CN104816827A - Low-induced-resistance helicopter rotor wing with sweepback anhedral wingtip - Google Patents
Low-induced-resistance helicopter rotor wing with sweepback anhedral wingtip Download PDFInfo
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- CN104816827A CN104816827A CN201510151522.6A CN201510151522A CN104816827A CN 104816827 A CN104816827 A CN 104816827A CN 201510151522 A CN201510151522 A CN 201510151522A CN 104816827 A CN104816827 A CN 104816827A
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- winglet
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- tip
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Abstract
The invention discloses a low-induced-resistance helicopter rotor wing with a sweepback anhedral wingtip. The low-induced-resistance helicopter rotor is characterized in that a winglet is additionally arranged at one end, far away from the rotating center, namely a wingtip, of a rotor wing, the chordwise length of the root of the winglet is smaller than that of the tip of a main wing, the chord line of the tip of the winglet is lower than the rotary plane of the main wing, namely that the winglet has an anhedral angle, and the winglet twists inwards by a certain angle, so that the front edge of the winglet sweeps backwards. The low-induced-resistance helicopter rotor wing with the sweepback anhedral wingtip, which is provided by the invention, is entirely new, and the most significant innovation point lies in the aerodynamic layout of the wingtip. The rotor wing has the obvious characteristic of low hovering induced resistance, which is helpful for improving the hovering efficiency of helicopters.
Description
Technical field
The present invention is rotor craft rotor pneumatic design, belongs to field of flight vehicle design, low induced drag lifting airscrew anti-under relating to a kind of wing tip sweepback specifically, and it is a kind of lifting airscrew having special wing tip aerodynamic arrangement.
Background technology
Rotor craft, with helicopter and cyclogyro for representative, having can the higher advantage of vertical takeoff and landing, flexible, speed and efficiency.This characteristic makes helicopter be particularly suitable for performing the task such as patrol, supervision in crowded urban district and field with a varied topography.
The pneumatic design core of rotor craft is rotor.Rotor due to own load general comparatively large and have cyclical movement, efficiency generally comparatively Fixed Wing AirVehicle be low, this situation is especially obvious in hovering flight.Therefore, rotor design is always using the hovering efficiency improving helicopter as an important design objective.
Improve the hovering efficiency of helicopter, a mode the simplest is exactly improve the rotor solidity of helicopter.This scheme can realize by increasing rotor chord length or increasing rotor blade number.But this method all has limitation for high-speed helicopter and low-speed helicopter.For high-speed helicopter, excessive rotor solidity causes rotor wetted area to increase, and rotor consumed power rises, and flight efficiency declines; For low-speed helicopter, excessive rotor solidity makes gyroplane rotate speed decline, and air-flow sinuous flow disturbance sensivity increases to external world, and the stationarity of flight declines.Therefore will be improved the hovering efficiency of helicopter by suitable rotor configuration design, wherein the design of wing tip is very important component part.
Summary of the invention
1. the technical matters that will solve
Generally, rotor hovering resistance torque is large, and hovering efficiency is low.This problem cannot by the simple Scalable of rotor or increase rotor blade number and solve.In order to address this problem, low induced drag lifting airscrew anti-under the present invention proposes a kind of wing tip sweepback, it is a kind of brand-new lifting airscrew, and wherein main innovative point is wing tip aerodynamic arrangement form (hereinafter referred to as wing tip).This rotor has obvious low hovering induced drag characteristic, very helpful to the hovering efficiency improving helicopter.
2. the technical scheme adopted
A low induced drag lifting airscrew anti-under wing tip sweepback, it is main is characterised in that:
1) in rotor one end (i.e. wing tip) away from centre of gration, increase a winglet, the tangential length of root of winglet is less than the tangential length in main wing tip, and the winglet tip string of a musical instrument is lower than main wing plane of rotation (namely anti-under winglet), and to intort certain angle.The leading-edge sweep of winglet.
The shape of winglet and position can be described by following parameter: little wing root chord length clr, little wingtip chord length clt, winglet length b, winglet leading edge sweep X, winglet inverted diherdral θ, winglet twist angle
in the present invention, little wing root chord length clr is about main wing wing tip chord length C
30.7 to 0.5 times, the ratio of winglet length b and little wing root chord length clr is about 1.5 to 1, and winglet leading edge sweep X is between 40 ° to 60 °, and winglet inverted diherdral is greater than 20 °, and winglet twist angle is-3 ° to-5 °.In all geometric parameters of winglet, the physical dimension of angle and rotor has nothing to do, and all sizes all grow up to ratio with the tip chord of rotor.
2) part (the basic wing) in rotor except winglet, adopts double trapezoid plane figure form.The chord change rule of this distribution form is: with blade S. A. (propeller hub) for basic point, opens up in 0% ~ 40% length, by C
1linear change is to C
2; Open up in 40% to 100% length, by C
2linear change is to C
3.Wherein, C
2>C
1, C
2>C
3, C
1with C
3there is no particular kind of relationship.The taper ratio of each trapezoidal wing panel is not more than 2.
3) Changing Pattern of basic wing blade twist angle γ is: with blade S. A. (propeller hub) for basic point, opens up in 0% ~ 40% length, by γ
1linear change is to γ
2; Open up in 40% to 100% length, by γ
2linear change is to γ
3.Wherein, γ
1for negative value, namely there is negative twist at root and turn in blade; γ
2, γ
3for on the occasion of, and γ
2> γ
3.General γ
2be not more than 5 °, often get 3 °; γ
1be not less than-3 °, often get-2 °.Rotor cross sectional shape (aerofoil profile) selection strategy is, uses thicker low camber aerofoil profile at root, and open up and to use camber and the moderate aerofoil profile of thickness to 40% position, taper is thin symmetrical airfoil.Aerofoil profile needs to select according to specific needs.
3. beneficial effect
The invention has the advantages that, adopt the rotor blade of this design, compared with the rotor blade of rectangular planar shape, resistance torque can decline and reach 12%, and lift only loses 3%, can think do not have significantly sacrificing.
Accompanying drawing explanation
Fig. 1 is isometric drawing of the present invention;
Fig. 2 is birds-eye view of the present invention;
Fig. 3 is the front elevation of winglet part of the present invention;
Fig. 4 is the birds-eye view of winglet part of the present invention;
Fig. 5 is the direction view of winglet part of the present invention.
In figure, nomenclature is as follows:
B, the basic wing; L, winglet; γ
1, rotary-wing root section twist angle; γ
2, rotor 40% position twist angle; γ
3, rotor taper twist angle; C1, rotary-wing root section chord length; C2, rotor 40% position chord length; C3, rotor taper chord length; Φ, winglet twist angle; θ, winglet inverted diherdral; B, winglet length; X, winglet leading edge sweep; Clr, little wing root chord length;
Clt, little wingtip chord length.
Detailed description of the invention
Below in conjunction with accompanying drawing and embodiment, the present invention is described in further detail.See Fig. 1-Fig. 5,
1. in the present invention, the root chord length (C1) of the basic wing is 56mm, and 40% exhibition is 104mm to chord length (C2), tip chord length (C3) 70mm, length 1175mm, rotary-wing root section twist angle (γ
1) being-2 °, 40% exhibition is to twist angle (γ
2) be 3 °, taper twist angle (γ
3) be 1 °
2. in the present invention, the root aerofoil profile of the basic wing is NACA 67A236, and opening up to 40% to 80% position aerofoil profile is NACA 25013, and the aerofoil profile outside 80% position is NACA 0008.
3. the winglet in the present invention is positioned at rotor tip location, as shown in fig. 1; The geometric parameter of winglet is described as shown in Figures 2 and 3.In this example, the length of little wing root chord length clr is main rotor tip chord length (C
3) 0.57 times, be 40mm; Little wingtip chord length clt is 0.6 times of little wing root chord length, is 24mm; Winglet length b is 1.25 times of little wing root chord length clr, is 50mm.Winglet sweepback angle X is 44 °, and winglet inverted diherdral θ is 30 °, winglet twist angle
for-3 °.
Claims (1)
1. low induced drag lifting airscrew anti-under a wing tip sweepback, it is characterized in that: at rotor away from one end of centre of gration and wing tip, increase a winglet, the tangential length of root of winglet is less than the tangential length in main wing tip, and the winglet tip string of a musical instrument is lower than anti-under main wing plane of rotation and winglet, and to intort certain angle, the leading-edge sweep of winglet;
The shape of winglet and position are described by following parameter: little wing root chord length clr, little wingtip chord length clt, winglet length b, winglet leading edge sweep X, winglet inverted diherdral θ, winglet twist angle
wherein, little wing root chord length clr is main wing wing tip chord length C
30.7 to 0.5 times, the ratio of winglet length b and little wing root chord length clr is 1.5 to 1, and winglet leading edge sweep X is between 40 ° to 60 °, and winglet inverted diherdral is greater than 20 °, and winglet twist angle is-3 ° to-5 °; In all geometric parameters of winglet, the physical dimension of angle and rotor has nothing to do, and all sizes all grow up to ratio with the tip chord of rotor;
Part in rotor except winglet and the basic wing, adopt double trapezoid plane figure form; The chord change rule of this distribution form is: with blade S. A. and propeller hub for basic point, open up in 0% ~ 40% length, by C
1linear change is to C
2; Open up in 40% to 100% length, by C
2linear change is to C
3, wherein, C
2>C
1, C
2>C
3, C
1with C
3do not have particular kind of relationship, the taper ratio of each trapezoidal wing panel is not more than 2;
The Changing Pattern of basis wing blade twist angle γ is: with blade S. A. and propeller hub for basic point, open up in 0% ~ 40% length, by γ
1linear change is to γ
2; Open up in 40% to 100% length, by γ
2linear change is to γ
3; Wherein, γ
1for negative value, namely there is negative twist at root and turn in blade; γ
2, γ
3for on the occasion of, and γ
2> γ
3; General γ
2be not more than 5 °, often get 3 °; γ
1be not less than-3 °, often get-2 °; Rotor cross sectional shape selection strategy is, uses thicker low camber aerofoil profile at root, and open up and to use camber and the moderate aerofoil profile of thickness to 40% position, taper is thin symmetrical airfoil, and aerofoil profile is selected according to specific needs.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510151522.6A CN104816827B (en) | 2015-04-01 | 2015-04-01 | Anti- low induced drag lifting airscrew under a kind of wing tip sweepback |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510151522.6A CN104816827B (en) | 2015-04-01 | 2015-04-01 | Anti- low induced drag lifting airscrew under a kind of wing tip sweepback |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104816827A true CN104816827A (en) | 2015-08-05 |
| CN104816827B CN104816827B (en) | 2017-04-05 |
Family
ID=53727359
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510151522.6A Active CN104816827B (en) | 2015-04-01 | 2015-04-01 | Anti- low induced drag lifting airscrew under a kind of wing tip sweepback |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104816827B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105711833A (en) * | 2016-03-08 | 2016-06-29 | 哈尔滨飞机工业集团有限责任公司 | Aerodynamic configuration of helicopter main blade |
| CN108163192A (en) * | 2017-12-29 | 2018-06-15 | 江苏方阔航空科技有限公司 | A kind of high-efficient low-noise rotor |
| CN110525644A (en) * | 2019-07-12 | 2019-12-03 | 天津曙光天成科技有限公司 | Lifting airscrew blade tip structure, the production method of rotor and blade tip |
| CN110896626A (en) * | 2018-05-25 | 2020-03-20 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
| CN111846199A (en) * | 2019-04-26 | 2020-10-30 | 空客直升机德国有限公司 | Rotorcraft with stabilizer blades |
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| US5332362A (en) * | 1992-04-09 | 1994-07-26 | Societe Anonyme Dite: Eurocopter France | Blade for aircraft rotary wings, with swept-back tip |
| US6142738A (en) * | 1997-12-22 | 2000-11-07 | Eurocopter | Blade for rotary wing aircraft |
| US20050281676A1 (en) * | 2004-06-16 | 2005-12-22 | Egolf Thomas A | Multi-hedral rotary wing |
| US20090148301A1 (en) * | 2007-12-10 | 2009-06-11 | Leahy Kevin P | Main rotor blade with removable tip cap |
| CN104326082A (en) * | 2014-10-20 | 2015-02-04 | 清华大学 | Helicopter and blade thereof |
| 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 |
-
2015
- 2015-04-01 CN CN201510151522.6A patent/CN104816827B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5332362A (en) * | 1992-04-09 | 1994-07-26 | Societe Anonyme Dite: Eurocopter France | Blade for aircraft rotary wings, with swept-back tip |
| US6142738A (en) * | 1997-12-22 | 2000-11-07 | Eurocopter | Blade for rotary wing aircraft |
| US20050281676A1 (en) * | 2004-06-16 | 2005-12-22 | Egolf Thomas A | Multi-hedral rotary wing |
| US20090148301A1 (en) * | 2007-12-10 | 2009-06-11 | Leahy Kevin P | Main rotor blade with removable tip cap |
| CN104326082A (en) * | 2014-10-20 | 2015-02-04 | 清华大学 | Helicopter and blade thereof |
| 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 |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105711833A (en) * | 2016-03-08 | 2016-06-29 | 哈尔滨飞机工业集团有限责任公司 | Aerodynamic configuration of helicopter main blade |
| CN105711833B (en) * | 2016-03-08 | 2018-04-10 | 哈尔滨飞机工业集团有限责任公司 | Helicopter main blade |
| CN108163192A (en) * | 2017-12-29 | 2018-06-15 | 江苏方阔航空科技有限公司 | A kind of high-efficient low-noise rotor |
| CN110896626A (en) * | 2018-05-25 | 2020-03-20 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
| CN111846199A (en) * | 2019-04-26 | 2020-10-30 | 空客直升机德国有限公司 | Rotorcraft with stabilizer blades |
| CN111846199B (en) * | 2019-04-26 | 2024-04-12 | 空客直升机德国有限公司 | Rotorcraft with stabilizing wings |
| CN110525644A (en) * | 2019-07-12 | 2019-12-03 | 天津曙光天成科技有限公司 | Lifting airscrew blade tip structure, the production method of rotor and blade tip |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104816827B (en) | 2017-04-05 |
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