CN109533314A - A kind of light-duty unmanned helicopter Rotor Aerodynamics Shape - Google Patents
A kind of light-duty unmanned helicopter Rotor Aerodynamics Shape Download PDFInfo
- Publication number
- CN109533314A CN109533314A CN201811355589.1A CN201811355589A CN109533314A CN 109533314 A CN109533314 A CN 109533314A CN 201811355589 A CN201811355589 A CN 201811355589A CN 109533314 A CN109533314 A CN 109533314A
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- China
- Prior art keywords
- blade
- rotor
- light
- helicopter rotor
- helicopter
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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
-
- 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
Abstract
This application provides a kind of light-duty unmanned helicopter Rotor Aerodynamics Shapes, belong to helicopter pneumatic design technical field.The helicopter rotor blade is 10%-14% to the profile thickness of blade tip from blade rotation center A, the helicopter rotor blade is X to the torsion rate of blade tip from blade rotation center B, wherein A takes 0.24R~0.26R, B takes 0.24R~0.26R, X takes -6.01 °/R~-5.99 °/R, R to form round radius when being rotated by rotor blade.The application promotes rotor while the pulling force ability of rotor can be improved can use the hovering efficiency of weight range section, reduce lifting airscrew required horsepower；The promotion of Hingeless Rotor in Forward Flight lift resistance ratio simultaneously is conducive to improve helicopter maneuverability, while having certain noise reduction effect.
Description
Technical field
The invention belongs to helicopter pneumatic design technical field, in particular to a kind of light-duty unmanned helicopter rotor blade gas
Dynamic shape.
Background technique
For rotor as the distinctive lifting surface of helicopter and control surface, advance is directly related to the performance of platform and advanced
Property, at the same have it is very high can identification and very strong technology it is representative, it has also become one of the key technology of helicopter development is
The emphasis of lifting airscrew designing technique research is carried out both at home and abroad.In the pneumatic conceptual design of rotor, for simultaneously meet rotor hang
Stop and it is preceding fly etc. different flight duty requirements, while consider vibration and aerodynamic noise influence, need to aerofoil profile choose and arrange, turn round
Turn distribution and blade tip region carries out emphasis optimization design, experienced imitative production for manned helicopter, with reference to setting domestic early period
The stages such as meter, autonomous innovation, but the strategic structural that needs in terms of unmanned helicopter rotor aerodynamic arrangement.
Summary of the invention
At least one in order to solve the above-mentioned technical problem, this application provides a kind of light-duty unmanned helicopter rotor blade gas
Dynamic shape, meets the rotor aerodynamic arrangement scheme of light-duty unmanned helicopter multitask demand, the specially described lifting airscrew paddle
Leaf is 10%-14% to the profile thickness of blade tip from blade rotation center A, and the helicopter rotor blade is from distance
At blade rotation center B rise to blade tip torsion rate be X, wherein A take 0.24R~0.26R, B take 0.24R~0.26R, X take-
6.01 °/R~-5.99 °/R, R forms round radius when being rotated by rotor blade.
According at least one embodiment of the application, the profile of the helicopter rotor blade is from blade rotation
It is risen at heart C and blade tip is extended to parabolic, taper ratio is 1:3, and the C is 0.94~0.96R.
According at least one embodiment of the application, the A is 0.25R.
According at least one embodiment of the application, the B is 0.25R.
According at least one embodiment of the application, the helicopter rotor blade is from blade rotation center A
Rising to the profile thickness of blade tip is 12%.
According at least one embodiment of the application, the X is -6 °/R.
According at least one embodiment of the application, a length of 0.06R of the reference chord of the helicopter rotor blade~
0.07R, the reference chord it is a length of from from blade rotation center A to the blade chord length at B.
According at least one embodiment of the application, a length of 0.0622R of reference chord.
According at least one embodiment of the application, the blade length is 2.888 ± 0.01m, and reference chord is a length of
0.195±0.01m。
According at least one embodiment of the application, the C is 0.95R.
The design of the light-duty unmanned helicopter Rotor Aerodynamics Shape of the application, can be improved the same of the pulling force ability of rotor
Shi Tisheng rotor can use the hovering efficiency of weight range section, reduce lifting airscrew required horsepower；Hingeless Rotor in Forward Flight lift resistance ratio simultaneously
Promotion be conducive to improve helicopter maneuverability, while there is certain noise reduction effect, light-duty nobody is straight in certain type for the rotor
Installation application has been carried out on the machine of liter, while having carried out Plain and plateau scientific research is taken a flight test, the results showed that the rotor has good flat
Former and Performance on Plateau.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of a preferred embodiment of the light-duty unmanned helicopter Rotor Aerodynamics Shape of the application.
Fig. 2 is the blade chord length design of a preferred embodiment of the light-duty unmanned helicopter Rotor Aerodynamics Shape of the application
Schematic diagram.
Fig. 3 is that the blade twist rate of a preferred embodiment of the light-duty unmanned helicopter Rotor Aerodynamics Shape of the application is set
Count schematic diagram.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction with the application embodiment
In attached drawing, the technical solution in the application embodiment is further described in more detail.In the accompanying drawings, identical from beginning to end
Or similar label indicates same or similar element or element with the same or similar functions.Described embodiment is
A part of embodiment of the application, rather than whole embodiments.Embodiment below with reference to attached drawing description is to show
Example property, it is intended to for explaining the application, and should not be understood as the limitation to the application.Based on the embodiment in the application,
Every other embodiment obtained by those of ordinary skill in the art without making creative efforts belongs to this
Apply for the range of protection.Presently filed embodiment is described in detail with reference to the accompanying drawing.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the present invention
The limitation of range.
This application provides a kind of light-duty unmanned helicopter Rotor Aerodynamics Shapes, meet light-duty unmanned helicopter more
The rotor aerodynamic arrangement scheme of business demand, the specially described helicopter rotor blade is from blade rotation center A to paddle
The profile thickness of point is 10%-14%, and the helicopter rotor blade is from blade rotation center B to the torsion of blade tip
Rate is X, and wherein A takes 0.24R~0.26R, B to take 0.24R~0.26R, X that -6.01 °/R~-5.99 °/R, R is taken to turn for rotor blade
Round radius is formed when dynamic.
In the embodiment, the helicopter rotor blade is as shown in Figure 1, the helicopter rotor blade starts to include blade root
Platform, blade root changeover portion, airfoil section and three-dimensional blade tip.The profile thickness refers to the maximum gauge tmax and chord length c of blade
The ratio between, embodiment defines the torsion rate of the thickness of blade and blade, the blade with the blade thickness and torsion rate is special
Not Shi Yongyu the light-duty unmanned plane of technical grade, such as blade length mentions while can be improved the pulling force ability of rotor in 3m or so
The hovering efficiency of weight range section can be used by rising rotor, and in the present embodiment, R forms round radius when referring to rotor blade rotation,
May be substantially identical to the length of blade, blade is typically expressed as from 0R section to 1R section at blade tip from blade root, such as
0.24R section indicates at the distance apart from propeller shank 0.24*R along the section that blade described in tangential cutting is formed.
As shown in figure 3, abscissa unit is mm in figure, ordinate unit is degree, which connects
Nearly 3m, starting is -6/3000 to torsion rate at blade tip at 0.24R~0.26R, and about every 500mm is reversed once, the reality of Fig. 3
It applies in example, starting point when windup-degree starts to be reversed to negative value can be located further forward than 0.24R, such as in the position of about 0.5m or so
It sets place and starts opposite direction torsion.Torsion rate design fully considers that light-duty small size blade avoids deforming and excessive load is brought to increase sharply
And the feature of process costs complexity, it is outstanding lifting airscrew can be improved while flying performance before guaranteeing lifting airscrew and not declining
Stop efficiency, reduces the noise level of helicopter.
In some alternative embodiments, the profile of the helicopter rotor blade is from blade rotation center C
It rises and blade tip is extended to parabolic, taper ratio is 1:3, and the C is 0.94~0.96R.
The present embodiment refers to Fig. 2, and unit is mm, the diagrammatically shown blade length about 2.8m in figure, from apart from blade root
2.7m or so starts, and chord length parabolically shrink by form, and sweepback forms blade tip, and taper ratio is 1:3, the i.e. chord length and paddle of blade tip
Ratio of the blde pitch from the chord length at blade root 2.7m is 1:3.Such as in diagram, chord length of the blade at blade root about 2.7m is about
0.2m, and the chord length at blade tip is about 0.06m.
In some alternative embodiments, the A is 0.25R.
In some alternative embodiments, the B is 0.25R.
In some alternative embodiments, the helicopter rotor blade is from blade rotation center A to paddle
The profile thickness of point is 12%.
In some alternative embodiments, the X is -6 °/R.
Aforementioned four embodiment can be combined with each other, and form a more preferably embodiment, the blade configuration design
And Plain and the plateau comprehensive performance of helicopter can be improved in aerofoil profile arrangement, makes the lifting airscrew maximum hovering efficiency be more than
0.73, preceding winged lift resistance ratio reaches 8, when take-off weight is 450kg, the full machine maximum overload nmax=2.0 in sea level.
In some alternative embodiments, a length of 0.06R~0.07R of the reference chord of the helicopter rotor blade, institute
State reference chord it is a length of from from blade rotation center A to the blade chord length at B.
In some alternative embodiments, a length of 0.0622R of the reference chord.Chord length distribution design can delay to go straight up to
Machine advancing blade stall improves helicopter max level speed, while reducing Rotor Aeroacoustic Noise.
In some alternative embodiments, the blade length be 2.888 ± 0.01m, reference chord a length of 0.195 ±
0.01m。
In some alternative embodiments, the C is 0.95R.
Such as in a preferred embodiment, it is 0.0622R from 0.25R section to the chord length of 0.95R section, is cutd open from 0.95R
Face starts leading edge parabola sweepback-rear flat design, taper ratio 1:3 to 1R section.From 0.25R section to 1R section (12%
Thickness airfoil section) torsion rate be -6 °/R；In the present embodiment, rotor blade radius R is 3.135m.
The design of the light-duty unmanned helicopter Rotor Aerodynamics Shape of the application, can be improved the same of the pulling force ability of rotor
Shi Tisheng rotor can use the hovering efficiency of weight range section, reduce lifting airscrew required horsepower；Hingeless Rotor in Forward Flight lift resistance ratio simultaneously
Promotion be conducive to improve helicopter maneuverability, while there is certain noise reduction effect, light-duty nobody is straight in certain type for the rotor
Installation application has been carried out on the machine of liter, while having carried out Plain and plateau scientific research is taken a flight test, the results showed that the rotor has good flat
Former and Performance on Plateau.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (10)
1. a kind of light-duty unmanned helicopter Rotor Aerodynamics Shape, which is characterized in that the helicopter rotor blade is from distance
Being risen at blade rotation center A to the profile thickness of blade tip is 10%~14%, and the helicopter rotor blade is revolved from apart from blade
Turning to rise at the B of center to the torsion rate of blade tip is X, and wherein A takes 0.24R~0.26R, B that 0.24R~0.26R, X is taken to take -6.01 °/R
~-5.99 °/R, R forms round radius when being rotated by rotor blade.
2. light-duty unmanned helicopter Rotor Aerodynamics Shape as described in claim 1, which is characterized in that the helicopter rotation
The profile of wing blade extends to blade tip from blade rotation center C with parabolic, and taper ratio is 1:3, and the C is
0.94~0.96R.
3. light-duty unmanned helicopter Rotor Aerodynamics Shape as described in claim 1, which is characterized in that the A is
0.25R。
4. light-duty unmanned helicopter Rotor Aerodynamics Shape as described in claim 1, which is characterized in that the B is
0.25R。
5. light-duty unmanned helicopter Rotor Aerodynamics Shape as described in claim 1, which is characterized in that the helicopter rotation
Wing blade is 12% to the profile thickness of blade tip from blade rotation center A.
6. light-duty unmanned helicopter Rotor Aerodynamics Shape as described in claim 1, which is characterized in that the X is -6 °/
R。
7. light-duty unmanned helicopter Rotor Aerodynamics Shape as described in claim 1, which is characterized in that the helicopter rotation
A length of 0.06R~the 0.07R of the reference chord of wing blade, the reference chord it is a length of from from blade rotation center A to the blade at B
Chord length.
8. light-duty unmanned helicopter Rotor Aerodynamics Shape as claimed in claim 7, which is characterized in that the benchmark chord length
For 0.0622R.
9. light-duty unmanned helicopter Rotor Aerodynamics Shape as claimed in claim 7, which is characterized in that the blade length
For 2.888 ± 0.01m, a length of 0.195 ± 0.01m of reference chord.
10. light-duty unmanned helicopter Rotor Aerodynamics Shape as claimed in claim 2, which is characterized in that the C is
0.95R。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811355589.1A CN109533314B (en) | 2018-11-14 | 2018-11-14 | Pneumatic appearance of light unmanned helicopter rotor blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811355589.1A CN109533314B (en) | 2018-11-14 | 2018-11-14 | Pneumatic appearance of light unmanned helicopter rotor blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109533314A true CN109533314A (en) | 2019-03-29 |
| CN109533314B CN109533314B (en) | 2021-02-26 |
Family
ID=65847503
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811355589.1A Active CN109533314B (en) | 2018-11-14 | 2018-11-14 | Pneumatic appearance of light unmanned helicopter rotor blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109533314B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111252243A (en) * | 2020-01-21 | 2020-06-09 | 南京航空航天大学 | Helicopter rotor blade down-turning reverse blade tip driving mechanism based on centrifugal mass block |
| CN112173077A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Big front-back sweeping combined helicopter rotor blade |
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| US20140241895A1 (en) * | 2013-02-27 | 2014-08-28 | General Electric Company | Fluid turbine blade and method of providing the same |
| CN106892105A (en) * | 2015-12-21 | 2017-06-27 | 空客直升机 | Its construction be useful in march into the arena flight during acoustics improve and in hovering flight and flight forward performance improvement rotator blade |
| JP2018131038A (en) * | 2017-02-15 | 2018-08-23 | 国立研究開発法人宇宙航空研究開発機構 | Rotor, drone and helicopter |
| CN207826548U (en) * | 2017-12-29 | 2018-09-07 | 江苏方阔航空科技有限公司 | A kind of high-efficient low-noise rotor |
| CN208070014U (en) * | 2018-04-11 | 2018-11-09 | 天津曙光天成科技有限公司 | A kind of multi-rotor unmanned aerial vehicle blade and multi-rotor unmanned aerial vehicle |
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2018
- 2018-11-14 CN CN201811355589.1A patent/CN109533314B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140241895A1 (en) * | 2013-02-27 | 2014-08-28 | General Electric Company | Fluid turbine blade and method of providing the same |
| CN106892105A (en) * | 2015-12-21 | 2017-06-27 | 空客直升机 | Its construction be useful in march into the arena flight during acoustics improve and in hovering flight and flight forward performance improvement rotator blade |
| JP2018131038A (en) * | 2017-02-15 | 2018-08-23 | 国立研究開発法人宇宙航空研究開発機構 | Rotor, drone and helicopter |
| CN207826548U (en) * | 2017-12-29 | 2018-09-07 | 江苏方阔航空科技有限公司 | A kind of high-efficient low-noise rotor |
| CN208070014U (en) * | 2018-04-11 | 2018-11-09 | 天津曙光天成科技有限公司 | A kind of multi-rotor unmanned aerial vehicle blade and multi-rotor unmanned aerial vehicle |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111252243A (en) * | 2020-01-21 | 2020-06-09 | 南京航空航天大学 | Helicopter rotor blade down-turning reverse blade tip driving mechanism based on centrifugal mass block |
| CN111252243B (en) * | 2020-01-21 | 2022-08-05 | 南京航空航天大学 | Helicopter rotor blade down-turning reverse blade tip driving mechanism based on centrifugal mass block |
| CN112173077A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Big front-back sweeping combined helicopter rotor blade |
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| Publication number | Publication date |
|---|---|
| CN109533314B (en) | 2021-02-26 |
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