CN104875873A - Aircraft wing with novel aerodynamic layout and aircraft using same - Google Patents
Aircraft wing with novel aerodynamic layout and aircraft using same Download PDFInfo
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Abstract
The invention provides an aircraft wing with a novel aerodynamic layout and an aircraft using the same. The aircraft comprises a fuselage, and an upper wing section and a lower wing section which are fixedly connected with the fuselage and outwardly extend along spanwise respectively, a wingtip of the upper wing section and the wingtip of the lower wing section are serially and fixedly connected along the spanwise in a staggered manner to form a combined wingtip section so that the upper wing section, the lower wing section and the fuselage form a ditrigon structure, the spanwise is defined as a back-forth direction, the trailing edge of the wingtip at the front side is connected with a leading edge of the wingtip at the rear side. According to the modern close coupling principle, the wingtip at the leading edge can disturb the airflow born by the tailing wingtip, the resistance influence caused by the airflow disturbance to the rear wingtip is lowered, the wingtip vortex produced by the front wingtip is continuously digested by the rear wingtip, the wingtip vortex produced by the front wingtip has lifting force effect on the rear wingtip, and then the effective wingspan for producing the lifting force effect of the combined wing in the triangle structure is enhanced.
Description
Technical field
The present invention relates to a kind of aircraft wing with novel pneumatic layout and the aircraft using this wing.
Background technology
Light-duty or ultra light aircraft not only " human-oriented ", and has wide application.Because this kind of aircraft cost is relatively low, make relatively easy, the lead time is short again, makes this kind of flivver have abundant aerodynamic configuration, and exquisite structure design, has the technology of more novelties to embody than large aircraft.
In order to obtain larger 1ift-drag ratio, aviette adopts the wing structure of high aspect ratio usually, and this wing area is usually larger to make the span of single width wing larger.But the mechanical strength structure efficiency of this too elongated wing is lower, airfoil lift is unfavorable for be delivered to fuselage, and this very thin high aspect ratio wing must have higher intensity to bear huge lift moment of torsion, this makes wing manufacture difficulty very large, and the life-span is not long.The structure of old-fashioned biplane is comparatively simple, it obtains comparatively lift by adopting the two-layer wing arranged up and down, this biplane lift is larger, low-altitude performance is stablized, low-speed operations is effective, easy manipulation, applies comparatively general in the work such as aerial survey, mine locating, aerophotography, aerial spraying agricultural chemicals.But this biplane installs support or pillar usually additional between upper and lower wing, although add wing intensity, but also greatly increase flight resistance, and a pair wing that biplane has more than monoplane also adds additional the induced drag produced by additional tip vortex.
The aircaft configuration of existing employing Lian Yi aerodynamic arrangement as shown in Figure 1 to Figure 3, it comprises the fuselage 300 extended along the longitudinal direction, fuselage 300 is provided with the top wing section 100 and lower wing section 200 that extend along spanwise respectively, on, the outer end wingtip of lower wing section be coupled to each other and on vertical up and down arranged superposed, although the problem having more the double induced drag that a wing causes occurring that conventional biplane brings can be avoided like this, but there is actual problem in use in this associating wing, because when there being object in the scope that a wing is less than chord length on vertical, be bound to disturb the flow field of wing, above-mentioned this upper and lower overlap upper, the interference formed between lower wing section can form chaotic eddy current, the eddy current of this part confusion can balance out the wing section that eddy current surrounds, this part wing section no longer produces effective lift, and then the efficient wing span producing effective lift can be reduced.
Be disclose a kind of Connected wing aircraft in the Chinese utility model patent application specification of CN2122834U at Authorization Notice No., this Connected wing aircraft arranges the end wing at the wing tip of two pairs of wings of traditional biplane, and by the end wing, the wingtip of two-layer wing is connected and fixed, wing tip arranged superposed on vertically of the upper and lower wing of this Connected wing aircraft, top wing, lower wing, fuselage and end plate entirety forms twoport box-structure.The wingtip of upper and lower wing staggers on vertical certain distance by the end wing, reduces the flow field interference each other of upper and lower wing section, meanwhile, and the induced drag utilizing the end wing to reduce wingtip vortex to produce.But the overall resistance of the connection wing layout of this twoport box-structure is comparatively large, reduces 1ift-drag ratio, cause the efficient wing span playing lift effect joining the wing less.Further, the vertical end plate of the connection wing layout larger because side has of above-mentioned this twoport box-structure, lateral stability is poor, when running into larger side to air-flow, easily occurs side direction perturbation accident.
Summary of the invention
The invention provides a kind of aircraft wing, cause more greatly with the overall resistance solving Connected wing aircraft aerodynamic arrangement in prior art the technical matters that the efficient wing span of connection wing layout is less; Meanwhile, the present invention also provides a kind of aircraft using above-mentioned aircraft wing.
The technical scheme of aircraft wing provided by the present invention is: a kind of aircraft wing, comprise respectively along the outward extending upper and lower wing section of spanwise, the wingtip of described top wing section and the wingtip chordwise dislocation tandem of lower wing section are connected and form associating wingtip section to make the fuselage formation ditrigon structure of described upper and lower wing Duan Keyu aircraft, chordwise is defined as fore-and-aft direction, and the trailing edge being positioned at the wingtip of front side connects with the leading edge of the wingtip being positioned at rear side.
The outside along spanwise of described associating wingtip section is fixed with swept-back triangle outer wing, and the chordwise at the wing root place of swept-back triangle outer wing is consistent with the chordwise of the wingtip of described upper and lower wing section.
The outside along spanwise of described associating wingtip section is fixed with connection end plate, and described swept-back triangle outer wing is connected with described wingtip section of combining by connecting end plate.
Described top wing section is positioned at the front of lower wing section, and the wing shapes of described upper and lower wing section adopt following wherein a kind of scheme:
(1) RECTANGULAR WINGS of the chord lengths such as the upper and lower wing section described in is, and the chord length of upper and lower wing section is equal;
(2) the upper and lower wing section described in is wing root chord and grows up in the tapered airfoil of wingtip chord length;
(3) the upper and lower wing section described in is the tapered airfoil that wing root chord length is less than wingtip chord length.
Described top wing section is positioned at the front of lower wing section, top wing section is for along the through through wing section being arranged in back of spanwise, the two ends wingtip along spanwise layout of through wing section is the wingtip of described top wing section, lower wing section comprises two the split air conditioner wing panels being distributed in described fuselage both sides along described spanwise correspondence, the outer end wingtip along spanwise layout of two split air conditioner wing panels is the wingtip of described lower wing section, and the inner wing root along spanwise layout of two split air conditioner wing panels is used for being fixedly connected at described underbelly.
Described through wing section and two split air conditioner wing panels such as to be at the RECTANGULAR WINGS of chord length, and the spacing of the inner wing root of the position that the chordwise of through wing section is corresponding with the inner wing root of two split air conditioner wing panels and described two split air conditioner wing panels is greater than the chord length of described through wing section.
The technical scheme of the aircraft of the above-mentioned wing of use provided by the present invention is: a kind of aircraft, comprise fuselage and to be connected on fuselage and respectively along the outward extending upper and lower wing section of spanwise, the wingtip chordwise dislocation tandem of the wingtip of described top wing section and lower wing section is connected and forms associating wingtip section and form ditrigon structure to make described upper and lower wing section and described fuselage, chordwise is defined as fore-and-aft direction, and the trailing edge being positioned at the wingtip of front side connects with the leading edge of the wingtip being positioned at rear side.
The outside along spanwise of described associating wingtip section is fixed with swept-back triangle outer wing, and the chordwise at the wing root place of swept-back triangle outer wing is consistent with the chordwise of the wingtip of described upper and lower wing section.
Described top wing section is positioned at the front of lower wing section, top wing section is for along the through through wing section being arranged in back of spanwise, the two ends wingtip along spanwise layout of through wing section is the wingtip of described top wing section, lower wing section comprises two the split air conditioner wing panels being distributed in described fuselage both sides along described spanwise correspondence, the outer end wingtip along spanwise layout of two split air conditioner wing panels is the wingtip of described lower wing section, and the inner wing root along spanwise layout of two split air conditioner wing panels is used for being fixedly connected at described underbelly.
The RECTANGULAR WINGS of the chord lengths such as described through wing section and two split air conditioner wing panels are, the inner wing root of through wing section and two split air conditioner wing panels is greater than the chord length of described through wing section in the spacing on vertical up and down.
The invention has the beneficial effects as follows: the wingtip of the top wing section of aircraft wing provided by the present invention and the wingtip chordwise dislocation tandem of lower wing section are connected and form associating wingtip section, like this, on, the fuselage of lower wing section and aircraft just forms ditrigon structure, this ditrigon structure makes wing resistance to overturning better, the disturbance of lateral airflow reduces its impact, and, because the wingtip chordwise dislocation tandem of two wing sections is connected, can know according to " nearly coupled wave theory ", the wingtip being positioned at front side can cause favourable interference to the air-flow born at rear wingtip, the wingtip vortex that preceding wingtip produces to be continued digestion by posterior wingtip, on, two width wingtips of lower wing section only produce the wingtip vortex of an aileron tip, and then reduction induced drag.
Further, swept-back triangle outer wing is fixed with in the outside along spanwise of associating wingtip section, this outer wing effectively can absorb the wingtip vortex that associating wingtip section produces, reduce induced drag, make thisly there is wingtip cascaded structure namely to combine the connection of wingtip section and the wing superposes connection in parallel up and down than existing wing tip and the wing adds the efficient wing span producing lift effect, become the high lift high-strength structure that induced drag is very little, and, the wing root chord length of the leg-of-mutton outer wing in this swept-back is comparatively large, can play larger lift contribution.
Further, by connect end plate by outer wing with combine wingtip section and be fixed together, be convenient to carry out assembling and changing.
Further, top wing section is along the through through wing section being arranged in back of spanwise, can reduce the impact of fuselage on wing flow field so as far as possible, improves the efficiency that wing produces lift.
Further, the inner wing root of through wing section and two split air conditioner wing panels is greater than the chord length of described through wing section in the spacing on vertical up and down, by making both set spacing apart, and then the aerodynamic interference between the lower surface of through wing section and top wing section and the upper surface of two split air conditioner wing panels and lower wing section can be reduced.
Accompanying drawing explanation
Fig. 1 is the structural representation of the aircraft in prior art with associating wing;
Fig. 2 is the birds-eye view of aircraft shown in Fig. 1;
Fig. 3 is the lateral plan of aircraft shown in Fig. 1;
Fig. 4 is the structural representation of a kind of embodiment of aircraft provided by the present invention;
Fig. 5 is the birds-eye view of aircraft shown in Fig. 4;
Fig. 6 is the lateral plan of aircraft shown in Fig. 4;
Fig. 7 is the structural representation of wing in Fig. 4;
Fig. 8 is the birds-eye view of wing shown in Fig. 7;
Fig. 9 is the lateral plan of wing shown in Fig. 7;
Figure 10 is the structural representation of the embodiment 2 of wing provided by the present invention;
Figure 11 is the birds-eye view of wing shown in Figure 10;
Figure 12 is the lateral plan of wing shown in Figure 10;
Figure 13 is the structural representation of the embodiment 3 of wing provided by the present invention;
Figure 14 is the birds-eye view of wing shown in Figure 13;
Figure 15 is the lateral plan of wing shown in Figure 13.
Detailed description of the invention
As shown in Fig. 4 to Fig. 9, a kind of embodiment of aircraft, in this embodiment, aircraft comprises fuselage 1, fuselage 1 is provided with wing, on comprising with wing of the prior art having unlike: the wing in the present embodiment, the associating wing of lower wing section and be arranged on the outer wing 4 in the outside along spanwise of associating wing, top wing section 2 and the lower wing section 3 of associating wing stretch out along spanwise respectively, and top wing section 2 is positioned at the front of lower wing section 3, top wing section 1 is for along the through through wing section being arranged in back of spanwise, the two ends wingtip along spanwise layout of through wing section is the wingtip of described top wing section 2, lower wing section 3 then comprises two the split air conditioner wing panels being distributed in described fuselage both sides along described spanwise correspondence, the inner wing root along spanwise layout of two split air conditioner wing panels is used for being fixedly connected at described underbelly, the outer end wingtip along spanwise layout of two split air conditioner wing panels is the wingtip of described lower wing section 3, in the present embodiment, the wingtip of described top wing section 2 and the wingtip chordwise tandem of lower wing section 3 are connected, and to form associating wingtip section 5 described upper to make, the fuselage of lower wing Duan Keyu aircraft forms ditrigon structure, chordwise is defined as fore-and-aft direction, the trailing edge being positioned at the wingtip of the top wing section 2 of front side connects with the leading edge of the wingtip of the lower wing section 3 being positioned at rear side.
In the present embodiment, outer wing 4 is swept-back triangle outer wing, outer wing 4 is connected in the outside along spanwise of associating wingtip section 5 by connecting end plate, connect end plate and combine wingtip section 5 and be connected, the chordwise at the wing root place of swept-back triangle outer wing is consistent with the chordwise of the wingtip of described upper and lower wing section.Further, outer wing 4 is namely outer wing can be folded up to reduce aircraft and take by folding outer wing space when aircraft is deposited.
In the present embodiment, the RECTANGULAR WINGS of the chord lengths such as the through wing section as top wing section 2 and two split air conditioner wing panels as lower wing section 3 are, and the spacing of the inner wing root of the chordwise of the through wing section position corresponding with the inner wing root of two split air conditioner wing panels and described two split air conditioner wing panels is greater than the chord length of described through wing section.
In order to reduce the aerodynamic interference between the lower surface of top wing section and the upper surface of lower wing section, the inner wing root of through wing section and two split air conditioner wing panels is greater than the chord length of described through wing section in the spacing on vertical up and down.
In the aircraft that the present embodiment provides, upper and lower wing section forms connection wing structure, the formation associating wingtip section and the wingtip chordwise of upper and lower wing section dislocation series connection is connected, the wingtip vortex that the wingtip of such top wing section produces then is intercepted and captured comb stream by the wingtip of lower wing section, theoretical according to modern times nearly Coupling Design, the wingtip vortex that the wingtip being positioned at front side produces to the wingtip generation lift upwards at rear, can improve the efficient wing span for providing lift of this wing structure.And, the wingtip vortex that associating wingtip section produces can absorb by the swept-back triangle outer wing set by the outside of connection wing structure, reduce induced drag, make this connection wing structure with associating wingtip section become the minimum high lift high-strength structure of induced drag.
Aircraft wing in the present embodiment is the embodiment 1 of wing, introduces the aircraft wing embodiment of two kinds of different wing shapes below in addition.
Embodiment 2:
As shown in Figure 10 to Figure 12, the present embodiment provides a kind of aircraft wing, main difference part in the embodiment of this aircraft wing and above-mentioned aircraft is the wing shapes of wing, the chord length that first top wing section 21, first lower wing section 31 of the associating wing in the present embodiment is wing root is greater than the tapered airfoil of the chord length of wingtip, although the first top wing section 21 is also through wing section herein, but the wing root 210 of this first top wing section 21 is positioned at the middle part of through wing section.Now, the wing chord of the associating wingtip section that the outer end wingtip dislocation tandem of upper and lower wing section is connected formed is less than the wing root chord length of top wing section and the wing root chord length sum of lower wing section, the first less outer wing 41 of area mixed again by the connection wing structure of this structure, is applicable to transportation burden.
Embodiment 3:
As shown in FIG. 13 to 15, the present embodiment provides a kind of aircraft wing, main difference part in the embodiment of this aircraft wing and above-mentioned aircraft is the wing shapes of wing, the chord length that second top wing section 22, second lower wing section 32 of the associating wing in the present embodiment is wing root is less than the tapered airfoil of the chord length of wingtip, although the second top wing section 22 is also through wing section herein, but the wing root 220 of the second top wing section 22 is positioned at the middle part of through wing section.Now, the wing chord of the associating wingtip section that the outer end wingtip dislocation tandem of upper and lower wing section is connected formed is greater than the wing root chord length of top wing section and the wing root chord length sum of lower wing section, the second larger outer wing 42 of area mixed again by the connection wing structure of this structure, is applicable to high motor-driven task.
As can be seen from above-described embodiment, mixed the outer wing of suitable area by the wing shapes of the upper and lower wing section of appropriate change again, this Connected wing aircraft can be made to adapt to different performance requriementss.
In above-described embodiment, top wing section is positioned at the front of lower wing section, in other embodiments, also top wing section can be arranged on the rear of lower wing section, as long as make the wingtip chordwise of upper and lower wing section dislocation tandem be connected form associating wingtip section.
In the embodiment of above-mentioned aircraft and wing, outer wing horizontal arrangement, in other embodiments, outer wing also can upwarp.
In above-described embodiment, have in associating wingtip section arranged outside and connect end plate and outer wing, certainly, in other embodiments, also outer wing can be removed, and only retaining associating wingtip section, the wingtip of the lift eddy current contraposition that the wingtip being positioned at front can be utilized equally to produce in rear produces the effective lift chord that lift effect improves whole wing structure.
Claims (10)
1. an aircraft wing, comprise respectively along the outward extending upper and lower wing section of spanwise, it is characterized in that: the wingtip of described top wing section and the wingtip chordwise dislocation tandem of lower wing section are connected and form associating wingtip section to make the fuselage formation ditrigon structure of described upper and lower wing Duan Keyu aircraft, chordwise is defined as fore-and-aft direction, and the trailing edge being positioned at the wingtip of front side connects with the leading edge of the wingtip being positioned at rear side.
2. aircraft wing according to claim 1, it is characterized in that: the outside along spanwise of described associating wingtip section is fixed with swept-back triangle outer wing, the chordwise at the wing root place of swept-back triangle outer wing is consistent with the chordwise of the wingtip of described upper and lower wing section.
3. aircraft wing according to claim 2, is characterized in that: the outside along spanwise of described associating wingtip section is fixed with connection end plate, and described swept-back triangle outer wing is connected with described wingtip section of combining by connecting end plate.
4. the aircraft wing according to claim 1 or 2 or 3, is characterized in that: described top wing section is positioned at the front of lower wing section, and the wing shapes of described upper and lower wing section adopt following wherein a kind of scheme:
(1) RECTANGULAR WINGS of the chord lengths such as the upper and lower wing section described in is, and the chord length of upper and lower wing section is equal;
(2) the upper and lower wing section described in is wing root chord and grows up in the tapered airfoil of wingtip chord length;
(3) the upper and lower wing section described in is the tapered airfoil that wing root chord length is less than wingtip chord length.
5. the aircraft wing according to claim 1 or 2 or 3, it is characterized in that: described top wing section is positioned at the front of lower wing section, top wing section is for along the through through wing section being arranged in back of spanwise, the two ends wingtip along spanwise layout of through wing section is the wingtip of described top wing section, lower wing section comprises two the split air conditioner wing panels being distributed in described fuselage both sides along described spanwise correspondence, the outer end wingtip along spanwise layout of two split air conditioner wing panels is the wingtip of described lower wing section, the inner wing root along spanwise layout of two split air conditioner wing panels is used for being fixedly connected at described underbelly.
6. aircraft wing according to claim 5, it is characterized in that: described through wing section and two split air conditioner wing panels such as to be at the RECTANGULAR WINGS of chord length, the inner wing root of through wing section and two split air conditioner wing panels is greater than the chord length of described through wing section in the spacing on vertical up and down.
7. an aircraft, comprise fuselage and to be connected on fuselage and respectively along the outward extending upper and lower wing section of spanwise, it is characterized in that: the wingtip chordwise dislocation tandem of the wingtip of described top wing section and lower wing section is connected and forms associating wingtip section and form ditrigon structure to make described upper and lower wing section and described fuselage, chordwise is defined as fore-and-aft direction, and the trailing edge being positioned at the wingtip of front side connects with the leading edge of the wingtip being positioned at rear side.
8. aircraft according to claim 7, it is characterized in that: the outside along spanwise of described associating wingtip section is fixed with swept-back triangle outer wing, the chordwise at the wing root place of swept-back triangle outer wing is consistent with the chordwise of the wingtip of described upper and lower wing section.
9. the aircraft according to claim 7 or 8, it is characterized in that: described top wing section is positioned at the front of lower wing section, top wing section is for along the through through wing section being arranged in back of spanwise, the two ends wingtip along spanwise layout of through wing section is the wingtip of described top wing section, lower wing section comprises two the split air conditioner wing panels being distributed in described fuselage both sides along described spanwise correspondence, the outer end wingtip along spanwise layout of two split air conditioner wing panels is the wingtip of described lower wing section, the inner wing root along spanwise layout of two split air conditioner wing panels is used for being fixedly connected at described underbelly.
10. aircraft according to claim 9, it is characterized in that: described through wing section and two split air conditioner wing panels such as to be at the RECTANGULAR WINGS of chord length, the spacing of the inner wing root of the position that the chordwise of through wing section is corresponding with the inner wing root of two split air conditioner wing panels and described two split air conditioner wing panels is greater than the chord length of described through wing section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510225888.3A CN104875873B (en) | 2015-05-06 | 2015-05-06 | A kind of aircraft wing with aerodynamic arrangement and the aircraft using this wing |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510225888.3A CN104875873B (en) | 2015-05-06 | 2015-05-06 | A kind of aircraft wing with aerodynamic arrangement and the aircraft using this wing |
Publications (2)
| Publication Number | Publication Date |
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| CN104875873A true CN104875873A (en) | 2015-09-02 |
| CN104875873B CN104875873B (en) | 2017-03-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510225888.3A Active CN104875873B (en) | 2015-05-06 | 2015-05-06 | A kind of aircraft wing with aerodynamic arrangement and the aircraft using this wing |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108725750A (en) * | 2018-04-28 | 2018-11-02 | 昆明鞘翼科技有限公司 | A method of improving aircraft VTOL using winglet and flight controls |
| CN112455699A (en) * | 2020-11-13 | 2021-03-09 | 中国航空工业集团公司沈阳飞机设计研究所 | High fusion aircraft afterbody |
| CN112607025A (en) * | 2020-12-24 | 2021-04-06 | 中国航空工业集团公司西安飞机设计研究所 | High-aspect-ratio and high-strength double-layer wing solar unmanned aerial vehicle |
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| US20120085858A1 (en) * | 2010-10-11 | 2012-04-12 | Eads Deutschland Gmbh | Aircraft Having a Variable Geometry |
| CN102458988A (en) * | 2009-04-07 | 2012-05-16 | 空中客车西班牙运营有限责任公司 | Aircraft having a lambda-box wing configuration |
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| EP1493660A1 (en) * | 2003-06-30 | 2005-01-05 | The Boeing Company | Efficient wing tip devices and methods for incorporating such devices into existing wing designs |
| CN101254753A (en) * | 2007-02-28 | 2008-09-03 | 西北工业大学 | Solar pilotless plane |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108725750A (en) * | 2018-04-28 | 2018-11-02 | 昆明鞘翼科技有限公司 | A method of improving aircraft VTOL using winglet and flight controls |
| CN112455699A (en) * | 2020-11-13 | 2021-03-09 | 中国航空工业集团公司沈阳飞机设计研究所 | High fusion aircraft afterbody |
| CN112455699B (en) * | 2020-11-13 | 2024-01-02 | 中国航空工业集团公司沈阳飞机设计研究所 | High-fusion aircraft rear body |
| CN112607025A (en) * | 2020-12-24 | 2021-04-06 | 中国航空工业集团公司西安飞机设计研究所 | High-aspect-ratio and high-strength double-layer wing solar unmanned aerial vehicle |
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| Publication number | Publication date |
|---|---|
| CN104875873B (en) | 2017-03-01 |
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