CN105620727A - Low-noise unmanned aerial vehicle rotor wing/propeller - Google Patents
Low-noise unmanned aerial vehicle rotor wing/propeller Download PDFInfo
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- CN105620727A CN105620727A CN201610063152.5A CN201610063152A CN105620727A CN 105620727 A CN105620727 A CN 105620727A CN 201610063152 A CN201610063152 A CN 201610063152A CN 105620727 A CN105620727 A CN 105620727A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/18—Aerodynamic features
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
-
- 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
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Remote Sensing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides a low-noise unmanned aerial vehicle rotor wing/propeller which comprises blades. The front edge of each blade is of a sine-wave-shaped joint structure. The tail edge of each blade is of an isosceles triangle serrated structure. Microarray membrane structures are bonded to the suction faces of wing tips of the blades. Each microarray membrane structure is composed of a basic sheet and multiple flexible columns evenly distributed on the basic sheet. By the adoption of the low-noise unmanned aerial vehicle rotor wing/propeller, the blade design structure which is feasible, economical and environment-friendly is provided, the noise of the unmanned aerial vehicle rotor wing/propeller is lowered to a certain degree, the special requirements for the unmanned aerial vehicle noise level on different occasions can be met, the efficiency of an unmanned aerial vehicle is improved, the running capacity of the unmanned aerial vehicle is enhanced, and the low-noise unmanned aerial vehicle rotor wing/propeller can save more energy, is more environment-friendly and has the economic significance.
Description
Technical field
The present invention relates to unmanned plane rotor/propeller noise reduction technology field, specifically a kind of low noise unmanned plane rotor/propeller.
Background technology
Society, along with the technology of unmanned plane is more and more progressive, more and more many occasions its figure visible, such as military surveillance, assist anti-terrorism etc., unmanned plane has played great role, reduces unnecessary loss and improves success rate. But in some cases, its noise problem brings hidden danger to its safety, as military surveillance generation unmanned plane is found and fallen event. The reason that unmanned plane is found is largely precisely due to it has relatively larger noise, and its low altitude flight, volume are little, not easily found by radar, but noise governs its safety. For problems, present countries in the world all start the upsurge of one research low noise unmanned plane.
In general, the reduction of noise has two kinds of methods: active noise reduction and passive noise reduction. Active noise reduction is primarily referred to as offsets existing noise field with relevant sound wave, it is suppressed that produce the vibration source of noise. The units such as acoustics institute of domestic Nanjing University, utilize and the method achieve active noise reduction, and experiment effect clearly, but is at the laboratory research stage, far do not reach the degree of practicality. When in the face of the unmanned plane rotor/propeller complex sound field in spatial distribution, this mode more seems helpless. So-called passive noise reduction mainly includes by energy that the changes mechanical energy of incident acoustic wave is other forms such as heat energy or modifying its external structure by sound absorption structure so that fluid adsorbs its surface more, reduces fluid and separates and come off, thus reducing the generation of noise. For the situation of unmanned plane rotor/propeller quick rotation in space, sound absorption structure is utilized also to be difficult to carry out to the target reaching noise reduction. How last research exactly feasible for it reaches the purpose of noise reduction by the space structure of modification unmanned plane rotor/propeller.
Summary of the invention
It is an object of the invention to provide a kind of low noise unmanned plane rotor/propeller, it is possible to obtain effective noise reduction, practical, economic and environment-friendly.
The technical scheme is that
A kind of low noise unmanned plane rotor/propeller, including blade, the leading edge of described blade is sinuous nodular structure, the trailing edge of described blade is the broached-tooth design of isosceles triangle shape, being bonded with microarray diaphragm structure on the wing tip suction surface of described blade, described microarray diaphragm structure is made up of substrate and equally distributed some flexible columns of being arranged on substrate.
Described low noise unmanned plane rotor/propeller, described nodular structure is made up of several tuberositys, and the height value of described tuberosity is 0.005L��0.2L, and the width value of described tuberosity is 3mm��30mm, and the number value of described tuberosity is 2��20; Wherein, L represents the mean chord of single paddle, and its value is the horizontal projected area ratio with the span of single paddle, and its unit is mm.
Described low noise unmanned plane rotor/propeller, described broached-tooth design is made up of several sawtooth, and the height value of described sawtooth is 0.01L��0.4L, and the width value of described sawtooth is 0.01L��0.5L, and the number value of described sawtooth is 3��50; Wherein, L represents the mean chord of single paddle, and its value is the horizontal projected area ratio with the span of single paddle, and its unit is mm.
Described low noise unmanned plane rotor/propeller, the height value of described flexible column is 0.01%L��30%L, and the basal diameter value of described flexible column is 0.1 �� L��30%L, and described flexible column distribution density value on substrate is 0.5%��20%; Wherein, L represents the mean chord of single paddle, and its value is the horizontal projected area ratio with the span of single paddle, and its unit is mm.
The invention have the benefit that
(1) for the complexity of unmanned plane rotor/propeller noise, the present invention proposes a kind of practical blade design structure economic and environment-friendly again, reduce the noise of unmanned plane rotor/propeller to a certain extent, it is possible to meet the different occasion particular/special requirement to unmanned plane noise level.
(2) present invention is copy in nature the owl structure with " quiet " flight characteristics to get based on coupling bionical denoising structure, the efficiency of unmanned plane can be improved, the flying power making unmanned plane is strengthened, more energy-conserving and environment-protective, has economic implications. Although object of study of the present invention is for unmanned plane rotor/propeller, but one or more in leading edge nodular structure, trailing edge broached-tooth design and wing tip suction surface microarray diaphragm structure these three structure can be used as rotating machineries such as fan, axial flow blower, turbines, can be used alone or combine use, it is also possible to being used for solving the aerodynamic noise problem of aircraft.
(3) The present invention gives the span of above-mentioned three kinds of structural parameters, the size Selection of concrete structure in practical application is had directive significance by this.
(4) above-mentioned three kinds of structures that the present invention proposes are except being fixed to integration with blade, it is also possible to make and can tear can fill movable open, in order to are used according to practical situation, are even combined formation active noise reduction system with control system.
Accompanying drawing explanation
Fig. 1 is the structural representation of the present invention;
Fig. 2 is the A portion enlarged drawing of Fig. 1;
Fig. 3 is the B portion enlarged drawing of Fig. 1;
Fig. 4 is the C portion enlarged drawing of Fig. 1.
Detailed description of the invention
The present invention is further illustrated below in conjunction with the drawings and specific embodiments.
As shown in Figure 1 to 4, a kind of low noise unmanned plane rotor/propeller, including blade 1, the leading edge 11 of blade 1 adopts sinuous nodular structure, the trailing edge 12 of blade 1 adopts the broached-tooth design of isosceles triangle shape, being bonded with microarray diaphragm structure 2 on the wing tip suction surface of blade 1, wherein, microarray diaphragm structure 2 is made up of substrate and equally distributed some flexible columns 21 of being arranged on substrate.
The major parameter of nodular structure includes tuberosity height a, tuberosity width b, node number M, and the span after these three parameter optimization is as follows:
Tuberosity height a value is at 0.005L��0.2L;
Tuberosity width b value is at 3mm��30mm;
Node number M value is 2��20.
The major parameter of broached-tooth design includes sawtooth height c, tooth width d, sawtooth number N, and the span after these three parameter optimization is as follows:
Sawtooth height c value is at 0.01L��0.4L;
Tooth width d value is at 0.01L��0.5L;
Sawtooth number N value is 3��50.
The microarray diaphragm structure 2 pasted on wing tip suction surface is to adopt MEMS technology to process circular silicon post holes array or nickel post holes array mould plate, and again through building and spin coating PDMS flexible material, curing and demolding obtains. Wherein, the height of silicon post holes or nickel post holes or diameter are height and the diameter of the single flexible post 21 of microarray diaphragm structure 2.
Below with the example that is made as of silicon post holes array mould plate, introducing lower technical process, choose 3 inch silicon wafer for making silicon post holes array mould plate, utilize L-Edit software development mask plate patterns, concrete preparation flow is as follows:
(1) the single-sided polishing silicon chip selecting diameter 3 inches, crystal orientation to be (100), thickness is 500 microns, and then monocrystalline polished silicon slice carries out Chemical cleaning, rear dried;
(2) on the burnishing surface of monocrystalline polished silicon slice, growth deposits the silica membrane of 600 nanometer thickness and the metallic aluminium thin film of 200 nanometer thickness successively;
(3) on metallic aluminium thin film, the photoresist (positive glue) that a layer thickness is 2 microns is coated;
(4) the mechanical mask exposure of front lighting;
(5) development, fixing;
(6) corrosion window of front side aluminum is opened;
(7) corrosion window of front silicon dioxide is opened;
(8) erosion removal front lighting photoresist;
(9) inductively coupled plasma (ICP) deep etching process is adopted to etch the silicon degree of depth to design at corrosion window place, etching does not have metallic aluminium mask pattern and the monocrystal silicon of earth silicon mask figure protection zone, until the required degree of depth is to obtain meeting the silicon post holes array of design;
(10) front metal aluminum mask layer is removed;
(11) front earth silicon mask layer is removed;
(12) spraying process is adopted to make one layer containing fluorine-based compound in silicon post holes array surface, to reduce its adhesiveness.
Owing to silicon post holes array aperture is less, hole depth is relatively big, and the density of array is high, the adhesion caused because contact area is big between silicon post holes array and PDMS is very big, if silicon post holes array mould plate not being carried out pretreatment, damaged after very easily causing the PDMS demoulding, even it is difficult to the demoulding. It is therefore possible to use spraying process is at the silicon post holes array surface one layer ultra-thin fluoride compound of spraying, reduce its adhesiveness, in order to PDMS is from the demoulding silicon post holes array mould plate.
The major parameter of microarray diaphragm structure 2 includes the height h of flexible column 21, basal diameter �� and the flexible column 21 distribution density �� on substrate, wherein, the flexible column 21 distribution density �� on substrate refers to the ratio of the floor space sum of all flexible columns 21 and chip area on substrate, and the span after these three parameter optimization is as follows:
The height h value of flexible column 21 is at 0.01%L��30%L;
The basal diameter �� value of flexible column 21 is at 0.1 �� L��30%L;
The flexible column 21 distribution density �� value on substrate is 0.5%��20%.
Above-mentioned L represents the mean chord of single paddle 1, and its value is the horizontal projected area ratio with the span of single paddle 1, unit: mm.
In nature, some biologies were through the evolution of 1 years, defined the somatic stigmata with environmental suitability, and the quiet flight characteristics such as owl is exactly Typical Representative therein. The present invention is inspired by " quiet " flight of owl, in conjunction with coupling bionic theoretical foundation, design and made leading edge nodular structure, blade that trailing edge broached-tooth design couples with wing tip suction surface microarray diaphragm structure, and research obtains the combination of effect preferably parameter by experiment.
These three structure role in unmanned plane rotor/propeller noise reduction differs, and leading edge nodular structure mainly improves the momentum of downstream direction eddy current, increases its adhesive force, delays to separate, to suppressing noise to have certain effect while improving lift; Trailing edge broached-tooth design makes the radiated noise of unmanned plane rotor/propeller trailing edge be reduced further; Wing tip suction surface microarray diaphragm structure is that flow behavior according to the fluid on suction surface is arranged so that the fluid of modified can flow to trailing edge gently, reduces eddy current in a way and comes off the noise caused.
These three structure can difference be used alone in different objects according to the actual requirements, or combination of two (leading edge nodular structure couples with trailing edge broached-tooth design, leading edge nodular structure couples with wing tip suction surface microarray diaphragm structure, trailing edge broached-tooth design couples with wing tip suction surface microarray diaphragm structure), all can effectively reduce aerodynamic noise.
The results show, adopts the unmanned plane rotor/propeller of coupling biomimetic features, and its noise reduction becomes apparent from, and this greatly improves " quiet " performance of unmanned plane, has ensured the security performance of unmanned plane to a certain extent.
The coupling biomimetic features of the present invention has portability, except unmanned plane, it is also possible to need the rotating machinery of noise reduction for other, such as axial flow blower, fan, turbomachinery etc., it is possible to effectively reduce aerodynamic noise.
The above embodiment is only that the preferred embodiment of the present invention is described; not the scope of the present invention is defined; under the premise designing spirit without departing from the present invention; various deformation that technical scheme is made by those of ordinary skill in the art and improvement, all should fall in the protection domain that claims of the present invention are determined.
Claims (4)
1. low noise unmanned plane rotor/propeller, including blade, it is characterized in that: the leading edge of described blade is sinuous nodular structure, the trailing edge of described blade is the broached-tooth design of isosceles triangle shape, being bonded with microarray diaphragm structure on the wing tip suction surface of described blade, described microarray diaphragm structure is made up of substrate and equally distributed some flexible columns of being arranged on substrate.
2. low noise unmanned plane rotor/propeller according to claim 1, it is characterized in that: described nodular structure is made up of several tuberositys, the height value of described tuberosity is 0.005L��0.2L, and the width value of described tuberosity is 3mm��30mm, and the number value of described tuberosity is 2��20; Wherein, L represents the mean chord of single paddle, and its value is the horizontal projected area ratio with the span of single paddle, and its unit is mm.
3. low noise unmanned plane rotor/propeller according to claim 1, it is characterized in that: described broached-tooth design is made up of several sawtooth, the height value of described sawtooth is 0.01L��0.4L, and the width value of described sawtooth is 0.01L��0.5L, and the number value of described sawtooth is 3��50; Wherein, L represents the mean chord of single paddle, and its value is the horizontal projected area ratio with the span of single paddle, and its unit is mm.
4. low noise unmanned plane rotor/propeller according to claim 1, it is characterized in that: the height value of described flexible column is 0.01%L��30%L, the basal diameter value of described flexible column is 0.1 �� L��30%L, and described flexible column distribution density value on substrate is 0.5%��20%; Wherein, L represents the mean chord of single paddle, and its value is the horizontal projected area ratio with the span of single paddle, and its unit is mm.
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Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106114850A (en) * | 2016-06-23 | 2016-11-16 | 湖北大秀天域科技发展有限公司 | A kind of quiet blade and containing its rotor wing unmanned aerial vehicle |
| CN106275423A (en) * | 2016-08-23 | 2017-01-04 | 成都翼高九天科技有限公司 | A kind of novel unmanned plane rotor aerodynamics structure |
| WO2017106376A1 (en) * | 2015-12-18 | 2017-06-22 | Amazon Technologies, Inc. | Propeller blade treatments for sound control |
| CN107074344A (en) * | 2017-01-13 | 2017-08-18 | 深圳市大疆创新科技有限公司 | Propeller, power suit and the unmanned plane of aircraft |
| US10011346B2 (en) | 2015-12-18 | 2018-07-03 | Amazon Technologies, Inc. | Propeller blade indentations for improved aerodynamic performance and sound control |
| CN108263608A (en) * | 2016-12-30 | 2018-07-10 | X开发有限责任公司 | Rotor unit with asymmetric rotor blades |
| US10099773B2 (en) | 2015-12-18 | 2018-10-16 | Amazon Technologies, Inc. | Propeller blade leading edge serrations for improved sound control |
| WO2018206860A1 (en) * | 2017-05-11 | 2018-11-15 | Jose Buendia | Optimized helicopter - aeroplane - wing- propeller/rotor profiles |
| CN109356802A (en) * | 2018-12-29 | 2019-02-19 | 南京航空航天大学 | A kind of pneumatic equipment bladess with denoising structure |
| US10259562B2 (en) | 2015-12-18 | 2019-04-16 | Amazon Technologies, Inc. | Propeller blade trailing edge fringes for improved sound control |
| US10259574B2 (en) | 2015-12-18 | 2019-04-16 | Amazon Technologies, Inc. | Propeller surface area treatments for sound dampening |
| US10460717B2 (en) | 2015-12-18 | 2019-10-29 | Amazon Technologies, Inc. | Carbon nanotube transducers on propeller blades for sound control |
| CN110429158A (en) * | 2019-07-04 | 2019-11-08 | 云南师范大学 | The wet etching method of non-refrigerated infrared focal plane probe optical window |
| 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 |
| US10933988B2 (en) | 2015-12-18 | 2021-03-02 | Amazon Technologies, Inc. | Propeller blade treatments for sound control |
| CN112896503A (en) * | 2021-03-18 | 2021-06-04 | 厦门大学 | Helicopter rotor blade capable of restraining tip vortex of blade |
| CN113086169A (en) * | 2021-03-30 | 2021-07-09 | 吉林大学 | Bionic propeller capable of reducing drag and noise and preparation method thereof |
| US11163302B2 (en) | 2018-09-06 | 2021-11-02 | Amazon Technologies, Inc. | Aerial vehicle propellers having variable force-torque ratios |
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| US10933988B2 (en) | 2015-12-18 | 2021-03-02 | Amazon Technologies, Inc. | Propeller blade treatments for sound control |
| US10259562B2 (en) | 2015-12-18 | 2019-04-16 | Amazon Technologies, Inc. | Propeller blade trailing edge fringes for improved sound control |
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| US10460717B2 (en) | 2015-12-18 | 2019-10-29 | Amazon Technologies, Inc. | Carbon nanotube transducers on propeller blades for sound control |
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| CN108263608A (en) * | 2016-12-30 | 2018-07-10 | X开发有限责任公司 | Rotor unit with asymmetric rotor blades |
| CN108263608B (en) * | 2016-12-30 | 2021-11-26 | Wing航空有限责任公司 | Rotor unit with asymmetric rotor blades, aircraft and selection method |
| US11059576B2 (en) | 2016-12-30 | 2021-07-13 | Wing Aviation Llc | Rotor units having asymmetric rotor blades |
| WO2018129721A1 (en) * | 2017-01-13 | 2018-07-19 | 深圳市大疆创新科技有限公司 | Propeller of aircraft, power set and unmanned aerial vehicle |
| CN107074344B (en) * | 2017-01-13 | 2018-09-25 | 深圳市大疆创新科技有限公司 | Propeller, power suit and the unmanned plane of aircraft |
| CN107074344A (en) * | 2017-01-13 | 2017-08-18 | 深圳市大疆创新科技有限公司 | Propeller, power suit and the unmanned plane of aircraft |
| WO2018206860A1 (en) * | 2017-05-11 | 2018-11-15 | Jose Buendia | Optimized helicopter - aeroplane - wing- propeller/rotor profiles |
| US11163302B2 (en) | 2018-09-06 | 2021-11-02 | Amazon Technologies, Inc. | Aerial vehicle propellers having variable force-torque ratios |
| CN109356802B (en) * | 2018-12-29 | 2019-10-01 | 南京航空航天大学 | A kind of pneumatic equipment bladess with denoising structure |
| CN109356802A (en) * | 2018-12-29 | 2019-02-19 | 南京航空航天大学 | A kind of pneumatic equipment bladess with denoising structure |
| CN110429158A (en) * | 2019-07-04 | 2019-11-08 | 云南师范大学 | The wet etching method of non-refrigerated infrared focal plane probe optical window |
| 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 |
| CN112896503A (en) * | 2021-03-18 | 2021-06-04 | 厦门大学 | Helicopter rotor blade capable of restraining tip vortex of blade |
| 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 |
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