CN106275423A - A kind of novel unmanned plane rotor aerodynamics structure - Google Patents
A kind of novel unmanned plane rotor aerodynamics structure Download PDFInfo
- Publication number
- CN106275423A CN106275423A CN201610705654.3A CN201610705654A CN106275423A CN 106275423 A CN106275423 A CN 106275423A CN 201610705654 A CN201610705654 A CN 201610705654A CN 106275423 A CN106275423 A CN 106275423A
- Authority
- CN
- China
- Prior art keywords
- blade
- unmanned plane
- winglet
- lift
- described blade
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Remote Sensing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a kind of novel unmanned plane rotor aerodynamics structure, including rotor shaft and the blade being connected in rotor shaft, the leading edge of described blade is sinusoidal wave-like configuration, the trailing edge of described blade is the broached-tooth design of isosceles right triangle, the end of described blade is provided with winglet, winglet is vertically mounted on blade tip, wing tip installs winglet, in order to hinder the air of upper and lower surface to stream, reduce the induced drag caused because of wingtip vortex, reduce and stream the destruction to lift, improve lift-drag ratio, reach to increase the purpose of lift, simultaneously, because using sinusoidal wave leading edge and jagged trailing edge, use bionic design, air drag is less, the noise produced is the lowest.It is an advantage of the current invention that: blade lift is high, and flying power is strong；During work, air drag is little, and noise is low.
Description
Technical field
The present invention relates to a kind of UAV Components, be specifically related to a kind of novel unmanned plane rotor aerodynamics structure.
Background technology
UAV is called for short " unmanned plane ", and english abbreviation is " UAV ", utilizes radio robot and provides for oneself
The most manned aircraft that presetting apparatus is handled.Can be divided into from technical standpoint definition: unmanned fixed-wing aircraft, unmanned VTOL
Machine, unmanned airship, depopulated helicopter, unmanned multi-rotor aerocraft, unmanned parasol etc..Unmanned plane presses application, can be divided into
Military and civilian.Military aspect, unmanned plane is divided into reconnaissance plane and target drone.Civilian aspect, unmanned plane+sector application, is unmanned plane
Real just needs；At present taking photo by plane, agricultural, plant protection, auto heterodyne, express transportation, disaster relief, observation wild animal, monitoring infection
The application in disease, mapping, news report, electric inspection process, the disaster relief, movies-making, manufacture romance etc. field, has greatly expanded nothing
Man-machine purposes own, developed country is also at actively extension sector application and development unmanned air vehicle technique.In November, 2013, middle its people
Issue " civilian push-button aircraft system driver management temporary provisions " with aviation office, AOPA association of China be responsible for the people
By the related management of unmanned plane.According to " regulation ", unmanned plane operation in inland of China can be divided into 11 according to type size, flying area
The situation of kind, the most only the unmanned plane of more than 116 kilograms and the dirigible of more than 4600 cubic metres are merging spatial domain flight by civil aviaton
Office's management, remaining situation, other flights including the most popular miniature aerial photography aircraft, managed by employer's organization,
Or be responsible for voluntarily by manipulator.
Traditional unmanned plane is unprotected device time out of control, easily crashes, and unmanned plane cost is higher, causes during crash
Economic loss is bigger.
Summary of the invention
When the technical problem to be solved is traditional unmanned plane aircraft maintenance normal flight, wing produces
Lift is not enough, and the noise that wing produces simultaneously is bigger, it is therefore intended that provide a kind of novel unmanned plane rotor aerodynamics structure,
Solving unmanned plane airfoil lift not enough, aircraft flying power is affected, the problem that noise is bigger simultaneously.
The present invention is achieved through the following technical solutions:
A kind of novel unmanned plane rotor aerodynamics structure, including rotor shaft and the blade being connected in rotor shaft, described oar
The leading edge of leaf is sinusoidal wave-like configuration, and the trailing edge of described blade is the broached-tooth design of isosceles right triangle, the end of described blade
End is provided with winglet, and winglet is vertically mounted on blade tip.Lift required during the aircraft normal flight of maintenance is
By wing upper and lower surface pressure differential produce, due to the existence of upper and lower surface pressure reduction, the air of wing lower surface near wing tip
Wingtip vortex can be formed around flowing to upper surface, causes wing tip near zone wing upper and lower surface pressure reduction to reduce, thus cause this district
The lift that territory produces reduces.In order to weaken this impact around flow phenomenon on lift, the wing tip of a lot of aircrafts installs winglet,
In order to hinder the air of upper and lower surface to stream, reduce the induced drag caused because of wingtip vortex, reduce and stream the destruction to lift, carry
High lift-drag ratio, reaching to increase the purpose of lift, meanwhile, because using sinusoidal wave leading edge and jagged trailing edge, using bionical
Learning design, air drag is less, and the noise of generation is the lowest.
The sinusoidal configuration of the leading edge of described blade, wavelength is the length of 0.1-0.125 times of blade, and amplitude is 0.6-0.9
Wavelength again.The leading edge air drag using this Proportionality design is less, more energy-conservation, is conducive to continuation of the journey.
The trailing edge of described blade is the broached-tooth design of isosceles right triangle, and triangle chord length is 0.02-0.025 times of blade
Length.The vibrations making air produce with the trailing edge of this Proportionality design are smaller, and during flight, noise is less.
Winglet be swept-back wing and in blade lateral bend, angle of sweep 30-40 degree, height be 0.2-0.3 times of blade
Length.High by the winglet stability of this Proportionality design, can effectively water conservancy diversion, the lift of raising blade.
The present invention compared with prior art, has such advantages as and beneficial effect:
1, a kind of novel unmanned plane rotor aerodynamics structure, blade lift is high, and flying power is strong.
2, a kind of novel unmanned plane rotor aerodynamics structure, during work, air drag is little, and noise is low.
Accompanying drawing explanation
Accompanying drawing described herein is used for providing being further appreciated by the embodiment of the present invention, constitutes of the application
Point, it is not intended that the restriction to the embodiment of the present invention.In the accompanying drawings:
Fig. 1 is present configuration schematic top plan view；
Fig. 2 is present configuration schematic front view；
Fig. 3 is winglet schematic side view of the present invention；
The parts title of labelling and correspondence in accompanying drawing:
1-rotor shaft, 2-leading edge, 3-trailing edge, 4-winglet, 5-blade.
Detailed description of the invention
For making the object, technical solutions and advantages of the present invention clearer, below in conjunction with embodiment and accompanying drawing, to this
Invention is described in further detail, and the exemplary embodiment of the present invention and explanation thereof are only used for explaining the present invention, do not make
For limitation of the invention.
Embodiment 1
As shown in Figures 1 to 3, a kind of novel unmanned plane rotor aerodynamics structure, including rotor shaft 1 be connected to rotor shaft 1
On the blade 5 of long 20cm, the leading edge 2 of described blade 5 is sinusoidal wave-like configuration, and wavelength is the length of 0.1 times of blade 5, amplitude
Being the wavelength of 0.9 times, the trailing edge 3 of described blade is the broached-tooth design of isosceles right triangle, and triangle chord length is 0.025 times of oar
The length of leaf 5, the end of described blade is provided with winglet 4, and winglet 4 is vertically mounted on blade tip, winglet 4
For swept-back wing and in blade lateral bend, 30 degree of angle of sweep, height is the length of 0.2 times of blade 5, according to experiment, uses this type
The rotor of blade 5 is when rotating speed is identical, and lift improves 10%, and noise reduces 8%.
Embodiment 2
The present embodiment differs only in embodiment 1, and wavelength is the length of 0.125 times of blade 5, and amplitude is the ripple of 0.75 times
Long, the length that triangle chord length is 0.02 times of blade 5 of the broached-tooth design of triangle, the angle of sweep of winglet 4 is 35 degree, high
Degree is the length of 0.225 times of blade 5, according to experiment, uses the rotor of this type blade 5 when rotating speed is identical, and lift improves
13%, noise reduces 10%.
Embodiment 3
The present embodiment differs only in, with embodiment 1, the length that wavelength is 0.1125 times of blade 5, and amplitude is the wavelength of 0.6 times,
The length that triangle chord length is 0.0225 times of blade 5 of the broached-tooth design of triangle, the angle of sweep of winglet 4 is 40 degree, high
Degree is the length of 0.25 times of blade 5, according to experiment, uses the rotor of this type blade 5 when rotating speed is identical, and lift improves 12%,
Noise reduces 11%.
Above-described detailed description of the invention, has been carried out the purpose of the present invention, technical scheme and beneficial effect further
Describe in detail, be it should be understood that the detailed description of the invention that the foregoing is only the present invention, be not intended to limit the present invention
Protection domain, all within the spirit and principles in the present invention, any modification, equivalent substitution and improvement etc. done, all should comprise
Within protection scope of the present invention.
Claims (4)
1. a novel unmanned plane rotor aerodynamics structure, including rotor shaft (1) and the blade that is connected in rotor shaft
(5), it is characterised in that the leading edge (2) of described blade (5) is sinusoidal wave-like configuration, the trailing edge (3) of described blade is isosceles right angle
The broached-tooth design of triangle, the end of described blade (5) is provided with winglet (4), and winglet (4) is vertically mounted on blade
(5) end.
One the most according to claim 1 novel unmanned plane rotor aerodynamics structure, it is characterised in that described blade
(5) sinusoidal configuration of leading edge (2), wavelength is the length of 0.1-0.125 times of blade (5), and amplitude is the ripple of 0.6-0.9 times
Long.
One the most according to claim 1 novel unmanned plane rotor aerodynamics structure, it is characterised in that described blade
Trailing edge (3) be the broached-tooth design of isosceles right triangle, triangle chord length is the length of 0.02-0.025 times of blade (5).
One the most according to claim 1 novel unmanned plane rotor aerodynamics structure, it is characterised in that winglet
(4) be swept-back wing and in blade (5) lateral bend, angle of sweep 30-40 degree, height is the length of 0.2-0.3 times of blade (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610705654.3A CN106275423A (en) | 2016-08-23 | 2016-08-23 | A kind of novel unmanned plane rotor aerodynamics structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610705654.3A CN106275423A (en) | 2016-08-23 | 2016-08-23 | A kind of novel unmanned plane rotor aerodynamics structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106275423A true CN106275423A (en) | 2017-01-04 |
Family
ID=57615361
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610705654.3A Pending CN106275423A (en) | 2016-08-23 | 2016-08-23 | A kind of novel unmanned plane rotor aerodynamics structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106275423A (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106741857A (en) * | 2017-03-02 | 2017-05-31 | 南京那尔朴电子有限公司 | A kind of propeller that can be adjusted with thrust |
| CN108974326A (en) * | 2018-06-28 | 2018-12-11 | 西安交通大学 | A kind of bionical wave leading edge winglet device |
| CN110406660A (en) * | 2019-09-04 | 2019-11-05 | 江苏黑锋航空科技有限公司 | A kind of propeller and preparation method thereof |
| CN110422317A (en) * | 2019-09-04 | 2019-11-08 | 江苏黑锋航空科技有限公司 | A kind of propeller paddle set and preparation method thereof |
| CN110466751A (en) * | 2019-09-03 | 2019-11-19 | 中国科学院合肥物质科学研究院 | A kind of the high effective portable unmanned plane rotor structure and its design method of low noise |
| CN111046493A (en) * | 2019-12-04 | 2020-04-21 | 中国直升机设计研究所 | Rotor wing aerodynamic noise calculation method based on concentrated load |
| CN111874219A (en) * | 2020-07-28 | 2020-11-03 | 东南大学 | Noise reduction method for miniature single-rotor unmanned helicopter platform |
| CN111907699A (en) * | 2020-08-10 | 2020-11-10 | 北京航空航天大学 | Helicopter rotor dynamic stall control structure based on whale fin-imitated leading edge |
| CN112298549A (en) * | 2020-10-30 | 2021-02-02 | 北京航空航天大学 | Tilt rotor with bionic wavy leading edge and tilt rotor aircraft |
| CN112429250A (en) * | 2020-11-26 | 2021-03-02 | 广东国士健科技发展有限公司 | Auxiliary rotor wing device rotating in wingspan direction around main rotor wing |
| CN113086169A (en) * | 2021-03-30 | 2021-07-09 | 吉林大学 | Bionic propeller capable of reducing drag and noise and preparation method thereof |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5533865A (en) * | 1993-11-04 | 1996-07-09 | Stork Product Engineering B.V. | Wind turbine |
| 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 |
| CN204507266U (en) * | 2015-04-01 | 2015-07-29 | 天峋创新（北京）科技有限公司 | Low induced drag lifting airscrew anti-under a kind of wing tip sweepback |
| CN105129061A (en) * | 2015-08-10 | 2015-12-09 | 上海斯玛德大推船用螺旋桨设计有限公司 | Propeller |
| CN105346720A (en) * | 2015-11-13 | 2016-02-24 | 深圳市道通智能航空技术有限公司 | Blades, propeller and unmanned aerial vehicle |
| CN205221107U (en) * | 2015-11-26 | 2016-05-11 | 中国科学院合肥物质科学研究院 | Low noise unmanned aerial vehicle rotor based on coupling is bionical |
| CN105620727A (en) * | 2016-01-30 | 2016-06-01 | 中国科学院合肥物质科学研究院 | Low-noise unmanned aerial vehicle rotor wing/propeller |
| CN205418069U (en) * | 2016-01-30 | 2016-08-03 | 中国科学院合肥物质科学研究院 | Low noise unmanned aerial vehicle rotor / screw |
| CN206031777U (en) * | 2016-08-23 | 2017-03-22 | 成都翼高九天科技有限公司 | Novel unmanned aerial vehicle aerodynamic structure |
-
2016
- 2016-08-23 CN CN201610705654.3A patent/CN106275423A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5533865A (en) * | 1993-11-04 | 1996-07-09 | Stork Product Engineering B.V. | Wind turbine |
| 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 |
| CN204507266U (en) * | 2015-04-01 | 2015-07-29 | 天峋创新（北京）科技有限公司 | Low induced drag lifting airscrew anti-under a kind of wing tip sweepback |
| CN105129061A (en) * | 2015-08-10 | 2015-12-09 | 上海斯玛德大推船用螺旋桨设计有限公司 | Propeller |
| CN105346720A (en) * | 2015-11-13 | 2016-02-24 | 深圳市道通智能航空技术有限公司 | Blades, propeller and unmanned aerial vehicle |
| CN205221107U (en) * | 2015-11-26 | 2016-05-11 | 中国科学院合肥物质科学研究院 | Low noise unmanned aerial vehicle rotor based on coupling is bionical |
| CN105620727A (en) * | 2016-01-30 | 2016-06-01 | 中国科学院合肥物质科学研究院 | Low-noise unmanned aerial vehicle rotor wing/propeller |
| CN205418069U (en) * | 2016-01-30 | 2016-08-03 | 中国科学院合肥物质科学研究院 | Low noise unmanned aerial vehicle rotor / screw |
| CN206031777U (en) * | 2016-08-23 | 2017-03-22 | 成都翼高九天科技有限公司 | Novel unmanned aerial vehicle aerodynamic structure |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106741857A (en) * | 2017-03-02 | 2017-05-31 | 南京那尔朴电子有限公司 | A kind of propeller that can be adjusted with thrust |
| CN108974326A (en) * | 2018-06-28 | 2018-12-11 | 西安交通大学 | A kind of bionical wave leading edge winglet device |
| CN110466751A (en) * | 2019-09-03 | 2019-11-19 | 中国科学院合肥物质科学研究院 | A kind of the high effective portable unmanned plane rotor structure and its design method of low noise |
| CN110406660A (en) * | 2019-09-04 | 2019-11-05 | 江苏黑锋航空科技有限公司 | A kind of propeller and preparation method thereof |
| CN110422317A (en) * | 2019-09-04 | 2019-11-08 | 江苏黑锋航空科技有限公司 | A kind of propeller paddle set and preparation method thereof |
| CN111046493A (en) * | 2019-12-04 | 2020-04-21 | 中国直升机设计研究所 | Rotor wing aerodynamic noise calculation method based on concentrated load |
| CN111874219A (en) * | 2020-07-28 | 2020-11-03 | 东南大学 | Noise reduction method for miniature single-rotor unmanned helicopter platform |
| CN111907699A (en) * | 2020-08-10 | 2020-11-10 | 北京航空航天大学 | Helicopter rotor dynamic stall control structure based on whale fin-imitated leading edge |
| CN112298549A (en) * | 2020-10-30 | 2021-02-02 | 北京航空航天大学 | Tilt rotor with bionic wavy leading edge and tilt rotor aircraft |
| CN112429250A (en) * | 2020-11-26 | 2021-03-02 | 广东国士健科技发展有限公司 | Auxiliary rotor wing device rotating in wingspan direction around main rotor wing |
| CN113086169A (en) * | 2021-03-30 | 2021-07-09 | 吉林大学 | Bionic propeller capable of reducing drag and noise and preparation method thereof |
| CN113086169B (en) * | 2021-03-30 | 2022-07-12 | 吉林大学 | Bionic propeller capable of reducing drag and noise and preparation method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106275423A (en) | A kind of novel unmanned plane rotor aerodynamics structure | |
| US11634222B2 (en) | Vertical take-off and landing unmanned aerial vehicle having foldable fixed wing and based on twin-ducted fan power system | |
| US10414491B2 (en) | VTOL aircraft with tiltable propellers | |
| US10005554B2 (en) | Unmanned aerial vehicle | |
| US20190002076A1 (en) | Low stall or minimum control speed aircraft | |
| WO2013048339A1 (en) | An unmanned aerial vehicle | |
| CN105083550A (en) | Fixed-wing aircraft realizing vertical take-off and landing | |
| CN103803078A (en) | Flying saucer type helicopter utilizing active airflow to generate lifting power | |
| CN103332293A (en) | Tilting double-duct subminiature unmanned plane | |
| CN205418102U (en) | All -wing aircraft formula rotor craft that verts | |
| US20210245876A1 (en) | Tail sitter | |
| CN105947192A (en) | Tilting double-duct unmanned aerial vehicle | |
| CN104590555A (en) | Electrodynamic multi-rotor helicopter | |
| CN107140208A (en) | STOL top load multiaxis fans wing unmanned plane | |
| CN108394556A (en) | A kind of efficient tilting rotor wing unmanned aerial vehicle | |
| CN204489187U (en) | A kind of vertical takeoff and landing horizontal flight unmanned plane | |
| CN204660024U (en) | A kind of dish-type rotor unmanned helicopter | |
| CN107010205A (en) | A kind of aircraft and its control method with the empennage that can vert | |
| CN205022854U (en) | Deformable compound aircraft | |
| CN206719540U (en) | Tilting rotor type VUAV based on Flying-wing | |
| CN203698647U (en) | Low-wind-resistance and high-balance light flying wing type unmanned aerial vehicle | |
| CN211281472U (en) | Duct tail sitting posture VTOL unmanned aerial vehicle | |
| CN211253017U (en) | Unmanned aerial vehicle with tandem wings capable of vertically taking off and landing | |
| CN206031777U (en) | Novel unmanned aerial vehicle aerodynamic structure | |
| CN207523932U (en) | Tandem wing tilting rotor wing unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170104 |
|
| RJ01 | Rejection of invention patent application after publication |