CN111017191A - Winglet - Google Patents
Winglet Download PDFInfo
- Publication number
- CN111017191A CN111017191A CN201911318520.6A CN201911318520A CN111017191A CN 111017191 A CN111017191 A CN 111017191A CN 201911318520 A CN201911318520 A CN 201911318520A CN 111017191 A CN111017191 A CN 111017191A
- Authority
- CN
- China
- Prior art keywords
- winglet
- wing
- foldable
- wing surface
- airplane
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000002411 adverse Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 239000003638 chemical reducing agent Substances 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/32—Air braking surfaces
- B64C9/323—Air braking surfaces associated with wings
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention belongs to the field of aircraft design, and particularly relates to a wingtip winglet. The wingtip winglet comprises a fixed wing surface (2) and a foldable wing surface (4), wherein the fixed wing surface (2) is connected with the foldable wing surface (4) through a first rotating device (3). After the wingtip winglet is additionally arranged, the induced resistance of the airplane is reduced, and the additional lift force is generated, so that the lift-drag ratio of the airplane is increased, and the quick-sailing capability and the long-time stagnation patrol capability of the airplane can be improved.
Description
Technical Field
The invention belongs to the field of aircraft design, and particularly relates to a wingtip winglet.
Background
The wingtip winglet can reduce the induced resistance of the wing, and has very important significance for ship-borne fixed wing early warning patrol aircrafts with emphasized fast sailing capability and long-time stagnation patrol capability. The conventional wingtip winglet adopted by the carrier-based fixed-wing aircraft mainly has the following problems: 1. wingtip winglets are limited in size by the suitability and geometric compatibility of the aircraft and cannot be designed only to optimize the performance of the aircraft; 2. wingtips winglets reduce the induced drag of the wing and are advantageous for aircraft during take-off, climb and cruise phases, but increase drag is required during landing to reduce landing glide distance and bring the aircraft to a stop as quickly as possible, and therefore, the addition of conventional winglets has a detrimental effect on aircraft performance during landing.
Disclosure of Invention
The purpose of the invention is as follows: the wingtip winglet can meet the requirements of suitability and geometric compatibility of a warship aircraft, improve the rapid sailing capability and the long-time air stagnation patrol capability and can not generate adverse effects on the landing performance.
The technical scheme of the invention is as follows:
in a first aspect, there is provided a winglet comprising: the fixed wing surface 2, the foldable wing surface 4, the fixed wing surface 2 and the foldable wing surface 4 are connected through a first rotating device 3.
Alternatively, the foldable airfoil 4 is arranged to be folded inwards by the first turning device 3 to be perpendicular to the plane of symmetry of the fuselage.
Optionally, the first rotation means 3 is a hinge or a lead screw.
Optionally, a speed reduction plate 5 is further included, and the speed reduction plate 5 is arranged on one side of the foldable airfoil 4 close to the body through a second rotating device 6 and can rotate around a vertical shaft.
Optionally, the second rotating means 6 is a hinge or a lead screw.
Optionally, the winglet trailing edge and the wing trailing edge lie in the same plane.
Optionally, the height of the winglet is equal to the wing tip chord length.
Optionally, the winglet area comprises from 1.5% to 3% of the wing area.
Optionally, the winglet has an camber angle of no more than 25 degrees.
The invention has the advantages that:
the invention relates to a wingtip winglet which can be folded inwards and is provided with a speed reducing plate on the outer surface.
After the wingtip winglet is additionally arranged, the induced resistance of the airplane is reduced, and the additional lift force is generated, so that the lift-drag ratio of the airplane is increased, and the quick-sailing capability and the long-time stagnant patrol capability of the airplane can be improved; when the ship surface operates, the winglets can be folded inwards, so that the folding and unfolding envelope lines of the folded wings cannot be influenced, and the space requirement for additionally installing the winglets is increased; no matter the wings are folded downwards and backwards or upwards towards the symmetrical plane of the fuselage, the winglets do not generate geometric interference on the folding appearance, so the appearance size of the winglets is not limited by the adaptability and geometric compatibility of the ship; in addition, the speed reducer on the inner surface of the winglet can be opened during landing, so that the functions of increasing resistance and reducing the landing distance are achieved.
Drawings
Figure 1 is a schematic illustration of the winglet of the invention deployed with the speed reduction plate thereon not open;
figure 2 is a schematic view of the winglet of the invention in a folded condition;
FIG. 3 is a schematic view of the winglet according to the invention in an open position;
FIG. 4 is a schematic view of the installation position of the invention on a ship-based propeller-driven aircraft;
the labels in the figure are: 1. the airplane wing comprises a wing body, 2, a fixed wing surface, 3, a first rotating device, 4, a foldable wing surface, 5, a speed reducing plate, 6 and a second rotating device.
Detailed Description
The present invention is described in further detail below with reference to the attached drawings.
A winglet, comprising: the fixed wing surface 2, the foldable wing surface 4, the fixed wing surface 2 and the foldable wing surface 4 are connected through a first rotating device 3.
Alternatively, the foldable airfoil 4 is arranged to be folded inwards by the first turning device 3 to be perpendicular to the plane of symmetry of the fuselage.
Optionally, the first rotation means 3 is a hinge or a lead screw.
Optionally, a speed reduction plate 5 is further included, and the speed reduction plate 5 is arranged on one side of the foldable airfoil 4 close to the body through a second rotating device 6 and can rotate around a vertical shaft.
Optionally, the second rotating means 6 is a hinge or a lead screw.
Optionally, the winglet trailing edge and the wing trailing edge lie in the same plane.
Optionally, the height of the winglet is equal to the wing tip chord length.
Optionally, the winglet area comprises from 1.5% to 3% of the wing area.
Optionally, the winglet has an camber angle of no more than 25 degrees.
Example (b):
a winglet, comprising: the airplane wing comprises a fixed wing surface 2, a foldable wing surface 4 and a speed reducing plate 5, wherein the fixed wing surface 2 is arranged at the wing tip of a wing 1, the fixed wing surface 2 is connected with the foldable wing surface 4 through a first rotating device 3, and the foldable wing surface 4 can be inwards folded to be perpendicular to the symmetrical plane of a fuselage. The speed reducing plate 5 is arranged on one side, close to the machine body, of the foldable airfoil 4, the speed reducing plate 5 is connected with the foldable airfoil 4 through a second rotating device, and the speed reducing plate 5 can rotate around a vertical shaft.
The trailing edge of the wingtip winglet and the trailing edge of the wing are located in the same plane, and the structural strength of the wingtip winglet can be improved.
The height of the wingtip winglet is equal to the chord length of the wingtip of the wing, so that the aerodynamic characteristics of the wingtip winglet are optimal, and the structural weight cost is minimum.
The winglet area accounts for 1.5-3% of the wing area, and the total efficiency of the winglet can be improved.
The camber angle of the wingtip winglet is not more than 25 degrees, and the wing root bending moment and the rolling moment brought by the wingtip winglet can be reduced.
Claims (9)
1. A winglet, comprising: the fixed wing surface (2) and the foldable wing surface (4) are connected through the first rotating device (3).
2. A winglet according to claim 1, wherein the foldable wings (4) are arranged to be folded inwards by the first turning means (3) to be perpendicular to the plane of symmetry of the fuselage.
3. The winglet according to claim 1, wherein the first rotation device (3) is a hinge or a lead screw.
4. A winglet according to claim 1, further comprising a speed-reducing plate (5), the speed-reducing plate (5) being arranged on the side of the foldable airfoil (4) close to the fuselage by means of second turning means (6) and being rotatable about a vertical axis.
5. The winglet according to claim 1, wherein the second turning device (6) is a hinge or a lead screw.
6. The winglet of claim 1, wherein the winglet trailing edge and the wing trailing edge lie in the same plane.
7. The winglet of claim 1, wherein the winglet has a height equal to the chord length of the wing tip.
8. The winglet of claim 1, wherein the winglet area comprises from 1.5% to 3% of the wing area.
9. The winglet of claim 1, wherein the outboard cant angle of the winglet is no more than 25 degrees.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201911318520.6A CN111017191A (en) | 2019-12-19 | 2019-12-19 | Winglet |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201911318520.6A CN111017191A (en) | 2019-12-19 | 2019-12-19 | Winglet |
Publications (1)
Publication Number | Publication Date |
---|---|
CN111017191A true CN111017191A (en) | 2020-04-17 |
Family
ID=70210607
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN201911318520.6A Pending CN111017191A (en) | 2019-12-19 | 2019-12-19 | Winglet |
Country Status (1)
Country | Link |
---|---|
CN (1) | CN111017191A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112722237A (en) * | 2021-02-20 | 2021-04-30 | 江西经济管理干部学院 | Wingtip winglet of aviation aircraft |
Citations (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5988563A (en) * | 1997-12-30 | 1999-11-23 | Mcdonnell Douglas Corporation | Articulating winglets |
US20040262451A1 (en) * | 2003-06-30 | 2004-12-30 | Mclean James D. | Efficient wing tip devices and methods for incorporating such devices into existing wing designs |
US20110024556A1 (en) * | 2009-08-03 | 2011-02-03 | Airbus Operations (S.A.S) | Aircraft with yaw control by differential drag |
CN103786871A (en) * | 2012-10-30 | 2014-05-14 | 波音公司 | Hinged raked wing tip |
CN205022848U (en) * | 2015-10-10 | 2016-02-10 | 扬州新棱机械制造有限公司 | Wing speed reduction baffle controlling means |
CN105539807A (en) * | 2016-01-15 | 2016-05-04 | 杨汉波 | Deformable airplane with front-rear double propeller and front-rear double wing |
US20170021911A1 (en) * | 2015-07-21 | 2017-01-26 | Airbus Defence and Space GmbH | Coupling device, wing assembly for an aircraft comprising such coupling device and aircraft comprising such wing assembly |
CN205931234U (en) * | 2016-07-07 | 2017-02-08 | 海南航空股份有限公司 | Winglet of wing |
CN106516083A (en) * | 2016-08-01 | 2017-03-22 | 西北农林科技大学 | Winglet rotation device of minitype fixed wing unmanned aerial vehicle |
CN107010202A (en) * | 2017-02-28 | 2017-08-04 | 北京航空航天大学 | A kind of controllable aircraft folds wing spreading device |
CN107933879A (en) * | 2016-10-12 | 2018-04-20 | 空中客车英国运营有限责任公司 | Aircraft wing with aileron |
CN108313266A (en) * | 2018-03-20 | 2018-07-24 | 滨州学院 | A kind of deceleration harden structure for aircraft |
CN208149591U (en) * | 2018-05-15 | 2018-11-27 | 江西冠一通用飞机有限公司 | It is a kind of to realize the motor-driven wing of promotion rolling by can be changed winglet |
-
2019
- 2019-12-19 CN CN201911318520.6A patent/CN111017191A/en active Pending
Patent Citations (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5988563A (en) * | 1997-12-30 | 1999-11-23 | Mcdonnell Douglas Corporation | Articulating winglets |
US20040262451A1 (en) * | 2003-06-30 | 2004-12-30 | Mclean James D. | Efficient wing tip devices and methods for incorporating such devices into existing wing designs |
US20110024556A1 (en) * | 2009-08-03 | 2011-02-03 | Airbus Operations (S.A.S) | Aircraft with yaw control by differential drag |
CN103786871A (en) * | 2012-10-30 | 2014-05-14 | 波音公司 | Hinged raked wing tip |
US20170021911A1 (en) * | 2015-07-21 | 2017-01-26 | Airbus Defence and Space GmbH | Coupling device, wing assembly for an aircraft comprising such coupling device and aircraft comprising such wing assembly |
CN205022848U (en) * | 2015-10-10 | 2016-02-10 | 扬州新棱机械制造有限公司 | Wing speed reduction baffle controlling means |
CN105539807A (en) * | 2016-01-15 | 2016-05-04 | 杨汉波 | Deformable airplane with front-rear double propeller and front-rear double wing |
CN205931234U (en) * | 2016-07-07 | 2017-02-08 | 海南航空股份有限公司 | Winglet of wing |
CN106516083A (en) * | 2016-08-01 | 2017-03-22 | 西北农林科技大学 | Winglet rotation device of minitype fixed wing unmanned aerial vehicle |
CN107933879A (en) * | 2016-10-12 | 2018-04-20 | 空中客车英国运营有限责任公司 | Aircraft wing with aileron |
CN107010202A (en) * | 2017-02-28 | 2017-08-04 | 北京航空航天大学 | A kind of controllable aircraft folds wing spreading device |
CN108313266A (en) * | 2018-03-20 | 2018-07-24 | 滨州学院 | A kind of deceleration harden structure for aircraft |
CN208149591U (en) * | 2018-05-15 | 2018-11-27 | 江西冠一通用飞机有限公司 | It is a kind of to realize the motor-driven wing of promotion rolling by can be changed winglet |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112722237A (en) * | 2021-02-20 | 2021-04-30 | 江西经济管理干部学院 | Wingtip winglet of aviation aircraft |
CN112722237B (en) * | 2021-02-20 | 2023-08-25 | 江西经济管理干部学院 | Aviation aircraft wing tip winglet |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US10625847B2 (en) | Split winglet | |
US9637226B2 (en) | Split winglet system | |
US7971832B2 (en) | Wing tip devices | |
CN110667822B (en) | Rotatable bionical winglet of variable area | |
CN102282070A (en) | Horizontal stabilising surface of an aircraft | |
CN103158856B (en) | Light airscrew flying wing aircraft capable of taking off and landing in short distance | |
CN108750073B (en) | Variable wing leading edge with both subsonic and supersonic aerodynamic performance | |
US11084566B2 (en) | Passively actuated fluid foil | |
CN107804469A (en) | aircraft | |
CN111017191A (en) | Winglet | |
CN207580184U (en) | Aircraft | |
CN107161322A (en) | One kind becomes sweepback STOL Fixed Wing AirVehicle | |
CN202541831U (en) | Small wing of airplane | |
CN105775108A (en) | Upper air propeller in externally-loaded layout | |
CN218877550U (en) | Wing tip winglet structure for improving lift-drag ratio of airplane | |
CN205418071U (en) | Outer formula overall arrangement high altitude screw that carries | |
CN113911334B (en) | Pneumatic layout of tilting duct type aircraft | |
CN204956918U (en) | Unmanned aerial vehicle bispin wing structure | |
GB2577303A (en) | A wing tip device | |
CN214524368U (en) | Lower single-wing aircraft with low coverage coupling guide vane | |
CN219192541U (en) | Bionic eagle wing tip winglet pneumatic structure | |
CN203666981U (en) | Aircraft provided with double rotors | |
CN212501012U (en) | Three-tilting aircraft | |
CN210503149U (en) | Screw power trim tailless unmanned aerial vehicle | |
CN117163280A (en) | Retractable strake wing of wing-free body fusion layout aircraft |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PB01 | Publication | ||
PB01 | Publication | ||
SE01 | Entry into force of request for substantive examination | ||
SE01 | Entry into force of request for substantive examination | ||
RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200417 |
|
RJ01 | Rejection of invention patent application after publication |