CN105584625A - Propeller and aircraft - Google Patents
Propeller and aircraft Download PDFInfo
- Publication number
- CN105584625A CN105584625A CN201610118950.3A CN201610118950A CN105584625A CN 105584625 A CN105584625 A CN 105584625A CN 201610118950 A CN201610118950 A CN 201610118950A CN 105584625 A CN105584625 A CN 105584625A
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- Prior art keywords
- time
- blade
- oar
- hoop
- screw
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Classifications
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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
Abstract
The invention relates to the technical field of unmanned aerial vehicles, and in particular discloses a propeller and an aircraft. The propeller comprises a propeller hoop and at least two blades connected with the propeller hoop, wherein when the distance from each blade to the center of the propeller hoop is a, the width of the blade is b, and the following conditions are met: when a is more than or equal to 0 mm and less than or equal to 10 mm, b is more than 11 mm and less than 16 mm; when a is more than 10 mm and less than or equal to 30 mm, b is more than 14 mm and less than 31 mm; when a is more than 30 mm and less than or equal to 80 mm, b is more than 18 mm and less than 31 mm; when a is more than 80 mm and less than or equal to 100 mm, b is more than 13 mm and less than 18 mm; and when a is more than 100 mm and less than or equal to 120 mm, b is more than 9 mm and less than 16 mm. According to the propeller, by setting different blade widths at different positions of the radius of each blade, under the same energy consumption, the lift force of the propeller is improved, the air resistance is reduced and the efficiency is increased.
Description
[technical field]
The present invention relates to unmanned plane technical field, relate in particular to a kind of screw and aircraft.
[background technology]
Screw produces the necessary lift of unmanned helicopter flight, pulling force and steering force, collects multinomial meritCan be. Can complete efficiently the basic characteristics that vertical flight is depopulated helicopter screw. FromA properller is born 100 years till now, along with the science and technology in a centuryDevelopment, the design of screw several times changes, and has been tending towards perfect. Along with the rise of SUAV,Small propeller becomes the main direction of research and design gradually, and high efficiency screw can be greatImprove the flying quality of unmanned plane.
Hang time is one of principal element determining unmanned plane performance. Improve the hang time, have twoMain path, one is the weight that reduces unmanned plane; Second is the efficiency that improves screw. SpiralThe raising of oar efficiency depends on air dynamic behaviour to screw and the grasp of dynamics, andThe Design and analysis methods of blade. Existing screw resistance is large, efficiency is low, causes unmanned vehicleFlying speed is little, endurance distance is short. How to design effective raising unmanned plane lift and flight timeScrew is that prior art has problem to be solved.
[summary of the invention]
The present invention is intended to overcome the defect existing in prior art, and a kind of unmanned plane liter that effectively improves is providedThe screw of power and flight time and use the aircraft of this screw.
For solving the problems of the technologies described above, the invention provides following technical scheme:
A kind of screw, at least two blades that comprise oar hoop and be connected with described oar hoop, described bladeWhen the length at distance described Jiang Gu center is a, the width of described blade is b, and meets the following conditions:
In the time of 0mm≤a≤10mm, 11mm < b < 16mm;
In the time of 10mm < a≤30mm, 14mm < b < 31mm;
In the time of 30mm < a≤80mm, 18mm < b < 31mm;
In the time of 80mm < a≤100mm, 13mm < b < 18mm;
In the time of 100mm < a≤120mm, 9mm < b < 16mm.
In certain embodiments, when the length at described blade distance described Jiang Gu center is a, described oarThe width of leaf is b, also meets the following conditions:
In the time of a=0mm, 11mm < b < 14mm;
In the time of a=10mm, 14mm < b < 16mm;
In the time of a=30mm, 27mm < b < 31mm;
In the time of a=50mm, 27mm < b < 31mm;
In the time of a=80mm, 18mm < b < 21mm;
In the time of a=100mm, 13mm < b < 16mm;
In the time of a=120mm, 9mm < b < 12mm.
In certain embodiments, when the length at described blade distance described Jiang Gu center is a, described oarThe width of leaf is b, also meets the following conditions:
In the time of a=0mm, b=12.9mm;
In the time of a=10mm, b=15.5mm;
In the time of a=30mm, b=29.0mm;
In the time of a=50mm, b=29.0mm;
In the time of a=80mm, b=20.0mm;
In the time of a=100mm, b=14.8mm;
In the time of a=120mm, b=11.0mm.
In certain embodiments, when the length at described blade distance described Jiang Gu center is a, described oarThe width of leaf is b, and described b is piecewise function, and meets the following conditions:
In the time of 0mm≤a≤10mm, b=0.26a+12.9mm;
In the time of 10mm < a≤30mm, b=0.675a+8.75mm;
In the time of 30mm < a≤50mm, b=29mm;
In the time of 50mm < a≤80mm, b=﹣ 0.3a+44mm;
In the time of 80mm < a≤100mm, b=﹣ 0.26a+40.8mm;
In the time of 100mm < a≤120mm, b=﹣ 0.19a+33.8mm.
In certain embodiments, when the length at described blade distance described Jiang Gu center is a, described oarThe width of leaf is b, and described b is smooth function;
In the time of 0mm≤a≤10mm, described b curved;
In the time of 10mm < a≤30mm, described b curved two;
In the time of 30mm < a≤50mm, described b curved three;
In the time of 50mm < a≤80mm, described b curved four;
In the time of 80mm < a≤100mm, described b curved five;
In the time of 100mm < a≤120mm, described b curved six;
Described curve one, curve two, curve three, curve four, curve five and curve six are non-homogeneousRational curve.
In certain embodiments, described blade comprises blade root, leaf central part and leaf ending, described bladeWith described oar hoop contact position be described blade root, the edge of described blade is described leaf ending, connect instituteThe part of stating leaf heel and described leaf ending is described leaf central part.
In certain embodiments, described blade width is increased to described leaf from the 12.9mm of described blade rootThe 29.0mm at middle part is reduced to the 11mm of described leaf ending again.
In certain embodiments, described blade has two, and described blade is about described oar hoop Central SymmetryAnd around described oar hoop central rotation.
In certain embodiments, the aerofoil profile of described blade is ARA-D.
On the other hand, the invention provides a kind of aircraft, comprise fuselage, be arranged at flying of described fuselageRow control device and screw as above, described flight control assemblies is used for controlling described screwRotation.
Compared with prior art, beneficial effect of the present invention is: this screw passes through at blade radiusDiverse location different blade widths is set, under identical energy consumption, improved the lift of screw,Reduce air drag, increased efficiency; Meanwhile, use the aircraft of this screw can extend flightTime and flying distance, have higher flying quality.
[brief description of the drawings]
In order to be illustrated more clearly in technical scheme of the present invention, below will be to required making in embodimentWith accompanying drawing be briefly described, apparently, the accompanying drawing in the following describes is only of the present inventionSome embodiments, for those of ordinary skill in the art, do not pay creative work beforePut, can also obtain according to these accompanying drawings other accompanying drawing.
Fig. 1 is the view of the horizontal direction of 1 one kinds of screws of the embodiment of the present invention;
Fig. 2 is the view of the vertical direction of 1 one kinds of screws of the embodiment of the present invention;
Fig. 3 is the function relation figure of a-b in 1 one kinds of screws of the embodiment of the present invention;
Fig. 4 is the structural representation of 2 one kinds of screws of the embodiment of the present invention;
Fig. 5 is the structural representation of 3 one kinds of aircraft of the embodiment of the present invention.
[detailed description of the invention]
In order to make object of the present invention, technical scheme and advantage clearer, below in conjunction with accompanying drawingAnd embodiment, the present invention is further elaborated. Should be appreciated that described herein concreteEmbodiment only, in order to explain the present invention, is not intended to limit the present invention.
Embodiment 1
There is large, the inefficient defect of resistance in existing Design of Propeller, cause aircraft in applicationFlying speed little, the boat distance of continuing is short, has had a strong impact on the flying quality of aircraft. Send out based on thisBright a kind of new type propeller design proposed, to reduce resistance, to improve efficiency. For example, incite somebody to action thisWhen the design of invention is used for 9.4 cun of conventional screws, can obtain more existing 9.4 cun of screwsHigher efficiency. But those of ordinary skill in the art should be understood that technical scheme of the present invention is to spiral shellRevolve concrete size, model the no requirement (NR) of oar, 9.4 cun of screws that are also not limited to commonly use, but also suitableFor the screw of other sizes, model.
As shown in Figure 1-2, the embodiment of the present invention has proposed a kind of screw 100, comprise oar hoop 110 andWith at least two blades 120 that described oar hoop 110 is connected, described blade 120 comprise blade root 121,Leaf central part 122 and leaf ending 123, described blade 120 is described blade root with described oar hoop 110 contact positionsPortion 121, the edge of described blade 120 is described leaf ending 123, connects described leaf heel 121 and instituteThe part of stating leaf ending 123 is described leaf central part 122, and described blade 120 width are from described blade rootThe 29.0mm that 121 12.9mm is increased to described leaf central part 122 is reduced to described leaf ending 123 again11mm; Described blade 120 has two, and described blade 120 is about described oar hoop 110 Central SymmetriesAnd around described oar hoop 110 central rotations, the aerofoil profile of described blade 120 is ARA-D; When described bladeOn 120 radial directions, described in any center position, the length at Jiang Gu 110 centers is a position, thisDescribed in position, the width of blade 120 is b, and meets the following conditions: in the time of 0mm≤a≤10mm,11mm < b < 16mm; In the time of 10mm < a≤30mm, 14mm < b < 31mm; Work as 30mmWhen < a≤80mm, 18mm < b < 31mm; In the time of 80mm < a≤100mm, 13mm < b <18mm; In the time of 100mm < a≤120mm, 9mm < b < 16mm.
Furthermore, when the length at described blade 120 distance described Jiang Gu 110 centers is a, instituteThe width of stating blade 120 is b, also meets the following conditions: in the time of a=0mm, and 11mm < b < 14mm;In the time of a=10mm, 14mm < b < 16mm; In the time of a=30mm, 27mm < b < 31mm;In the time of a=50mm, 27mm < b < 31mm; In the time of a=80mm, 18mm < b < 21mm;In the time of a=100mm, 13mm < b < 16mm; In the time of a=120mm, 9mm < b < 12mm.
Preferably, when the length at described blade 120 distance described Jiang Gu 110 centers is a, described oarThe width of leaf 120 is b, also meets the following conditions: in the time of a=0mm, and b=12.9mm; Work as a=When 10mm, b=15.5mm; In the time of a=30mm, b=29.0mm; In the time of a=50mm, b=29.0mm; In the time of a=80mm, b=20.0mm; In the time of a=100mm, b=14.8mm;In the time of a=120mm, b=11.0mm.
As shown in Figure 3, be the function relation figure of a-b in 1 one kinds of screws of the embodiment of the present invention. DescribedWhen the length at blade 120 distance described Jiang Gu 110 centers is a, the width of described blade 120 is b,B=f (a), can set up transverse axis is that a axle, the longitudinal axis are the rectangular coordinate system of b axle. In this rectangular coordinate system,B is the piecewise smooth function about a, in the time of 0mm≤a≤10mm, and b=0.26a+12.9mm,Described b is curved one, by starting point (0,12.9), end point (10,15.5); Work as 10mmWhen < a≤30mm, b=0.675a+8.75mm, described b is curved two, by starting point (10,15.5), end point (30,29); In the time of 30mm < a≤50mm, b=29mm, it is bent that described b isLine three, by starting point (30,29), end point (50,29); In the time of 50mm < a≤80mm,B=﹣ 0.3a+44mm, described b is curved four, by starting point (50,29), end point (80,20); In the time of 80mm < a≤100mm, b=﹣ 0.26a+40.8mm, described b is curved five,By starting point (80,20), end point (100,14.8); In the time of 100mm < a≤120mm, b=﹣ 0.19a+33.8mm, described b is curved six, by starting point (100,14.8), end point(120，11)。
In the above-described embodiment, curve one, curve two, curve three, curve four, curve five andCurve six is non-uniform rational curve. This has further facilitated computer and has removed blade 120 described in matchingWidth b, further facilitated the manufacture of this screw.
The invention provides a kind of screw 100, this screw 100 passes through at blade 120 radius a notCo-located arranges different blades 120 width b, under identical energy consumption, improved screw 100Lift, has reduced air drag, has increased efficiency; And described blade 120 width b are about instituteState blade 120 radius a continually varying functions, improved the stability of screw 100, simultaneously instituteStating blade 120 width b is piecewise function, makes screw 100 have the property of making, and has saved cost.
Embodiment 2
As shown in Figure 4, be the structural representation of 2 one kinds of screws of the embodiment of the present invention. Described blade120 have three, and three blades 120 are centrosymmetric about oar Gu110 center and around described oar hoop110 central rotations.
What deserves to be explained is, the number of a kind of screw 100 blades 120 provided by the invention is not limitTwo or three that provide in the embodiment of the present invention, also can be according to the actual needs of flight, by screwThe number of 100 blades 120 is set to four, five etc.
The invention provides a kind of screw 100, this screw 100 passes through at blade 120 radius a notCo-located arranges different blades 120 width b, under identical energy consumption, improved screw 100Lift, has reduced air drag, has increased efficiency; Three blades are compared the design of two blades, makeObtain screw 100 and there is better balance.
Embodiment 3
As shown in Figure 5, be the structural representation of 3 one kinds of aircraft of the embodiment of the present invention. Described flightDevice comprises: fuselage 200, the flight control assemblies 300 that is arranged at fuselage 200 and spiral as aboveOar 100, flight control assemblies 300 rotates for controlling screw 100. In the present embodiment, fuselage200 comprise that main casing 210 and 220, four horns 220 of four horns that are connected in main casing are crossCross-distribution.
The invention provides a kind of aircraft, described aircraft comprises: fuselage 200, be arranged at fuselage 200Flight control assemblies 300 and screw as above 100, this screw 100 is by bladeThe diverse location of 120 radius a arranges different blades 120 width b, under identical energy consumption, improvesThe lift of screw 100, reduced air drag, increased efficiency; Meanwhile, use this spiralThe aircraft of oar can extend flight time and flying distance, has higher flying quality.
The foregoing is only preferred embodiment of the present invention, not in order to limit the present invention, allAny amendment of doing within the spirit and principles in the present invention, be equal to and replace and improvement etc., all should compriseWithin protection scope of the present invention.
Claims (10)
1. a screw, is characterized in that, comprises oar hoop and at least two of being connected with described oar hoopBlade, when the length at described blade distance described Jiang Gu center is a, the width of described blade is b, andMeet the following conditions:
In the time of 0mm≤a≤10mm, 11mm < b < 16mm;
In the time of 10mm < a≤30mm, 14mm < b < 31mm;
In the time of 30mm < a≤80mm, 18mm < b < 31mm;
In the time of 80mm < a≤100mm, 13mm < b < 18mm;
In the time of 100mm < a≤120mm, 9mm < b < 16mm.
2. screw according to claim 1, is characterized in that, the described oar of described blade distanceWhen the length at hoop center is a, the width of described blade is b, also meets the following conditions:
In the time of a=0mm, 11mm < b < 14mm;
In the time of a=10mm, 14mm < b < 16mm;
In the time of a=30mm, 27mm < b < 31mm;
In the time of a=50mm, 27mm < b < 31mm;
In the time of a=80mm, 18mm < b < 21mm;
In the time of a=100mm, 13mm < b < 16mm;
In the time of a=120mm, 9mm < b < 12mm.
3. screw according to claim 2, is characterized in that, the described oar of described blade distanceWhen the length at hoop center is a, the width of described blade is b, also meets the following conditions:
In the time of a=0mm, b=12.9mm;
In the time of a=10mm, b=15.5mm;
In the time of a=30mm, b=29.0mm;
In the time of a=50mm, b=29.0mm;
In the time of a=80mm, b=20.0mm;
In the time of a=100mm, b=14.8mm;
In the time of a=120mm, b=11.0mm.
4. screw according to claim 3, is characterized in that, the described oar of described blade distanceWhen the length at hoop center is a, the width of described blade is b, and described b is piecewise function, and meet withLower condition:
In the time of 0mm≤a≤10mm, b=0.26a+12.9mm;
In the time of 10mm < a≤30mm, b=0.675a+8.75mm;
In the time of 30mm < a≤50mm, b=29mm;
In the time of 50mm < a≤80mm, b=﹣ 0.3a+44mm;
In the time of 80mm < a≤100mm, b=﹣ 0.26a+40.8mm;
In the time of 100mm < a≤120mm, b=﹣ 0.19a+33.8mm.
5. screw according to claim 4, is characterized in that, the described oar of described blade distanceWhen the length at hoop center is a, the width of described blade is b, and described b is smooth function;
In the time of 0mm≤a≤10mm, described b curved;
In the time of 10mm < a≤30mm, described b curved two;
In the time of 30mm < a≤50mm, described b curved three;
In the time of 50mm < a≤80mm, described b curved four;
In the time of 80mm < a≤100mm, described b curved five;
In the time of 100mm < a≤120mm, described b curved six;
Described curve one, curve two, curve three, curve four, curve five and curve six are non-homogeneousRational curve.
6. screw according to claim 1, is characterized in that, described blade comprise blade root,Leaf central part and leaf ending, described blade and described oar hoop contact position are described blade root, described bladeEdge is described leaf ending, and the part that connects described leaf heel and described leaf ending is described leaf central part.
7. screw according to claim 6, is characterized in that, described blade width is from describedThe 29.0mm that the 12.9mm of blade root is increased to described leaf central part is reduced to described leaf ending again11mm。
8. screw according to claim 1, is characterized in that, described blade has two, instituteState blade about described oar hoop Central Symmetry and around described oar hoop central rotation.
9. screw according to claim 1, is characterized in that, the aerofoil profile of described blade isARA-D。
10. an aircraft, is characterized in that, comprises fuselage, is arranged at the flight control of described fuselageDevice processed and the screw as described in claim 1-9 any one, described flight control assemblies is for controllingDescribed screw rotation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610118950.3A CN105584625B (en) | 2016-03-02 | 2016-03-02 | A kind of propeller and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610118950.3A CN105584625B (en) | 2016-03-02 | 2016-03-02 | A kind of propeller and aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105584625A true CN105584625A (en) | 2016-05-18 |
| CN105584625B CN105584625B (en) | 2018-08-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201610118950.3A Active CN105584625B (en) | 2016-03-02 | 2016-03-02 | A kind of propeller and aircraft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110304245A (en) * | 2019-07-05 | 2019-10-08 | 智飞智能装备科技东台有限公司 | A kind of reinforced propeller of unmanned plane |
| WO2022004387A1 (en) * | 2020-06-30 | 2022-01-06 | ソニーグループ株式会社 | Propeller, flying object, and propeller manufacturing method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5433586A (en) * | 1991-03-27 | 1995-07-18 | Cessna Aircraft Company | Tapered propeller blade design |
| US6361279B1 (en) * | 1997-06-25 | 2002-03-26 | Office National D'etudes Et De Recherches Aerospatiales (Onera) | Blade profile for aircraft rotor and rotor comprising same |
| CN102963522A (en) * | 2012-10-31 | 2013-03-13 | 中国航天空气动力技术研究院 | Near space propeller |
| CN104149968A (en) * | 2014-08-07 | 2014-11-19 | 西北工业大学 | High-efficiency high-altitude propeller with extremely low Reynolds number and high-altitude unmanned aircraft |
| CN104176241A (en) * | 2014-08-07 | 2014-12-03 | 西北工业大学 | High-efficiency pneumatic layout structure of synergistic jet for high-altitude propeller and control method |
-
2016
- 2016-03-02 CN CN201610118950.3A patent/CN105584625B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5433586A (en) * | 1991-03-27 | 1995-07-18 | Cessna Aircraft Company | Tapered propeller blade design |
| US6361279B1 (en) * | 1997-06-25 | 2002-03-26 | Office National D'etudes Et De Recherches Aerospatiales (Onera) | Blade profile for aircraft rotor and rotor comprising same |
| CN102963522A (en) * | 2012-10-31 | 2013-03-13 | 中国航天空气动力技术研究院 | Near space propeller |
| CN104149968A (en) * | 2014-08-07 | 2014-11-19 | 西北工业大学 | High-efficiency high-altitude propeller with extremely low Reynolds number and high-altitude unmanned aircraft |
| CN104176241A (en) * | 2014-08-07 | 2014-12-03 | 西北工业大学 | High-efficiency pneumatic layout structure of synergistic jet for high-altitude propeller and control method |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110304245A (en) * | 2019-07-05 | 2019-10-08 | 智飞智能装备科技东台有限公司 | A kind of reinforced propeller of unmanned plane |
| WO2022004387A1 (en) * | 2020-06-30 | 2022-01-06 | ソニーグループ株式会社 | Propeller, flying object, and propeller manufacturing method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105584625B (en) | 2018-08-07 |
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Address after: 518055 Guangdong city of Shenzhen province Nanshan District Xili Street Xueyuan Road No. 1001 Chi Yuen Building 9 layer B1 Patentee after: Shenzhen daotong intelligent Aviation Technology Co.,Ltd. Address before: 518055 Guangdong city of Shenzhen province Nanshan District Xili Street Xueyuan Road No. 1001 Chi Yuen Building 9 layer B1 Patentee before: AUTEL ROBOTICS Co.,Ltd. |