CN106218886A - Many rotorcraft blades and many gyroplanes - Google Patents
Many rotorcraft blades and many gyroplanes Download PDFInfo
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- CN106218886A CN106218886A CN201610687093.9A CN201610687093A CN106218886A CN 106218886 A CN106218886 A CN 106218886A CN 201610687093 A CN201610687093 A CN 201610687093A CN 106218886 A CN106218886 A CN 106218886A
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- 230000010355 oscillation Effects 0.000 description 4
- 230000008901 benefit Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 235000006508 Nelumbo nucifera Nutrition 0.000 description 1
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- 238000010276 construction Methods 0.000 description 1
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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
- 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)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Laminated Bodies (AREA)
Abstract
The invention discloses a kind of many rotorcraft blades and many gyroplanes.Many rotorcraft blades according to the present invention include: the multiple blades being uniformly distributed on joint portion, and the most each blade includes the second sweep part that the first blade-section starting to extend from the end being combined with joint portion and the first blade-section connect and the 3rd sweepback part being connected with the second sweep part.
Description
Technical field
The present invention relates to many rotorcraft design field, particularly relate to a kind of many rotorcraft blades and comprise this many gyroplanes
Many gyroplanes of blade.
Background technology
At present multi-rotor aerocraft due to its VTOL, simple in construction, the characteristic such as be easily maintained and obtaining increasingly
Many application.Rotor blade as main power resources, the quality of its performance for the load carrying behaviour of many rotors, stability and
Operability, noiseproof feature has the biggest impact.The blade design thinking of current many gyroplanes mostlys come from the spiral of aircraft
Oar, but there is certain district in the work operating mode of the blade of many gyroplanes and lifting airscrew, the preposition propeller of fixed wing airplane
Not, the propeller therefore designed based on airplane design experience is extremely difficult to good effect on many gyroplanes, simultaneously because
The blade working speed of many gyroplanes is higher, and the aerodynamic noise thus induced is the highest.
Along with rotor theory is understood in depth by people, the pneumatic design of rotor blade have also been obtained further development.
Based on current gas dynamic theory, in conjunction with wind stick design experiences, for multi-rotor aerocraft, develop series of new
Blade, its main thought is the aerofoil profile of Development of Novel, optimize blade along exhibition to established angle and the distribution of chord length, thus optimize
The aeroperformance of whole blade.But, aerodynamic noise problem still hardly results in improvement.
Therefore, those skilled in the art is devoted to develop a kind of many gyroplanes oar that can be effectively improved aerodynamic noise
Leaf.
Summary of the invention
Because the drawbacks described above of prior art, the technical problem to be solved is to provide one and can effectively change
It is apt to many rotorcraft blades of aerodynamic noise and comprises many gyroplanes of these many rotorcraft blades.
For achieving the above object, the invention provides a kind of many rotorcraft blades to include: be uniformly distributed on joint portion
Multiple blades, the most each blade includes starting the first blade part extended from the end being combined with joint portion
Divide the second sweep part being connected with the first blade-section and the 3rd sweepback part being connected with the second sweep part.
Preferably, first blade-section length on blade bearing of trend is equal to the second sweep part at blade leaf
Three times of length on sheet bearing of trend.
Preferably, first blade-section length on blade bearing of trend is equal to the 3rd sweepback part at blade leaf
Three times of length on sheet bearing of trend.
Preferably, the cross section vertical with blade bearing of trend of the root portion adjacent with joint portion of blade
Thickness more than the thickness in the cross section vertical with blade bearing of trend of the other parts of blade.
Preferably, the cross sectional shape vertical with blade bearing of trend of the mid portion of leaf blade is lower camber line indent
Concaveconvex shape.
Preferably, the cross sectional shape plano-convex exterior shape vertical with blade bearing of trend of the leaf portion of blade.
Preferably, on the blade bearing of trend rearwardly extended from root, the leaf portion of blade with
The thickness in the cross section that blade bearing of trend is vertical becomes larger.
Preferably, on the blade bearing of trend rearwardly extended from root, prolonging with blade of blade
Chord length and the torsional angle of stretching vertical cross section, direction diminish.
For achieving the above object, present invention also offers a kind of many gyroplanes including above-mentioned many rotorcraft blades.
The present invention mainly has the advantage that (1) uses multiple aerofoil profile to merge, except geometric twist, zero liter of each section
The inconsistent torsion angle defined on pneumatic of the angle of attack, optimizes blade performance further；(2) sweepforward and the combination of swept tip
Enable blade to alleviate the impact of compressibility, reduce edge vortex density, reduce the interference of whirlpool/oar simultaneously, change further
It is apt to rotor aeroperformance；(3) when aircraft forward flight speed is the biggest, blade may produce shock stall and separate stall,
This blade can delay the generation of this problem；(4) in terms of aerodynamic noise, this blade can reduce air-flow stream to a certain extent
Form the pressure oscillation of boundary region and wake flow through blade surface thus reduce aerodynamic noise.
Below with reference to accompanying drawing, the technique effect of design, concrete structure and the generation of the present invention is described further, with
It is fully understood from the purpose of the present invention, feature and effect.
Accompanying drawing explanation
Fig. 1 is the floor map of the most rotorcraft blades.
Fig. 2 is the schematic perspective view of the most rotorcraft blades.
Fig. 3 be the most rotorcraft blades along exhibition to cross section aerofoil profile figure.
Fig. 4 be the most rotorcraft blades air-flow along exhibition to schematic diagram.
It should be noted that accompanying drawing is used for illustrating the present invention, and the unrestricted present invention.Note, represent that the accompanying drawing of structure can
Can be not necessarily drawn to scale.Further, in accompanying drawing, same or like element indicates same or like label.
Detailed description of the invention
Fig. 1 is the floor map of the most rotorcraft blades, and Fig. 2 is excellent according to the present invention
Select the schematic perspective view of many rotorcraft blades of embodiment.
As depicted in figs. 1 and 2, many rotorcraft blades of the preferred embodiment of the present invention include: be uniformly distributed in joint portion
Multiple blades 20 on 10, the most each blade 20 include starting from the end being combined with joint portion 10 extending the
The second sweep part 22 that one blade-section 21 is connected with the first blade-section 21 and being connected with the second sweep part 22
3rd sweepback part 23.
Preferably, first blade-section 21 length on blade bearing of trend is equal to the second sweep part 22 at oar
Three times of length on leaf blade bearing of trend.
Preferably, first blade-section 21 length on blade bearing of trend is equal to the 3rd sweepback part 23 at oar
Three times of length on leaf blade bearing of trend.
Preferably, as shown in Figure 3, the root portion 211 adjacent with joint portion 10 of blade 20 with blade leaf
The thickness in the cross section that sheet bearing of trend is vertical is vertical with blade bearing of trend more than the other parts of blade 20
The thickness in cross section.
Preferably, under the cross sectional shape vertical with blade bearing of trend of the mid portion 222 of blade 20 is
The concaveconvex shape of camber line indent.
Preferably, the cross sectional shape plano-convex vertical with blade bearing of trend of the leaf portion 233 of blade 20
Shape.
Such as, root portion 211 includes that a part for the first blade-section 21, mid portion 222 root portion 211 include
The remainder of the first blade-section 21 and the second sweep part 22, leaf portion 233 includes the 3rd sweepback part 23.But
Be, root portion 211, mid portion 222, leaf portion 233 three and first blade-section the 21, second sweep part 22, the
Relation between three sweepback part 23 threes can be other any proper proportion relation.
Preferably, on the blade bearing of trend rearwardly extended from root, the leaf portion of blade 20
The thickness in the cross section vertical with blade bearing of trend becomes larger.
Preferably, on the blade bearing of trend rearwardly extended from root, blade 20 and blade
Chord length and the torsional angle in the cross section that bearing of trend is vertical diminish.
Thus, close to leaf location of root, cross section profile thickness is very big, and it mainly considers it is to strengthen structural strength, is rising
The interruption that power is concentrated, the concavo-convex aerofoil profile of the most lower camber line indent of cross section aerofoil profile, improve lift and lift-drag ratio, at blade
Rear, aerofoil profile gradually transition is plano-convex aerofoil profile and thickness increase, and its main purpose is control load, increases hovering efficiency.
It is preferred that the chord length in cross section and torsional angle also with exhibition to carrying out distribution optimization, before lift is concentrated in
Section, chord length and torsional angle are relatively big, promote lift and bear Main Load, diminish with torsional angle to blade tip, wing chord in the middle rear end of blade, carry
Lotus is controlled, and thus aerodynamic force is more uniform to distribution along whole exhibition, reduces alternation on the basis of ensureing aeroperformance
The load impact on structure.Meanwhile, sweepforward and the combination of sweepback, make air-flow 30 along exhibition to creating component (accompanying drawing 4), delay
Opening up the pressure oscillation to turbulent flow, the reduction of chordwise component also makes the pressure oscillation of wake flow reduce, changing hence for aerodynamic noise
Kind have certain effect.
In another preferred embodiment of the present invention, present invention also offers that a kind of to comprise above-mentioned many rotorcraft blades many
Gyroplane.
The present invention mainly has the advantage that
(1) using multiple aerofoil profile to merge, except geometric twist, the inconsistent of zero liter of angle of attack of each section defines on pneumatic
Torsion angle, optimize blade performance further；
(2) sweepforward enables blade to alleviate the impact of compressibility with the combination of swept tip, reduces edge vortex density,
Reduce the interference of whirlpool/oar simultaneously, further improve rotor aeroperformance；
(3) when aircraft forward flight speed is the biggest, blade may produce shock stall and separate stall, and this blade is permissible
Delay the generation of this problem；
(4) in terms of aerodynamic noise, this blade can reduce airflow passes blade surface to a certain extent and form border
Layer is with the pressure oscillation of wake flow thus reduces aerodynamic noise.
Described above illustrate and describes the preferred embodiments of the present invention, as previously mentioned, it should be understood that the present invention not office
Be limited to form disclosed herein, be not to be taken as the eliminating to other embodiments, and can be used for other combinations various, amendment and
Environment, and can be changed by above-mentioned teaching or the technology of association area or knowledge in invention contemplated scope described herein
Dynamic.And the change that those skilled in the art are carried out and change are without departing from the spirit and scope of the present invention, the most all should be appended by the present invention
In scope of the claims.
Claims (9)
1. rotorcraft blade more than a kind, it is characterised in that including: the multiple blades being uniformly distributed on joint portion, wherein
Each blade includes that the first blade-section starting to extend from the end being combined with joint portion and the first blade-section connect
The second sweep part and the 3rd sweepback part that is connected with the second sweep part.
Many rotorcraft blades the most as claimed in claim 1, it is characterised in that the first blade-section is on blade bearing of trend
Length equal to three times of second sweep part length on blade bearing of trend.
Many rotorcraft blades the most as claimed in claim 1 or 2, it is characterised in that the first blade-section extends at blade
Length on direction is equal to three times of the 3rd sweepback part length on blade bearing of trend.
Many rotorcraft blades the most as claimed in claim 1 or 2, it is characterised in that the root adjacent with joint portion of blade
The thickness in the cross section vertical with blade bearing of trend of portion's part more than blade other parts and blade
The thickness in the cross section that bearing of trend is vertical.
Many rotorcraft blades the most as claimed in claim 1 or 2, it is characterised in that the mid portion of blade and blade
The cross sectional shape that blade bearing of trend is vertical is the concaveconvex shape of lower camber line indent.
Many rotorcraft blades the most as claimed in claim 1 or 2, it is characterised in that the leaf portion of blade and blade
The cross sectional shape plano-convex exterior shape that blade bearing of trend is vertical.
Many rotorcraft blades the most as claimed in claim 1 or 2, it is characterised in that at the blade leaf rearwardly extended from root
On sheet bearing of trend, the thickness in the cross section vertical with blade bearing of trend of the leaf portion of blade becomes larger.
Many rotorcraft blades the most as claimed in claim 1 or 2, it is characterised in that at the blade leaf rearwardly extended from root
On sheet bearing of trend, chord length and the torsional angle in the cross section vertical with blade bearing of trend of blade diminish.
9. many gyroplanes of the many rotorcraft blades included as described in claim 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610687093.9A CN106218886B (en) | 2016-08-18 | 2016-08-18 | Many gyroplanes paddle and many gyroplanes |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610687093.9A CN106218886B (en) | 2016-08-18 | 2016-08-18 | Many gyroplanes paddle and many gyroplanes |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106218886A true CN106218886A (en) | 2016-12-14 |
| CN106218886B CN106218886B (en) | 2024-08-20 |
Family
ID=57553867
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610687093.9A Active CN106218886B (en) | 2016-08-18 | 2016-08-18 | Many gyroplanes paddle and many gyroplanes |
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| Country | Link |
|---|---|
| CN (1) | CN106218886B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109923036A (en) * | 2017-06-30 | 2019-06-21 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and aircraft |
| CN110435877A (en) * | 2019-08-30 | 2019-11-12 | 西安倾云无人机技术有限公司 | A kind of adaptive pneumatic variable-pitch propeller |
| CN111498108A (en) * | 2020-03-30 | 2020-08-07 | 北京理工大学 | High-efficient paddle suitable for high-speed flight of many rotors |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4047841A (en) * | 1974-11-15 | 1977-09-13 | Ab Jarnforadling | Propeller blading for a self-adjusting propeller for boats |
| US20030123973A1 (en) * | 1999-11-11 | 2003-07-03 | Mitsunori Murakami | Propeller type windmill for power generation |
| US20050158175A1 (en) * | 2004-01-21 | 2005-07-21 | Daniele Falchero | Two-sweep rotary wing blade with limited taper ratio |
| US20100272576A1 (en) * | 2005-08-15 | 2010-10-28 | Abe Karem | High performance outboard section for rotor blades |
| CN102198858A (en) * | 2010-03-23 | 2011-09-28 | 尤洛考普特公司 | Rotary wing blade, rotary wing having the same and aircraft |
| CN104477380A (en) * | 2010-12-15 | 2015-04-01 | 空客直升机 | Blade for a helicopter anti-torque device |
| WO2016057107A1 (en) * | 2014-10-11 | 2016-04-14 | Richard Von Berg | Spacer for wind turbine rotor blade |
| CN105775108A (en) * | 2016-03-10 | 2016-07-20 | 中国航天空气动力技术研究院 | Upper air propeller in externally-loaded layout |
| CN206202683U (en) * | 2016-08-18 | 2017-05-31 | 上海未来伙伴机器人有限公司 | Many rotorcraft blades and many gyroplanes |
-
2016
- 2016-08-18 CN CN201610687093.9A patent/CN106218886B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4047841A (en) * | 1974-11-15 | 1977-09-13 | Ab Jarnforadling | Propeller blading for a self-adjusting propeller for boats |
| US20030123973A1 (en) * | 1999-11-11 | 2003-07-03 | Mitsunori Murakami | Propeller type windmill for power generation |
| US20050158175A1 (en) * | 2004-01-21 | 2005-07-21 | Daniele Falchero | Two-sweep rotary wing blade with limited taper ratio |
| US20100272576A1 (en) * | 2005-08-15 | 2010-10-28 | Abe Karem | High performance outboard section for rotor blades |
| CN102198858A (en) * | 2010-03-23 | 2011-09-28 | 尤洛考普特公司 | Rotary wing blade, rotary wing having the same and aircraft |
| US20110236208A1 (en) * | 2010-03-23 | 2011-09-29 | Eurocopter | Rotary wing blade, a rotary wing including such a blade, and an aircraft |
| CN104477380A (en) * | 2010-12-15 | 2015-04-01 | 空客直升机 | Blade for a helicopter anti-torque device |
| WO2016057107A1 (en) * | 2014-10-11 | 2016-04-14 | Richard Von Berg | Spacer for wind turbine rotor blade |
| CN105775108A (en) * | 2016-03-10 | 2016-07-20 | 中国航天空气动力技术研究院 | Upper air propeller in externally-loaded layout |
| CN206202683U (en) * | 2016-08-18 | 2017-05-31 | 上海未来伙伴机器人有限公司 | Many rotorcraft blades and many gyroplanes |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109923036A (en) * | 2017-06-30 | 2019-06-21 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and aircraft |
| CN110435877A (en) * | 2019-08-30 | 2019-11-12 | 西安倾云无人机技术有限公司 | A kind of adaptive pneumatic variable-pitch propeller |
| CN111498108A (en) * | 2020-03-30 | 2020-08-07 | 北京理工大学 | High-efficient paddle suitable for high-speed flight of many rotors |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106218886B (en) | 2024-08-20 |
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