CN102167152A - Airplane wingtip device with aligned front edge - Google Patents
Airplane wingtip device with aligned front edge Download PDFInfo
- Publication number
- CN102167152A CN102167152A CN2011100594218A CN201110059421A CN102167152A CN 102167152 A CN102167152 A CN 102167152A CN 2011100594218 A CN2011100594218 A CN 2011100594218A CN 201110059421 A CN201110059421 A CN 201110059421A CN 102167152 A CN102167152 A CN 102167152A
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- wing tip
- interconnecting gangway
- wing
- chord length
- aircraft
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- Y02T50/162—
Abstract
The invention provides an airplane wingtip device with an aligned front edge, which comprises a transition part and a wingtip part, wherein the inside end of the transition part is connected with the far end of an airplane wing, the outside end of the transition part is connected with the wingtip part, the wingtip part comprises a plurality of wingtip segments, each wingtip segment comprises a wingtip and a wing root, the wing root of the first wingtip segment is connected with the outside end of the transition part and is aligned with the front edge at the outside end of the transition part, the wing root of the (n+1)th wingtip segment is arranged on the wingtip of the nth wingtip segment, and the wing root chord length of the (n+1)th wingtip segment is less than or equal to the wingtip chord length of the nth wingtip segment, wherein n is more than 0. The wingtip device is step-shaped, so that each wingtip is additionally provided with at least one of discontinuity surfaces, the wingtip vortexes induced by the wingtips are restrained with one another, and the vortex intensity is reduced, therefore the airplane wingtip device achieves a damping effect; and the bending moment incremental quantity of each wing root is less, so that the structural weight of the airplane is reduced, and the influence on the buffeting characteristic is less.
Description
Technical field
The present invention relates to a kind of wing tip device of aircraft wing.
Background technology
Required lift was to lean on the difference of pressure of wing upper and lower surface to produce when aircraft was kept normal flight, because the upper and lower surface pressure differential exists, wing lower surface air can stream upper surface near the wing tip, form the wing tip whirlpool, cause the pressure reduction of wing tip near zone wing upper and lower surface to reduce, thereby the lift that causes this zone to produce reduce.
At the problems referred to above, wing tip winglet (winglet) is set on the aircraft wing wing tip usually again, the main effect of this winglet is not increase under the long prerequisite of wing exhibition, improving the actv. aspect ratio.The two dimensional effects of wing strengthens like this, and induced drag reduces, and lift increases, and 1ift-drag ratio improves.Secondly, the threat to the flivver of trailing flight is reduced in the winglet wing tip whirlpool of can also dissipating.
Yet in a single day aircraft wing has installed the wing tip winglet additional, has increased the weight of wing tip winglet.Wing wing tip structure also can increase some extra weight in order to assemble the wing tip winglet more complicated that can become.The wing tip winglet increases wing wing root moment of flexure and shearing load, also will cause the increase of wing structure weight.And the wing tip winglet designs gets bad, and the stalling characteristic of aircraft, flutter characteristic be variation thereupon also.
In recent decades, each aircraft industry developed country of the world all is being the unremitting effort of development wing tip device, and has designed various dissimilar wing tip devices.
According to the shape of wing tip device, several classes are arranged in the world at present: a kind of is the wing tip sail, or deserves to be called trans wing tip winglet.The wing tip winglet of this style generally has the structure of syllogic, promptly have construction section, arc transition section and straight plate section, this wing tip device has apparent in view crooked fin, in actual applications, the 747-400 type aircraft of Boeing (Boeing) production and the A330 and the A340 series aircraft of space truck (AIRBUS) have all used such wing tip device.When reequiping, this wing tip device can be installed also in addition as Boeing 727, Boeing 757 and Boeing-767 aircraft.
Another kind is a triangle wing tip sail, and the wing tip sail of this form aloft uses among passenger vehicle A320 series, A310 and the A380, also can the say so standard form of Airbus aircraft of such wing tip device.
In addition, newly-designed passenger plane of Boeing such as Boeing 777, Boeing 787, Boeing-747-8 all replace the wing tip sail with special shark fin type wing tip device (raked winglet).
No matter though go up trans wing tip winglet and wing tip sail tangible drag-reduction effect is arranged all, be wing tip winglet or wing tip sail, and the moment of flexure of their wing roots is all bigger, and this has just increased the structural weight of himself, and the flutter characteristic of aircraft is produced certain influence.
Therefore, people wish and can reduce the weight of wing tip device when keeping wing tip device aerodynamic characteristic, reduce because of installing that moment of flexure weight that the wing tip device brought increases and to the influence of flutter characteristic.
Summary of the invention
The object of the present invention is to provide a kind of wing tip device, it can reduce the weight of wing tip device when keeping wing tip device aerodynamic characteristic.
For achieving the above object, the invention provides a kind of aircraft wing tip device, described aircraft wing tip device comprises interconnecting gangway and wing tip portion, the medial end of described interconnecting gangway is connected with the far-end of aircraft wing, the outboard end of described interconnecting gangway is connected with described wing tip portion, wherein, described wing tip portion comprises a plurality of wing tip sections, each wing tip section all comprises wing tip and wing root respectively, the wing root of described first wing tip section is connected with the outboard end of described interconnecting gangway, and align with the leading edge of described interconnecting gangway outboard end, the wing root of described n+1 wing tip section is positioned on the wing tip of n wing tip section, and the wing root chord length of described n+1 wing tip section is in the wing tip chord length of n wing tip section, wherein n＞0.
In the present invention, the top in each wing tip section of aircraft is referred to as " wing tip ", the bottom of each wing tip section of aircraft is referred to as " wing root ".
Especially, the thickness of described n+1 wing tip section is thinner than described n wing tip section.
Especially, the chord length of the wing tip of described each wing tip section is all less than the chord length of its wing root.More particularly, the wing tip section of described each wing tip Duan Douwei chord length convergent.
Especially, the chord length of the wing root of described first wing tip section is smaller or equal to the chord length of the outboard end of described interconnecting gangway.
Especially, the medial end chord length of described interconnecting gangway is greater than the outboard end chord length of described interconnecting gangway.
Especially, described interconnecting gangway is the interconnecting gangway of chord length convergent.
Especially, the top-surface camber of described interconnecting gangway and lower surface camber are smooth surface.
Especially, the smooth connection of far-end of described interconnecting gangway and described aircraft wing.
Especially, described aircraft wing tip device and described aircraft wing are one-body molded.
Especially, the trailing edge line of the trailing edge line of described wing tip portion and described interconnecting gangway alignment.
Especially, the initiating terminal of the interconnecting gangway of described wing tip device be positioned at described wing along exhibition to the long 85%-100% of exhibition.
Especially, the chord length of first section wing root of described wing tip portion is the 10%-100% of described interconnecting gangway outboard end chord length.
Especially, the costa of each wing tip section of described wing tip portion is conic section line segment, line transect, straight line or broken line.More particularly, described conic section line segment is parabola, hyperbola or ellipse.
In addition, the present invention also provides a kind of aircraft wing tip device, described aircraft wing tip device comprises interconnecting gangway and wing tip portion, the medial end of described interconnecting gangway is connected with the far-end of aircraft wing, the outboard end of described interconnecting gangway is connected with described wing tip portion, it is characterized in that, described wing tip portion comprises wing root and wing tip, the wing root of described wing tip portion is connected with the outside end face of described interconnecting gangway, and align with the leading edge of described interconnecting gangway outboard end, the chord length of described wing root is less than the chord length of described interconnecting gangway outside end face.
Especially, the thickness of described wing tip portion is thinner than described interconnecting gangway.
Especially, the wing tip chord length of described wing tip portion is less than its wing root chord length.More particularly, described wing tip portion is the wing tip portion of chord length convergent.
Especially, the medial end chord length of described interconnecting gangway is greater than the outboard end chord length of described interconnecting gangway.More particularly, the described interconnecting gangway interconnecting gangway that is the chord length convergent.
Special than ground, the top-surface camber of described interconnecting gangway and lower surface camber are smooth surface.
Especially, the smooth connection of far-end of described interconnecting gangway and described aircraft wing.
Especially, described aircraft wing tip device and described aircraft wing are one-body molded.
Especially, the trailing edge line of the trailing edge line of described wing tip portion and described interconnecting gangway alignment.
Especially, the initiating terminal of the interconnecting gangway of described wing tip device be positioned at described wing along exhibition to the long 85%-100% of exhibition.
Especially, the chord length of the wing root of described wing tip portion is the 10%-100% of described interconnecting gangway outboard end chord length.
Especially, the costa of described wing tip portion is conic section line segment, line transect, straight line or broken line.More particularly, described conic section line segment is parabola, hyperbola or ellipse.
Because the stepped setting of wing tip device of the present invention, so increased more than one discontinuity surface on its wing tip, thereby the wing tip whirlpool that wing tip is induced suppresses mutually, weakened turbulence rate, thereby reached drag-reduction effect, in addition, wing root moment of flexure increment of the present invention is less, thereby alleviated the structural weight of aircraft, also less to the flutter characteristic influence.
Description of drawings
Fig. 1 is the front view of the winglet embodiment of trailing edge alignment of the present invention;
Fig. 2 is the scheme drawing of another trailing edge alignment winglet of the present invention embodiment;
Fig. 3 is the front view of the winglet embodiment of leading edge alignment of the present invention;
Fig. 4 is the scheme drawing of the winglet embodiment of another leading edge alignment of the present invention;
Fig. 5 is the front view of another winglet of the present invention embodiment, in this embodiment, and in the middle of described stepped wing tip portion is arranged on;
Fig. 6 is the scheme drawing of winglet as shown in Figure 5;
Fig. 7 shows the embodiment of another trailing edge alignment winglet of the present invention, in this embodiment, and the wing root chord length of n+1 wing tip section and the tip chord appearance of n wing tip section etc.
The specific embodiment
As depicted in figs. 1 and 2, in one embodiment of the invention, aircraft wing tip device is the multi-ladder shape, it comprises interconnecting gangway 1 and wing tip portion 2, the medial end of described interconnecting gangway 1 is connected with the far-end of aircraft wing 6, the outboard end of described interconnecting gangway 1 is connected with described wing tip portion 2, and wherein, described wing tip portion comprises a plurality of wing tip sections 3
n, each wing tip section all comprises wing tip 4 respectively
nWith wing root 5
n, described first wing tip section 3
1Wing root 5
1Be connected with the outboard end of described interconnecting gangway 1, and align described n+1 wing tip section 3 with the trailing edge of described interconnecting gangway 1 outboard end
N+1Wing root 5
1Be positioned at n wing tip section 3
nWing tip 4
nOn, and described n+1 wing tip section 3
N+1Wing root 5
1Chord length is less than n wing tip section 3
nWing tip 4
nChord length, wherein n＞0.In addition, as shown in Figure 1, the trailing edge line of described wing tip portion 2 and the alignment of the trailing edge line of described interconnecting gangway 1.
In a preferred embodiment of the invention, described n+1 wing tip portion 3
N+1Thickness be thinner than described n wing tip portion 3
nThe chord length of the wing tip 4 of described each wing tip section 3 is all less than the chord length of its wing root 5, and forms the wing tip section 3 of chord length convergent.Described first wing tip section 3
1Wing root 5
1Chord length smaller or equal to the chord length of the outboard end of described interconnecting gangway 1.The medial end chord length of described interconnecting gangway 1 is greater than the outboard end chord length of described interconnecting gangway 1, and the interconnecting gangway 1 of formation chord length convergent.The top-surface camber of described interconnecting gangway 1 and lower surface camber are smooth surface.The smooth connection of far-end of described interconnecting gangway 1 and described aircraft wing.Described aircraft wing tip device and described aircraft wing are one-body molded.
In addition, in a preferred embodiment of the invention, the initiating terminal of the interconnecting gangway 1 of described wing tip device be positioned at described wing along exhibition to the long 85%-100% of exhibition, first section wing root 5 of described wing tip portion 2
1Chord length be the 10%-100% of the outboard end chord length of described interconnecting gangway 1.
In another embodiment of the present invention, described wing tip device also can be the single-order echelon form, comprise interconnecting gangway 1 and wing tip portion 2, the medial end of described interconnecting gangway 1 is connected with the far-end of aircraft wing 6, the outboard end of described interconnecting gangway 1 is connected with described wing tip portion, it is characterized in that, described wing tip portion 2 comprises wing root 5 and wing tip 4, the wing root 5 of described wing tip portion 2 is connected with the outside end face of described interconnecting gangway 1, and align with the trailing edge of described interconnecting gangway 1 outboard end, and the chord length of described wing root 5 is less than the chord length of described interconnecting gangway 1 outside end face.
In addition, the costa of each wing tip section 3 of described wing tip portion 2 is conic section line segment, line transect, straight line or broken line.More particularly, described conic section line segment is parabola, hyperbola or ellipse.As shown in Figure 1, the leading edge of described in one embodiment of the invention wing tip portion 2 each wing tip section 3 is conic section line segments.
As shown in Figure 3 and Figure 4, in another embodiment of the present invention, described first wing tip section 3
1Wing root 5
1Can also align with the leading edge of described interconnecting gangway 1 outboard end.At this moment, the costa of the costa of described wing tip portion 2 and described interconnecting gangway 1 alignment.
In addition, the trailing edge line of each wing tip section 3 of described wing tip portion 2 is conic section line segment, line transect, straight line or broken line.More particularly, described conic section line segment is parabola, hyperbola or ellipse.And as shown in Figure 3, in one embodiment of the invention, the trailing edge line of each wing tip section 3 of described wing tip portion 2 is straight lines.
In addition, as shown in Figure 5 and Figure 6, in another embodiment of the present invention, described wing tip portion 2 can be arranged on the centre of described interconnecting gangway 1 outboard end, promptly described first wing tip section 3
1Wing root 5
1Neither align, also do not align with the trailing edge of described interconnecting gangway 1 outboard end with the leading edge of described interconnecting gangway 1 outboard end.
At this moment, the costa and the trailing edge line of each wing tip section of described wing tip portion 2 can be respectively conic section line segment, line transect, straight line or broken line, and more particularly, described conic section line segment is parabola, hyperbola or ellipse.Described costa and trailing edge line can adopt same type line segment, also can adopt dissimilar line segments.And as shown in Figure 5 and Figure 6, the trailing edge line of the wing tip section 3 of described in one embodiment of the invention wing tip portion 2 is straight lines, and costa is the conic line segment.
Above-mentionedly can be used for the winglet of single-order scalariform as the described set-up mode of Fig. 3-6, its method to set up and above-mentioned multistage scalariform winglet similar do not repeat them here yet.
In addition, as shown in Figure 7, in one embodiment, n+1 wing tip section 3
N+1Wing root 5
N+1Chord length and n wing tip section 3
nWing tip 4
nChord length equates, in this case, in the junction of each wing tip section chord length is cut, so it still can produce the shape of ladder.
Technology contents of the present invention and technical characterstic disclose as above, yet are appreciated that under creative ideas of the present invention, those skilled in the art can make various changes and modifications to said structure, but all belongs to protection scope of the present invention.The description of the foregoing description is exemplary rather than restrictive, and protection scope of the present invention is determined by claim.
Claims (29)
1. aircraft wing tip device, described aircraft wing tip device comprises interconnecting gangway and wing tip portion, the medial end of described interconnecting gangway is connected with the far-end of aircraft wing, the outboard end of described interconnecting gangway is connected with described wing tip portion, it is characterized in that, described wing tip portion comprises a plurality of wing tip sections, each wing tip section all comprises wing tip and wing root respectively, the wing root of described first wing tip section is connected with the outboard end of described interconnecting gangway, and align with the leading edge of described interconnecting gangway outboard end, the wing root of described n+1 wing tip section is positioned on the wing tip of n wing tip section, and the wing root chord length of described n+1 wing tip section is smaller or equal to the wing tip chord length of n wing tip section, wherein n＞0.
2. aircraft wing tip device as claimed in claim 1 is characterized in that the thickness of described n+1 wing tip section is thinner than described n wing tip section.
3. aircraft wing tip device as claimed in claim 1 is characterized in that, the chord length of the wing tip of described each wing tip section is all less than the chord length of its wing root.
4. aircraft wing tip device as claimed in claim 3 is characterized in that, the wing tip section of described each wing tip Duan Douwei chord length convergent.
5. aircraft wing tip device as claimed in claim 1 is characterized in that the chord length of the wing root of described first wing tip section is smaller or equal to the chord length of the outboard end of described interconnecting gangway.
6. aircraft wing tip device as claimed in claim 1 is characterized in that the medial end chord length of described interconnecting gangway is greater than the outboard end chord length of described interconnecting gangway.
7. aircraft wing tip device as claimed in claim 5 is characterized in that described interconnecting gangway is the interconnecting gangway of chord length convergent.
8. aircraft wing tip device as claimed in claim 1 is characterized in that the top-surface camber of described interconnecting gangway and lower surface camber are smooth surface.
9. aircraft wing tip device as claimed in claim 1 is characterized in that, the smooth connection of far-end of described interconnecting gangway and described aircraft wing.
10. aircraft wing tip device as claimed in claim 1 is characterized in that described aircraft wing tip device and described aircraft wing are one-body molded.
11. aircraft wing tip device as claimed in claim 1 is characterized in that, the costa of described wing tip portion and the alignment of the costa of described interconnecting gangway.
12. aircraft wing tip device as claimed in claim 1 is characterized in that, the initiating terminal of the interconnecting gangway of described wing tip device be positioned at described wing along exhibition to the long 85%-100% of exhibition.
13. aircraft wing tip device as claimed in claim 1 is characterized in that, the chord length of the wing root of first wing tip section of described wing tip portion is the 10%-100% of described interconnecting gangway outboard end chord length.
14. aircraft wing tip device as claimed in claim 1 is characterized in that, the trailing edge line of each wing tip section of described wing tip portion is conic section line segment, line transect, straight line or broken line.
15. aircraft wing tip device as claimed in claim 14 is characterized in that described conic section line segment is parabola, hyperbola or ellipse.
16. aircraft wing tip device, described aircraft wing tip device comprises interconnecting gangway and wing tip portion, the medial end of described interconnecting gangway is connected with the far-end of aircraft wing, the outboard end of described interconnecting gangway is connected with described wing tip portion, it is characterized in that, described wing tip portion comprises wing root and wing tip, the wing root of described wing tip portion is connected with the outside end face of described interconnecting gangway, and described wing tip portion aligns with the leading edge of described interconnecting gangway, and the chord length of described wing root is smaller or equal to the chord length of described interconnecting gangway outside end face.
17. aircraft wing tip device as claimed in claim 16 is characterized in that, the thickness of described wing tip portion is thinner than described interconnecting gangway.
18. aircraft wing tip device as claimed in claim 16 is characterized in that, the wing tip chord length of described wing tip portion is less than its wing root chord length.
19. aircraft wing tip device as claimed in claim 18 is characterized in that, described wing tip portion is the wing tip portion of chord length convergent.
20. aircraft wing tip device as claimed in claim 16 is characterized in that the medial end chord length of described interconnecting gangway is greater than the outboard end chord length of described interconnecting gangway.
21. aircraft wing tip device as claimed in claim 20 is characterized in that described interconnecting gangway is the interconnecting gangway of chord length convergent.
22. aircraft wing tip device as claimed in claim 16 is characterized in that the top-surface camber of described interconnecting gangway and lower surface camber are smooth surface.
23. aircraft wing tip device as claimed in claim 16 is characterized in that, the smooth connection of far-end of described interconnecting gangway and described aircraft wing.
24. aircraft wing tip device as claimed in claim 16 is characterized in that described aircraft wing tip device and described aircraft wing are one-body molded.
25. aircraft wing tip device as claimed in claim 16 is characterized in that, the costa of described wing tip portion and the alignment of the costa of described interconnecting gangway.
26. aircraft wing tip device as claimed in claim 16 is characterized in that, the initiating terminal of the interconnecting gangway of described wing tip device be positioned at described wing along exhibition to the long 85%-100% of exhibition.
27. aircraft wing tip device as claimed in claim 16 is characterized in that, the chord length of the wing root of described wing tip portion is the 10%-100% of described interconnecting gangway outboard end chord length.
28. aircraft wing tip device as claimed in claim 16 is characterized in that, the trailing edge line of described wing tip portion is conic section line segment, line transect, straight line or broken line.
29. aircraft wing tip device as claimed in claim 28 is characterized in that described conic section line segment is parabola, hyperbola or ellipse.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110059421.8A CN102167152B (en) | 2011-03-11 | 2011-03-11 | Airplane wingtip device with aligned front edge |
| EP12757583.5A EP2684797B1 (en) | 2011-03-11 | 2012-03-12 | Airplane wingtip device |
| PCT/CN2012/072188 WO2012122925A1 (en) | 2011-03-11 | 2012-03-12 | Airplane wingtip device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110059421.8A CN102167152B (en) | 2011-03-11 | 2011-03-11 | Airplane wingtip device with aligned front edge |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102167152A true CN102167152A (en) | 2011-08-31 |
| CN102167152B CN102167152B (en) | 2014-04-16 |
Family
ID=44488521
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201110059421.8A Active CN102167152B (en) | 2011-03-11 | 2011-03-11 | Airplane wingtip device with aligned front edge |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102167152B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012122925A1 (en) * | 2011-03-11 | 2012-09-20 | 中国商用飞机有限责任公司 | Airplane wingtip device |
| EP2604516A3 (en) * | 2011-12-13 | 2013-08-14 | Lockheed Martin Corporation | Minimally intrusive wingtip vortex wake mitigation using microvane arrays |
| CN109677587A (en) * | 2019-01-20 | 2019-04-26 | 成都飞机工业（集团）有限责任公司 | A kind of control method of oblique wing aircraft that taking into account high low-speed operations |
| CN110891857A (en) * | 2017-07-12 | 2020-03-17 | 航空器性能公司 | Aircraft wing with at least two winglets |
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| US4205810A (en) * | 1977-12-19 | 1980-06-03 | The Boeing Company | Minimum drag wing configuration for aircraft operating at transonic speeds |
| US6578798B1 (en) * | 2002-04-08 | 2003-06-17 | Faruk Dizdarevic | Airlifting surface division |
| US20040104309A1 (en) * | 2002-06-21 | 2004-06-03 | Darko Segota | Method and system for regulating external fluid flow over an object's surface, and particularly a wing and diffuser |
| CN101228067A (en) * | 2005-07-21 | 2008-07-23 | 波音公司 | Integrated wingtip extensions for jet transport aircraft and other types of aircraft |
| CN101716995A (en) * | 2009-10-12 | 2010-06-02 | 章成谊 | Waved wing and waved surface of object |
| WO2010124877A1 (en) * | 2009-04-30 | 2010-11-04 | Airbus Operations Gmbh | Non-planar wing tip device for wings of aircraft, and wing comprising such a wing tip device |
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2011
- 2011-03-11 CN CN201110059421.8A patent/CN102167152B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4205810A (en) * | 1977-12-19 | 1980-06-03 | The Boeing Company | Minimum drag wing configuration for aircraft operating at transonic speeds |
| US6578798B1 (en) * | 2002-04-08 | 2003-06-17 | Faruk Dizdarevic | Airlifting surface division |
| US20040104309A1 (en) * | 2002-06-21 | 2004-06-03 | Darko Segota | Method and system for regulating external fluid flow over an object's surface, and particularly a wing and diffuser |
| CN101228067A (en) * | 2005-07-21 | 2008-07-23 | 波音公司 | Integrated wingtip extensions for jet transport aircraft and other types of aircraft |
| WO2010124877A1 (en) * | 2009-04-30 | 2010-11-04 | Airbus Operations Gmbh | Non-planar wing tip device for wings of aircraft, and wing comprising such a wing tip device |
| CN101716995A (en) * | 2009-10-12 | 2010-06-02 | 章成谊 | Waved wing and waved surface of object |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012122925A1 (en) * | 2011-03-11 | 2012-09-20 | 中国商用飞机有限责任公司 | Airplane wingtip device |
| EP2604516A3 (en) * | 2011-12-13 | 2013-08-14 | Lockheed Martin Corporation | Minimally intrusive wingtip vortex wake mitigation using microvane arrays |
| US9896192B2 (en) | 2011-12-13 | 2018-02-20 | Lockheed Martin Corroration | Minimally intrusive wingtip vortex wake mitigation using microvane arrays |
| CN110891857A (en) * | 2017-07-12 | 2020-03-17 | 航空器性能公司 | Aircraft wing with at least two winglets |
| CN109677587A (en) * | 2019-01-20 | 2019-04-26 | 成都飞机工业（集团）有限责任公司 | A kind of control method of oblique wing aircraft that taking into account high low-speed operations |
| CN109677587B (en) * | 2019-01-20 | 2022-01-25 | 成都飞机工业（集团）有限责任公司 | Control method of oblique wing aircraft capable of flying at high and low speeds |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102167152B (en) | 2014-04-16 |
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