CN113002771A - Low-noise unmanned aerial vehicle rotor - Google Patents
Low-noise unmanned aerial vehicle rotor Download PDFInfo
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- CN113002771A CN113002771A CN202110369667.9A CN202110369667A CN113002771A CN 113002771 A CN113002771 A CN 113002771A CN 202110369667 A CN202110369667 A CN 202110369667A CN 113002771 A CN113002771 A CN 113002771A
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- 238000000034 method Methods 0.000 abstract 1
- 230000003313 weakening effect Effects 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008034 disappearance Effects 0.000 description 1
- 210000005069 ears Anatomy 0.000 description 1
- 230000037406 food intake Effects 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/463—Blade tips
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/467—Aerodynamic features
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
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Abstract
本发明提供一种低噪声无人机旋翼，涉及无人机技术领域，所述旋翼包含四个叶片：两个对位上反叶片与两个对位下反叶片。其中上反叶片具有上反翼尖，下反叶片具有下反翼尖，所述翼尖均具有尖削与后掠的结构特征。本发明通过上反与下反叶片相结合的设计，减小了旋转过程中翼尖涡对旋翼叶片的干扰，同时通过上反、下反、后掠、尖削的翼尖结构削弱翼尖涡的强度并提高升阻比，具有结构简单、便于加工、升阻比高、低噪声的特点。
The invention provides a low-noise unmanned aerial vehicle rotor, which relates to the technical field of unmanned aerial vehicles. The rotor comprises four blades: two upper counter-blades in alignment and two lower counter-blades in alignment. The upper anti-blade has an upper anti-wing tip, and the lower anti-blade has a lower anti-wing tip, and the wing tips all have the structural features of sharpening and swept back. The invention reduces the interference of the wing tip vortex on the rotor blade during the rotation process through the design of the combination of the upper reverse and the lower reverse blade, and at the same time weakens the wing tip vortex through the upper reverse, lower reverse, swept, and sharp wing tip structures. It has the characteristics of simple structure, easy processing, high lift-drag ratio and low noise.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a low-noise unmanned aerial vehicle rotor wing.
Background
With the continuous extension of the application field of unmanned aerial vehicles, the noise of unmanned aerial vehicles is becoming a topic of heat, so that the rotor wing which is one of the main noise sources of unmanned aerial vehicles is also receiving attention of many scientific researchers.
The rotor noise of the unmanned aerial vehicle can be divided into thickness noise, load noise, broadband noise and oar-vortex interference noise. Thickness noise is caused by the blades expelling air; load noise is caused by blade surface loading; the mechanism of broadband noise formation is many, and currently recognized are: self noise, ingestion noise, and blade-trail interference noise; the blade-vortex interference noise is caused by the blade interfering with the tip vortex. Wherein the main audio frequency of the paddle-vortex interference noise is in the auditory sensitivity region of human ears, and once the paddle-vortex interference occurs, the generated noise will cover other noise.
When the rotor wing generates positive lift, the pressure of the lower wing surface is higher than that of the upper wing surface, so that airflow bypasses the wingtip from the high-pressure area of the lower wing surface to the low-pressure area of the upper wing surface, and meanwhile, wingtip vortex with certain intensity is formed. The formation of the tip vortex reduces the lift of the rotor and interferes with the rotor blades to produce strong noise. The unmanned aerial vehicle rotor can compensate the lift disappearance that the wingtip vortex caused through improving the rotational speed, but higher rotational speed also can arouse stronger wingtip vortex and bigger noise.
Rotor that unmanned aerial vehicle used in the existing market mostly is straight appearance, and a minority has the wingtip structure of sharpening, sweepback, but all can't effectively weaken the wingtip vortex. Therefore, a low-noise rotor wing capable of effectively weakening the tip vortex of the rotor wing and improving the lift force is needed.
Disclosure of Invention
The invention aims to provide a high-efficiency low-noise rotor wing to solve the problems that the existing unmanned aerial vehicle rotor wing cannot effectively weaken wing tip vortex, and is low in efficiency and high in noise.
The invention comprises two contraposition lower anti-vanes 2 and two contraposition upper anti-vanes 3, wherein the lower anti-vanes are provided with lower anti-wingtips 1, and the upper anti-vanes are provided with upper anti-wingtips 4; the wingtips are provided with a taper structure and a sweepback angle; the blades are all equal in size.
The upper counter blade 3 and the lower counter blade 2 form an included angle of 5 degrees with the plane of the paddle disk.
The angles of the upper reflection and the lower reflection of the wingtip are both 45 degrees.
The root-tip ratio of the tapered structure part of the wingtip is 5: 1.
The trailing edge sweep angle of the wingtip is 47 degrees.
The invention has the beneficial effects that:
1. by adopting the four-blade structure, compared with a structure adopting more double blades, the four-blade structure can change two originally stronger wingtip vortexes into four weaker wingtip vortexes under the condition of the same solidity and lift force, thereby avoiding the generation of strong paddle-vortex interference and reducing the paddle-vortex interference noise; meanwhile, the aspect ratio of the blade is increased, the noise energy is dispersed, and the thickness and the load noise are reduced.
2. By adopting a structure combining double upper counter blades and double lower counter blades, the interference distance between the blades and the wing tip vortex is increased while the wing tip vortex is weakened, and the paddle-vortex interference is weakened; during forward flight, the front blade tip vortex cannot effectively interfere with the adjacent blades coming next, and the paddle-vortex interference phenomenon is reduced.
3. The upper reverse blade tip and the lower reverse blade tip are adopted, the interference distance of the blade-vortex is further increased, and meanwhile, the blade tip end plate can play a role in weakening the blade tip vortex.
4. The wing tip structure adopting sweepback and tapering can weaken the thickness noise of the rotor wing, and the sweepback structure can reduce the noise by weakening the Doppler effect.
Drawings
FIG. 1 is a schematic view of the structure of the present invention
FIG. 2 is a schematic view of the upper counter blade structure
FIG. 3 is a schematic view of the structure of a lower counter blade
FIG. 4 is a schematic view of a swept-back configuration of the wingtip
FIG. 5 is a schematic view of a hovering attitude wingtip vortex according to the present invention
FIG. 6 is a schematic view of tip vortices in hovering attitude with reference to four-blade flat wing
FIG. 7 is a sound pressure spectrum plot of a 5000RPM hover condition at 4m directly below the rotor
Wherein: 1. lower anti-wingtip 2, lower anti-blade 3, upper anti-blade 4, upper anti-wingtip
Detailed Description
The invention is described below with reference to the accompanying drawings.
As shown in fig. 1 to 4, the present invention comprises two aligned lower counter blades 2 and two aligned upper counter blades 3, wherein the lower counter blades have lower counter tips 1 and the upper counter blades have upper counter tips 4; the wingtips are provided with a taper structure and a sweepback angle; the blades are all equal in size.
The upper counter blade 3 and the lower counter blade 2 form an included angle of 5 degrees with the plane of the paddle disk.
The angles of the upper reflection and the lower reflection of the wingtip are both 45 degrees.
The root-tip ratio of the tapered structure part of the wingtip is 5: 1.
The trailing edge sweep angle of the wingtip is 47 degrees.
As shown in fig. 5 to 7, the combined structure of the upper and lower counter-blades allows the tip vortex of the rotor wing to dissipate earlier than that of a straight wing. The rotor wing during operation can produce four wing tip whirlpools at the wingtip, and the distance that the oar-whirlpool disturbed has been increased with anti-blade down to combining together on anti-blade down for the wingtip whirlpool of anti-blade on can't form stronger interference to anti-blade down. Under the condition that the blade solidity is equal, the four blades have smaller strength than the wing tip vortex generated by the two blades, and simultaneously, the noise energy is dispersed, so that the whole noise of the rotor wing is reduced. The upper and lower inverted wingtips can weaken the tip vortex, further increase the distance of the oar-vortex interference, reduce the noise of the rotor and improve the lift-drag ratio of the rotor. The swept-back structure of the wingtip can then attenuate the doppler effect and help reduce noise during forward flight attitude. According to simulation results, compared with a reference flat wing, the lift force is improved by about 6.2% (5.30N → 5.63N), and the noise obtained by monitoring the position 4m under the rotor wing is reduced by 2.68dB (54.88dB → 52.20dB) under the 5000RPM hovering condition.
Claims (5)
1. The utility model provides a low noise unmanned aerial vehicle rotor, its characterized in that, the rotor contains two counterpoint down anti-blade (2) and two counterpoint up anti-blade (3), wherein: the lower anti-vane (2) is provided with a lower anti-wingtip (1), and the upper anti-vane (3) is provided with an upper anti-wingtip (4); the wingtips are provided with a tapered structure and a trailing edge sweepback angle; the blades are all equal in size.
2. The upper counter blade (3) and the lower counter blade (2) according to claim 1 both form an angle of 5 ° with the plane of the paddle disk.
3. The wing tip dihedral and anhedral angles according to claim 1 are both 45 °.
4. The tip of claim 1 wherein the ratio of the root to the tip of the tapered portion of the tip is 5: 1.
5. The wing tip trailing edge sweep of claim 1 being 47 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110369667.9A CN113002771A (en) | 2021-03-26 | 2021-03-26 | Low-noise unmanned aerial vehicle rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110369667.9A CN113002771A (en) | 2021-03-26 | 2021-03-26 | Low-noise unmanned aerial vehicle rotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113002771A true CN113002771A (en) | 2021-06-22 |
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| CN202110369667.9A Pending CN113002771A (en) | 2021-03-26 | 2021-03-26 | Low-noise unmanned aerial vehicle rotor |
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Citations (13)
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| US20080003103A1 (en) * | 2004-09-23 | 2008-01-03 | Usa As Represented By The Administrator Of The National Aeronautics & Space Administration | Vortex control for rotor blade devices |
| CN201632056U (en) * | 2010-02-09 | 2010-11-17 | 深圳市兴耀华实业有限公司 | Propeller of model plane |
| US20110024552A1 (en) * | 2008-04-25 | 2011-02-03 | Karem Aircraft, Inc. | Anhedral Tip Blades for Tiltrotor Aircraft |
| CN203666986U (en) * | 2014-01-05 | 2014-06-25 | 曹乃承 | Aircraft |
| CN104044736A (en) * | 2014-07-08 | 2014-09-17 | 天津宏泽天成科技有限公司 | Rotor blade tip of unmanned helicopter |
| CN104139849A (en) * | 2014-08-07 | 2014-11-12 | 西北工业大学 | High-altitude propeller and propeller tip winglet capable of improving efficiency of high-altitude propeller |
| CN105923155A (en) * | 2016-06-08 | 2016-09-07 | 南京航空航天大学 | Low-noise paddle for rotor craft |
| US9592910B1 (en) * | 2015-12-18 | 2017-03-14 | Amazon Technologies, Inc. | Geometrically reconfigurable propellers |
| CN108163192A (en) * | 2017-12-29 | 2018-06-15 | 江苏方阔航空科技有限公司 | A kind of high-efficient low-noise rotor |
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| US20190225332A1 (en) * | 2018-01-19 | 2019-07-25 | Aerhart, LLC | Aeronautical Apparatus |
| CN209159997U (en) * | 2018-12-06 | 2019-07-26 | 酷黑科技（北京）有限公司 | A kind of duct rotor structure and flight equipment |
| CN210484191U (en) * | 2019-09-19 | 2020-05-08 | 江西天岳汽车电器有限公司 | An axial flow fan blade structure with reduced tip vortex noise |
-
2021
- 2021-03-26 CN CN202110369667.9A patent/CN113002771A/en active Pending
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| US20110024552A1 (en) * | 2008-04-25 | 2011-02-03 | Karem Aircraft, Inc. | Anhedral Tip Blades for Tiltrotor Aircraft |
| CN201632056U (en) * | 2010-02-09 | 2010-11-17 | 深圳市兴耀华实业有限公司 | Propeller of model plane |
| CN203666986U (en) * | 2014-01-05 | 2014-06-25 | 曹乃承 | Aircraft |
| CN104044736A (en) * | 2014-07-08 | 2014-09-17 | 天津宏泽天成科技有限公司 | Rotor blade tip of unmanned helicopter |
| CN104139849A (en) * | 2014-08-07 | 2014-11-12 | 西北工业大学 | High-altitude propeller and propeller tip winglet capable of improving efficiency of high-altitude propeller |
| US9592910B1 (en) * | 2015-12-18 | 2017-03-14 | Amazon Technologies, Inc. | Geometrically reconfigurable propellers |
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