gap B between the induction rail and the permanent magnet array is greater than the gap a between the support ball and the rotor.
Advantageously, the sensing area a of the permanent magnet array relative to the sensing rail is smaller than the sensing area B of the sensing rail relative to the permanent magnet array, and the sensing area a of the permanent magnet array is projected within the profile of the sensing area B of the sensing rail.
The invention also provides an aircraft comprising a magnetically levitated rotor structure according to any of claims to 9 for providing aerodynamic forces to the aircraft.
Compared with the prior art, the magnetic suspension one-out structure has the following advantages:
1) the invention solves the problem that the existing aircraft rotor wing supporting structure can not be suitable for the conditions of large size and high rotating speed, and the invention utilizes the advantages of non-contact and high rotating speed of the magnetic suspension technology to solve the problem that the mechanical bearing can not be used for supporting outside and reduce the vibration noise when the rotor wing rotates;
2) the rotary driving module adopts electromagnetic driving, has the characteristics of small volume, light weight and high efficiency, and enables the magnetic suspension rotor wing to have compact structure and improve the stealth performance of the magnetic suspension rotor wing.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the invention and together with the description, serve to explain the principles of the invention.
Fig. 1 is a schematic view of a magnetic levitation rotor of the present invention;
FIG. 2 is a schematic view of the internal structure of the magnetic levitation rotor of the present invention;
FIG. 3 is an enlarged view of a portion of the support assembly of FIG. 2;
FIG. 4 is a top view of the non-contact supporting permanent magnet array and the induction rail in the axial support module;
FIG. 5 is a top view of a radial support module;
reference numerals:
10-a rotor;
20-rotor stator, 21-upper rotor stator, 22-lower rotor stator;
30-a rotor of a rotor;
40-a rotation driving module, 41-an electromagnetic excitation stator and 42-an electromagnetic excitation rotor;
50-axial support module, 51-permanent magnet array, 52-induction rail, 53-support component, 531-support ball and 532-retainer;
60-radial support module, 61-electromagnet, 61 a-first electromagnet, 61 b-second electromagnet, 61 c-third electromagnet, 62-armature ring, 63-displacement sensor.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention.
As shown in fig. 1 to 5, the magnetic levitation rotor structure of the present invention includes a rotor 10, a rotor stator 20, a rotor 30, a rotation driving module 40, and an axial support module 50.
The rotor 10 is intended to serve the dual purpose of generating lift and/or drag during flight of the aircraft.
The rotor stator 20 includes an upper rotor stator 21 and a lower rotor stator 22, the upper rotor stator 21 and the lower rotor stator 22 are oppositely disposed to form a receiving portion 23, and the receiving portion 23 can receive the rotor 30 and other accessories.
The rotary drive module 40 includes an electromagnetically excited stator 41 and an electromagnetically excited rotor 42, and the electromagnetically excited stator 41 is mounted and fixed to the upper rotor stator 21 or the lower rotor stator 22, or both. The electromagnetically excited rotor 42 is fixed to the rotor 10, and the rotor 10 is rotated by excitation electromagnetism generated by the electromagnetically excited stator 41 and the electromagnetically excited rotor 42.
In the present invention, the rotation driving module 40 employs a disk-type permanent magnet brushless motor, which has excellent performance and a short axial dimension, and is very suitable for applications in robots, electric bicycles, small aircraft, and the like.
The rotor 30 is fixed relative to the rotor 10 by an electromagnetically excited rotor 42 fixed along the radial line L2 of the rotor 10.
In the example shown in fig. 2, the electromagnetically excited rotor 42 is fixed to the end of the rotor 10, but the rotary drive module 40 is used to drive the rotor 10 to rotate, and therefore, the electromagnetically excited rotor 42 may be mounted on the upper and lower end surfaces of the rotor 10 in addition to the mounting method shown in the drawing, when the above-described function is realized. On the basis of this, the rotor 30 can be fixed directly opposite the rotor 10, without the need for switching the electromagnetically excited rotor 42.
The axial support module 50 includes an induction rail 51, a permanent magnet array 52 and a support component 53, wherein the induction rail 51 and the permanent magnet array 52 are configured to support the rotor 30 in a non-contact manner, the induction rail 51 is embedded into the upper and lower surfaces of the rotor 30, the permanent magnet array 52 and the induction rail 51 are oppositely disposed in the upper rotor stator 21 and the lower rotor stator 22, and the rotor 30 is suspended in the accommodating portion 23 under the action of the induction rail 51 and the permanent magnet array 52. Support assembly 53 is disposed on rotor 20 for contacting the rotor.
In order to suspend the rotor 30 in the accommodating portion 23 stably, in the present invention, two sets of the induction rails 51 and the permanent magnet arrays 52 are respectively disposed on two sides of the rotor 30, so that the non-contact support assemblies on the two sides support the rotor 30 in a non-contact manner.
Similarly, two sets of support members 53 are disposed on either side of rotor 30 to provide support.
In an embodiment of the present invention, the support assembly 53 includes a support ball 531 for supporting the rotor 30 in a contact manner and a retainer 532 for limiting the movement of the support ball 531, and the retainer 532 is fixedly mounted on the rotor stator 20.
In another embodiment of the present invention, the support assembly 53 includes a support cylinder for contact-supporting the rotor 30 and a cage 532 for restricting the movement of the holding support ball 531, and the cage 532 is fixedly mounted on the rotor stator 20.
While non-contact support assembly 53 is used to support rotor 30, the difference is that support assembly 53 is used to support rotor 30 at rest and at low speeds, and non-contact support assembly is used to levitatively support rotor 30 during high speed rotation of rotor 30.
For the support in both states, there is a gap a between the support ball 531 and the rotor 30, and the gap B between the induction rail 51 and the permanent magnet array 52 is larger than the gap a. This is so that in the initial stage, rotor 30 is supported by support assembly 53, and when rotated, the non-contact support assembly begins to stably support rotor 30, eventually suspending rotor 30 within receptacle 23.
In the present invention, the gap B is not more than 1.5 mm.
In the present invention, the permanent magnet array 52 is a Halbach array that can produce the strongest magnetic field with the least amount of magnets.
In the present invention, both the rotor stator 20 and the rotor 30 are made of lightweight materials.
In addition, in the present invention, the sensing area a of the permanent magnet array 52 facing the sensing rail 51 is smaller than the sensing area B of the sensing rail 51 facing the permanent magnet array 52, and the sensing area a of the permanent magnet array 52 is projected within the contour of the sensing area B of the sensing rail.
The magnetic suspension rotor structure of the invention further comprises a radial support module 60, wherein the radial support module 60 comprises an electromagnet 61 and an armature ring 62, the armature ring 62 is arranged along the radial direction of the rotor 10 and is positioned at the end part of the rotor 30, and the electromagnet 61 and the armature ring 62 are arranged on the rotor stator 20 opposite to each other.
In an embodiment of the present invention, armature ring 62 may be secured to rotor 30 by adhesive, threaded connection, or interference fit.
The radial support module 60 further comprises a displacement sensor 63, the displacement sensor 63 being arranged on the electromagnet 61 at a position opposite to the armature ring 62 in the radial direction of the rotor 10.
The electromagnets 61 include a first electromagnet 61a disposed along the radial direction of the rotor 10, and a second electromagnet 61b and a third electromagnet 61c disposed along the axial direction of the rotor 10, and the first electromagnet 61a, the second electromagnet 61b, and the third electromagnet 61c are all mounted on the rotor stator 20.
Gaps are formed between the armature ring 62 and the displacement sensor 63 and between the electromagnet 61, and the gap between the armature ring 62 and the displacement sensor 63 is smaller than the gap between the armature ring 62 and the electromagnet 61.
In the embodiment of the invention, air gaps of 0.5mm and 0.3mm are respectively reserved between the armature ring 62 and the electromagnet 61 and the displacement sensor.
The radial support modules 60 are plural and are uniformly distributed in the axial direction of the rotor 10.
In the present embodiment, there are three radial support modules 60.
The invention also comprises an aircraft comprising at least one magnetic levitation rotor structure as described above, which magnetic levitation rotor structure is used to provide the aircraft with the required aerodynamic forces.
The operation process of the invention is as follows:
in the floating stage, the rotor 30 runs at a low speed under the support of the support balls 531, then the rotary driving module 40 drives the rotor 30 to rotate at a high speed, so that the rotor 10 rotates at a high speed to generate a vertical upward lift force, and simultaneously the axial bearing module 50 induces a bearing force supporting the gravity of the rotor 30 and the rotor lift force due to the high-speed running of the rotor 30, so that the rotor 30 is suspended, separated from the physical support of the balls, and transmits the lift force generated by the rotor 10 to the rotor stator 20 to pull the aircraft to take off; when the rotor (10) is ready to stop working (the rotation speed of the blades is gradually reduced until the rotation is stopped), the rotation speed of the rotor (30) is gradually reduced, the lift force is gradually reduced to complete the landing of the aircraft, and the rotation of the rotor (30) is stopped; during the flight, the adjustment of the flight speed and the attitude is realized by adjusting the rotating speed of the rotor wing 10 and then adjusting the lift force. During the whole process, the rotor 10 and the rotor 30 are always in the equilibrium position in the radial position by changing the electromagnetic force of the radial support module.
During the braking process, the rotor speed can be optionally rapidly reduced to a stop by the back-drive of the rotary drive module 40.
The magnetic suspension rotor wing structure utilizes the advantages of non-contact and high rotating speed of the magnetic suspension technology, solves the problem that a large-size rotor wing cannot be supported by a mechanical bearing at the outer side, and can effectively reduce the vibration noise of an aircraft and improve the stealth performance of the aircraft.
The above description is only for the best mode of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (10)
1. A magnetic suspension rotor wing structure is characterized in that the magnetic suspension rotor wing structure comprises a rotor wing (10), a rotor wing stator (20), a rotor wing rotor (30), a rotary driving module (40) and an axial supporting module (50);
the rotor stator (20) comprises an upper rotor stator (21) and a lower rotor stator (22) which are oppositely arranged so as to form an accommodating part (23) for placing the rotor (30);
the rotary driving module (40) comprises an electromagnetic excitation stator (41) and an electromagnetic excitation rotor (42), the electromagnetic excitation stator (41) is fixedly arranged on the upper rotor stator (21) and/or the lower rotor stator (22), the electromagnetic excitation rotor (42) is fixed on the rotor (10), and the rotor (10) is driven to rotate through the electromagnetic excitation stator (41) and the electromagnetic excitation rotor (42);
the rotor wing rotors (30) are relatively fixed along the radial direction of the rotor wing (10);
axial support module (50) include with rotor (30) non-contact support permanent magnetism array (52) and response rail (51) and with rotor (30) contact support assembly (53) that support, response rail (51) set up in on rotor (30), just permanent magnetism array (52) set up in go up rotor stator (21) and down rotor stator (22) on, support assembly (53) set up respectively in go up rotor stator (21) and down rotor stator (22) support with the contact rotor (30).
2. Magnetic levitation rotor structure according to claim 1, further comprising a radial support module (60), the radial bearing module (60) comprising an electromagnet (61) and an armature ring (62), the armature ring (62) being arranged radially along the rotor (10) and at the end of the rotor (30), the electromagnet (61) being arranged on the rotor stator (20) opposite to the armature ring (62).
3. Magnetic levitation rotor structure according to claim 2, wherein the radial support module (60) further comprises a displacement sensor (63), the displacement sensor (63) being arranged on the electromagnet (61) in a position opposite the armature ring (62) in a radial direction of the rotor (10).
4. The maglev rotor structure of claim 3, wherein the electromagnets (61) comprise a first electromagnet (61a) arranged radially along the rotor (10) and a second electromagnet (61b) and a third electromagnet (61c) arranged axially along the rotor (10), the first electromagnet (61a), the second electromagnet (61b) and the third electromagnet (61c) being mounted to the rotor stator (20).
5. The maglev rotor structure of claim 4, wherein the armature ring (62) has a gap with the displacement sensor (63) and the electromagnet (61), and the gap between the armature ring (62) and the displacement sensor (63) is smaller than the gap in front of the armature ring (62) and the electromagnet (61).
6. Magnetic levitation rotor structure according to any one of claims 1-5, wherein the radial support modules (60) are provided in plurality and are distributed uniformly along the axial direction of the rotor (10).
7. Magnetic levitation rotor structure according to claim 1, wherein the support assembly (53) comprises a support bead (531) for supporting the rotor (30) and a cage (532) for limiting the radial movement of the support bead along the rotor (10), the cage (532) being fixed to the rotor stator (20).
8. Magnetic levitation rotor structure according to claim 7, wherein the support bead (531) has a gap a with the rotor (30) and the induction track (51) has a gap B with the permanent magnet array (52), and the gap B between the induction track (51) and the permanent magnet array (52) is larger than the gap a between the support bead (531) and the rotor (30).
9. The magnetic levitation rotor structure according to claim 1, wherein the sensing area a of the permanent magnet array (51) with respect to the sensing track (51) is smaller than the sensing area B of the sensing track (51) with respect to the permanent magnet array (52), and the sensing area a of the permanent magnet array (52) is projected within the profile of the sensing area B of the sensing track (51).
10. An aircraft, characterized in that the aircraft comprises a magnetic levitation rotor structure according to any one of claims 1 to 9 for providing aerodynamic forces to the aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810677921.XA CN108945404A (en) | 2018-06-27 | 2018-06-27 | A kind of magnetic suspension rotor structure and the aircraft with it |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810677921.XA CN108945404A (en) | 2018-06-27 | 2018-06-27 | A kind of magnetic suspension rotor structure and the aircraft with it |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108945404A true CN108945404A (en) | 2018-12-07 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810677921.XA Withdrawn CN108945404A (en) | 2018-06-27 | 2018-06-27 | A kind of magnetic suspension rotor structure and the aircraft with it |
Country Status (1)
| Country | Link |
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| CN (1) | CN108945404A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110356553A (en) * | 2019-08-29 | 2019-10-22 | 吕福瑞 | A kind of wheel rotor aircraft |
| CN112622547A (en) * | 2020-12-24 | 2021-04-09 | 中国直升机设计研究所 | Rotor wheel and hovercar |
| CN113086219A (en) * | 2021-04-29 | 2021-07-09 | 中国航空发动机研究院 | Shaftless electric engine for aircraft, control method and aircraft |
| CN115158650A (en) * | 2022-08-03 | 2022-10-11 | 浙江大学 | A double-layer top-mounted electrostatic drive aircraft |
| CN118560694A (en) * | 2024-05-21 | 2024-08-30 | 四川天舜动力科技有限公司 | Magnetic suspension rotor with built-in rotor stator and aircraft thereof |
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| WO2001087707A1 (en) * | 2000-05-15 | 2001-11-22 | Sunlase, Inc. | Aircraft and hybrid with magnetic airfoil suspension and drive |
| CN1647998A (en) * | 2003-07-30 | 2005-08-03 | C.R.F.阿西安尼顾问公司 | Flying machine |
| CN107089323A (en) * | 2016-02-17 | 2017-08-25 | 徐丛逸 | A kind of aircraft rotor driver and aircraft |
| CN108100245A (en) * | 2016-11-24 | 2018-06-01 | 中航贵州飞机有限责任公司 | Full electromagnetic suspension magnetic control rotor system |
| CN108382566A (en) * | 2018-01-22 | 2018-08-10 | 武汉理工大学 | A kind of magnetic suspension rotor structure |
-
2018
- 2018-06-27 CN CN201810677921.XA patent/CN108945404A/en not_active Withdrawn
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2001087707A1 (en) * | 2000-05-15 | 2001-11-22 | Sunlase, Inc. | Aircraft and hybrid with magnetic airfoil suspension and drive |
| CN1647998A (en) * | 2003-07-30 | 2005-08-03 | C.R.F.阿西安尼顾问公司 | Flying machine |
| CN107089323A (en) * | 2016-02-17 | 2017-08-25 | 徐丛逸 | A kind of aircraft rotor driver and aircraft |
| CN108100245A (en) * | 2016-11-24 | 2018-06-01 | 中航贵州飞机有限责任公司 | Full electromagnetic suspension magnetic control rotor system |
| CN108382566A (en) * | 2018-01-22 | 2018-08-10 | 武汉理工大学 | A kind of magnetic suspension rotor structure |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110356553A (en) * | 2019-08-29 | 2019-10-22 | 吕福瑞 | A kind of wheel rotor aircraft |
| CN112622547A (en) * | 2020-12-24 | 2021-04-09 | 中国直升机设计研究所 | Rotor wheel and hovercar |
| CN112622547B (en) * | 2020-12-24 | 2023-02-24 | 中国直升机设计研究所 | Rotor wheel and hovercar |
| CN113086219A (en) * | 2021-04-29 | 2021-07-09 | 中国航空发动机研究院 | Shaftless electric engine for aircraft, control method and aircraft |
| CN115158650A (en) * | 2022-08-03 | 2022-10-11 | 浙江大学 | A double-layer top-mounted electrostatic drive aircraft |
| CN118560694A (en) * | 2024-05-21 | 2024-08-30 | 四川天舜动力科技有限公司 | Magnetic suspension rotor with built-in rotor stator and aircraft thereof |
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Application publication date: 20181207 |