CN108116656A - A kind of solar energy unmanned plane - Google Patents
A kind of solar energy unmanned plane Download PDFInfo
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- CN108116656A CN108116656A CN201711402232.XA CN201711402232A CN108116656A CN 108116656 A CN108116656 A CN 108116656A CN 201711402232 A CN201711402232 A CN 201711402232A CN 108116656 A CN108116656 A CN 108116656A
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- unmanned plane
- solar energy
- fuselage
- spar
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- 210000004276 hyalin Anatomy 0.000 claims description 7
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- 229920000049 Carbon (fiber) Polymers 0.000 claims description 4
- 239000004743 Polypropylene Substances 0.000 claims description 4
- 239000004917 carbon fiber Substances 0.000 claims description 4
- 238000013016 damping Methods 0.000 claims description 4
- -1 polypropylene Polymers 0.000 claims description 4
- 229920001155 polypropylene Polymers 0.000 claims description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 3
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- 230000035939 shock Effects 0.000 abstract description 4
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- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 7
- 229910052799 carbon Inorganic materials 0.000 description 7
- 239000002131 composite material Substances 0.000 description 7
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
- B64C3/182—Stringers, longerons
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/02—Tailplanes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02S—GENERATION OF ELECTRIC POWER BY CONVERSION OF INFRARED RADIATION, VISIBLE LIGHT OR ULTRAVIOLET LIGHT, e.g. USING PHOTOVOLTAIC [PV] MODULES
- H02S20/00—Supporting structures for PV modules
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Photovoltaic Devices (AREA)
Abstract
The present invention provides a kind of solar energy unmanned plane, including：Fuselage, which is provided with the carrying nacelle and propeller of place apparatus instrument, and propeller is located at the front of fuselage head；Wing, including wing block, spar, stringer, vertical wall, wing block includes several flexible obturators, several wing floors, and wing floor is arranged in the both sides of each flexibility obturator；Spar, vertical wall through flexible obturator and wing floor, are connected with fuselage；Holding tank is equipped in the upper surface of flexible obturator, solar panel is embedded in holding tank；In the present invention, wing is solid, and flexible obturator is combined closely respectively with rigid wing floor, spar and vertical wall, forms interlayer structure, antivibration, strong shock resistance；Solar panel insertion is located on flexible obturator, vibration and impact are absorbed by wing structure, greatly reduce the fragmentation and damage of solar panel, reduces solar panel damage, is conducive to improve the service life of solar panel.
Description
Technical field
The present invention relates to a kind of solar energy unmanned planes.
Background technology
At present, existing unmanned plane is divided into that rotor, fixed-wing, flapping wing etc. are a variety of, wherein the continuation of the journey energy of fixed-wing unmanned plane
Power is relatively strong among several unmanned planes.Conventional small-sized fixed-wing unmanned plane carries the battery or fuel for determining energy, during continuation of the journey
Between when 2 to 4 is small, can not meet demand in executive chairman's voyage, long endurance task；And solar energy unmanned plane with fixed-wing without
It is man-machine to be referred to as basic shape, solar panel is arranged on unmanned plane, by absorbing solar energy and inverted becoming
Electric energy is given UAV system to provide the lasting energy and is supported so that solar energy unmanned plane can accomplish 24 it is small when persistently fly
Row.The continual ability of leaving blank can allow this unmanned plane to perform communication relaying, scout the tasks such as monitoring, patrol, specifically may be used
To complete such as remote wireless network covering, weather forecast, marine resources detection, border patrol, protection zone monitoring task.
Current solar energy unmanned plane, mostly based on wooden structure, wing is internal using traditional rib, girder construction
It is hollow, outer surface cladding heat shrinkage film covering；Mostly using inefficient flexible solar battery piece be adhered to upper surface of the airfoil or
High efficiency non-flexible cells plate is positioned in wing, and is pulled between rib with Kafra fiber beam etc. or timber structure support is in rib
Between.
Chinese patent 201210104242.6, which discloses a kind of small-sized solar unmanned plane, to be included：Fuselage；Wing；It sets respectively
Put the two motors in the left side of the wing and right side front；Two spirals being separately mounted on described two motor
Paddle；The tailplane and vertical tail being connected with fuselage.
Chinese patent 201510853267.X discloses a kind of solar energy integral type unmanned plane wing, including the first fin,
Intermediate fins and the second fin, first fin and the second fin are hingedly set by pivot with intermediate fins, and described first
Solar panel, the solar panel and the first fin, second are mounted in fin, the second fin and intermediate fins
Fin and intermediate fins are integrally formed setting.
The defects of above-mentioned prior art, is：
1st, non-flexible solar panel setting is unreasonable, easily chipping to lead to not use；
2nd, inefficient flexible battery piece has been used, has affected the acquisition efficiency of energy；
3rd, unmanned plane structural strength is low, and poor rigidity, fatiguability, impact resistant capability is weak, short so as to cause service life, reliably
Property is poor, and landing number is limited.
Therefore, how to provide a kind of suitable for non-flexible solar panel, structural strength height, the solar energy of good reliability
Unmanned plane becomes problem to be solved in the industry.
The content of the invention
The defects of for the prior art, the present invention provides a kind of solar energy unmanned planes, and structural strength is high, entire wing
Using solid construction, unmanned plane intensity is improved, extends the service life of unmanned plane, and structure is firm, is hardly damaged；The sun
Energy solar panel is hardly damaged, antivibration, strong shock resistance, and reliability is high.
To achieve these goals, the present invention provides a kind of solar energy unmanned plane, including：
Fuselage, which is provided with carrying nacelle and propeller for place apparatus instrument, and propeller is located at fuselage head
Front；
Wing, including wing block, spar, spar connection fuselage；Spar runs through wing block；The upper surface of wing block is equipped with
Several holding tanks for being used to accommodate solar panel, solar panel are embedded in holding tank；
Empennage, is arranged at afterbody, and empennage includes tailplane and vertical tail.
The present invention is generally fixed-wing aircraft aerodynamic arrangement, head arrangement single motor propeller power；Wing is high mounted wing cloth
Office, based on the straight rectangular wing of high aspect ratio.
Non-flexible solar panel is used in the present invention, adds the acquisition efficiency of energy.
Another kind specific embodiment according to the present invention, empennage is single vertical fin configuration, and tailplane is placed in vertically
After empennage, for horizontal tail leading edge at vertical tail rudder rotating shaft position, tail fin design mode can reduce tailplane other side
To the air-flow screen effect of rudder face.
Another kind specific embodiment according to the present invention, wing block is entity interlayer structure, is filled out including several flexibilities
Fill body；Spar runs through flexible obturator, and holding tank is located at the upper surface of flexible obturator.The solid knot of entire wing in this programme
Structure improves unmanned plane intensity, and structural member quantity is few, and structure is simplified, and utmostly to reduce take-off weight so that unmanned plane
Service life is long, is hardly damaged, and improves the number of landing.Non-flexible solar panel is embedded in the receiving of flexible obturator
In slot, the bottom surface of solar panel and the surface of holding tank fit closely, under the action of external atmosphere pressure, solar cell
Plate is in the case of strong vibration or external impacts, all without departing from holding tank；Flexible obturator can also absorb big absolutely well
Partial vibration and impact energy ensure the normal use of solar panel.
Another kind specific embodiment according to the present invention, wing block further comprise several wing floors：Each flexibility
The both sides of obturator are equipped with wing floor；Spar runs through wing floor.In the present solution, section of flexible obturator and wing floor
Face shape is identical, and each flexibility and forms sandwich at obturator between the wing floor of flexible obturator both sides, ensures
The integrally-built stability of wing and reliability.
Another kind specific embodiment according to the present invention, flexible obturator are fixedly connected with wing floor；Wing floor is consolidated
Surely spar is connected；For example, by way of glue bonding, realize and flexible obturator, wing floor, spar interfix.
Another kind specific embodiment according to the present invention, stringer, vertical wall are additionally provided on wing, and vertical wall corresponds to spar and sets
It puts；Stringer is located at the trailing edge of wing, and the outside of wing is equipped with hyaline membrane, and hyaline membrane is covered in the upper of flexible obturator by stringer
Surface.The effect of hyaline membrane is：Ensureing the smooth and solar panel of outer surface will not come off from upper surface.
Another kind specific embodiment according to the present invention, states flexible obturator and is made of expanded polypropylene material；Fuselage,
Empennage, spar, wing floor, stringer, vertical wall are that carbon fibre composite is made.In the present solution, the main body of entire unmanned plane
Structure is based on carbon fibre composite, such as the full carbon fibers of 3k；Flexible obturator is plastic foam.
Another kind specific embodiment according to the present invention, wing are divided into the inner segment wing, the outer section of wing；The inner segment wing is flattener
The wing, the outer section of wing include flat segments, tilting section；Flat segments are straight wing, and tilting section is equipped with 5 ° -8 ° of the upper counterangle；Preferably,
Tilting section is equipped with 6 ° of the upper counterangle.
Another kind specific embodiment according to the present invention, the length of tilting section account for 1/3 ￣ 1/2 of wing total length；It is excellent
Choosing, the length of tilting section accounts for the 1/3 of wing total length.
Another kind specific embodiment according to the present invention, solar energy unmanned plane are equipped with bracing device, connect including fuselage
Connect end, wing connecting pin, supporting rod；Supporting rod connects fuselage by fuselage connecting pin, and supporting rod is connected by wing connecting pin
Wing.Between wing and fuselage, it is connected by wing with back, while with the mode of diagonal brace by underbelly and the wing wing
It being connected at exhibition, wing connecting pin is located at apart from wing close to the position of fuselage one end 1/3, so as to reinforce complete machine structure intensity,
Reduce the cantilever beam sagging effect of high aspect ratio wing.
Another kind specific embodiment according to the present invention, solar energy unmanned plane are equipped with take-off and landing device, and take-off and landing device is
First three point type take-off and landing device, including undercarriage after nose-gear, two, nose-gear is located at the lower section of fuselage head, two
Undercarriage is relatively arranged below wing afterwards；Take-off and landing device is equipped with damping.Damping is spring damping, whole
Body structure is simplified, and effective loss of weight simultaneously ensures preferable cushioning effect.In the present solution, take-off and landing device is the knot of carbon fibre composite
Structure main body.
The present invention uses carbon fibre composite and expanded polypropylene material as primary structural material, the entire solid knot of wing
Structure while the intensity of unmanned plane is improved, ensure that whole weight, reduces the influence that vibration is brought, extends unmanned plane
Service life.
In the present invention, solar panel is mounted in the holding tank of flexible obturator, and flexible obturator selects foam material
Material, light flexible are easily worked, and have certain Anti-pull-press ability.Before assembling, added according to the size of solar panel
Work goes out flexible obturator, and processes the holding tank of corresponding solar panel in the upper surface of flexible obturator.When mounted,
Wing is whole first to complete assembling, and solar panel tandem is placed on after separately welding in the holding tank of flexible obturator, is squeezed
Sunny energy solar panel and the air for accommodating rooved face, fit closely it；The advantages of this arrangement are as follows foam pole can be utilized
Overwhelming majority vibration and impact energy are absorbed and dissipated by strong vibration absorption ability；Foam has good elastic property and tension, resists
Pressure energy power can ensure that influence when wing is deformed to solar panel is minimum；Foam and solar panel are fitted closely,
So that solar panel is difficult to depart from from foam carrier；When placing the battery panel, without using rigid connection, (such as glue glues
Mode on wing etc.) so that solar panel can carry out small size planar movement on carrier, to adapt to wing
The inevitable deformation occurred, so as to which wing deformation be avoided to cause the situation of the direct embrittlement of solar panel.
The section of flexible obturator between wing floor is processed into the shape of wing floor in the present invention, it is poly- using foaming
Propylene material light flexible and the characteristics of be easily worked, using it as carrier, is embedded into receiving by non-flexible solar panel
Slot, solar panel and holding tank fit closely, and under external atmosphere pressure effect, solar panel is in strong vibration or external impacts
In the case of, all without departing from holding tank；Expanded polypropylene material can be very good to absorb vibration and the impact energy of the overwhelming majority
Amount ensures the normal use of solar panel.
Compared with prior art, the invention has the beneficial effects that：
1st, empennage is single vertical fin configuration, and after tailplane is placed in vertical tail, and the leading edge of tailplane is located at vertical
At straight tail rudder rotating shaft position, which can reduce air-flow screen effect of the tailplane to rudder surface；
2nd, wing is solid to be combined closely by rigid girt strip structure and flexible obturator, formation interlayer structure, antivibration,
Strong shock resistance, it is synchronous to improve unmanned plane strength and stiffness, enhance body compages ability, extend making for unmanned plane
With the service life, and structure is firm, and landing is hardly damaged；Integral structure component quantity is few, easy to produce, installation；
3rd, efficient and be hardly damaged using non-flexible solar panel, cruising time is long；
4th, solar panel is embedded on flexible obturator, vibration and impact is absorbed by wing structure, greatly reduced
The fragmentation and damage of solar panel are conducive to improve the service life of solar panel.
The present invention is described in further detail below in conjunction with the accompanying drawings.
Description of the drawings
Fig. 1 is the overall structure diagram of the solar energy unmanned plane of embodiment 1；
Fig. 2 is the top view of solar energy unmanned plane；
Fig. 3 is the front view of solar energy unmanned plane；
Fig. 4 is the partial schematic diagram of Fig. 1.
Specific embodiment
Embodiment 1
A kind of solar energy unmanned plane is present embodiments provided, as shown in Figs 1-4, including：Fuselage 1, wing 2, empennage 3,
Propeller 4, bracing device 5, take-off and landing device 6.
Wherein, fuselage 1 is made of carbon fibre composite, is column structure, is equipped with to place in the lower section of fuselage 1
The carrying platform 11 of external equipment；Propeller 4 is single motor propeller, is located at the front end of fuselage 1.
Wing 2 includes wing block 21, spar 22, vertical wall 23, stringer 29, and wing block 21 includes wing floor 24 and foam is filled out
Body 25 is filled, the both sides of each foamed filler body 25 are equipped with wing floor 24, wherein, spar 22 runs through wing shaft of rib 24 and foam
Obturator 25, the position that foamed filler body 25, wing floor 24, spar 22, stringer 29 are connected are bonded by glue；It is steeping
The upper surface of foam obturator 25 is equipped with to accommodate the holding tank 26 of solar panel, and the cell wall of holding tank 26 adds for integral type
The foam rib 261 that work forms；In solar panel insertion holding tank 26；The outside of wing 2 is equipped with hyaline membrane (in figure not
Show), hyaline membrane is covered in the upper surface of foamed filler body 25 by stringer 29 and foam rib 261.
Empennage 3 is connected with the rear end of fuselage 1, including tailplane 31 and vertical tail 32；Empennage 3 is single vertical tail
Configuration, and after tailplane 31 is placed in the 32 of vertical tail, 31 leading edge of tailplane is located at 32 rudder shaft of vertical tail
At position, the structure of the empennage 3 can reduce air-flow screen effect of the tailplane 31 to rudder surface.
Bracing device 5 includes fuselage connecting pin 51, wing connecting pin 52, supporting rod 53；Supporting rod 53 is connected by fuselage
51 connection fuselage of end, supporting rod 53 connect wing 2 by wing connecting pin 52, and wing 2 is connected with 1 top of fuselage, passes through support
Bar 53 by the lower end of fuselage 1 with connected at 2 span of wing, wing connecting pin 52 is located at apart from wing 2 close to one end of fuselage 1 1/
3 position.
Take-off and landing device 6 is bikini take-off and landing device, is the main structure body of carbon fibre composite；Take-off and landing device 6 includes
Undercarriage 62 after nose-gear 61, two, nose-gear 61 are located at 1 head of fuselage, and undercarriage 62 is relatively arranged on machine after two
2 lower section of the wing；Take-off and landing device 6 is equipped with spring shock absorption mechanism (not shown).
In the present embodiment, wing 2 is shoulder-wing configuration, and using the straight rectangular wing of high aspect ratio, wing 2 divides for the inner segment wing
27 and the outer section of wing 28, the outer section of wing 28 includes flat segments 281 and tilting section 282, wherein, the inner segment wing 27 is straight wing, flat segments
281 be straight wing, and the length of tilting section 282 is 2 times of 281 length of flat segments, and the length of tilting section 282 accounts for wing 2 always
The 1/3 of length；Tilting section 282 is equipped with 6 ° of the upper counterangle.
In the present embodiment, based on carbon fibre composite and foamed material, other plane institution movements such as wing floor by
Carbon fiber sheet is process, and it is carbon fiber pipe to indulge wall and fuselage sections.Loss of weight engraved structure is equipped on wing floor,
On the premise of proof strength rigidity, excess stock is removed；The both sides of foamed filler body are equipped with wing floor, and foam-filled
Body is fixed with wing floor by bonding mode, spar pass through wing floor and foamed filler body, and with foamed filler body, wing
Floor is fixed by bonding mode, and spar, vertical wall, wing floor, foamed filler body are fixedly connected, and ensure that wing fracture strength
With bending resistance torsional rigidity.
Although the present invention is disclosed above with preferred embodiment, the scope that the present invention is implemented is not limited to.Any
The those of ordinary skill in field in the invention scope for not departing from the present invention, improves when can make a little, i.e., every according to this hair
Bright done equal improvement, should be the scope of the present invention and is covered.
Claims (10)
1. a kind of solar energy unmanned plane, which is characterized in that the solar energy unmanned plane includes：
Fuselage, which is provided with carrying nacelle and propeller for place apparatus instrument, and the propeller is located at the fuselage head
The front in portion；
Wing, including wing block, spar, the spar connects the fuselage；The spar runs through the wing block；The machine
The upper surface of wing is equipped with several holding tanks for being used to accommodate solar panel, and the solar panel is embedded in the receiving
In slot；
Empennage, is arranged at the afterbody, and the empennage includes tailplane and vertical tail.
2. solar energy unmanned plane as described in claim 1, which is characterized in that the wing block is entity interlayer structure, is wrapped
Include several flexible obturators；For the spar through the flexible obturator, the holding tank is located at the upper of the flexible obturator
Surface.
3. solar energy unmanned plane as claimed in claim 2, which is characterized in that the wing block further comprises several wing ribs
Plate：
The both sides of each flexible obturator are equipped with the wing floor；The spar runs through the wing floor.
4. solar energy unmanned plane as claimed in claim 3, which is characterized in that the flexibility obturator is fixedly connected with the wing
Floor；The wing floor is fixedly connected with the spar.
5. solar energy unmanned plane as claimed in claim 3, which is characterized in that stringer, vertical wall are additionally provided on the wing, it is described
Vertical wall corresponds to the spar and sets；The stringer is located at the trailing edge of the wing, and the outside of the wing is equipped with hyaline membrane, described
Hyaline membrane is covered in the upper surface of the flexible obturator by the stringer.
6. solar energy unmanned plane as claimed in claim 5, which is characterized in that the flexibility obturator is expanded polypropylene material
It is made；The fuselage, the empennage, the spar, the wing floor, the stringer, the vertical wall are that carbon fiber is compound
Material is made.
7. solar energy unmanned plane as described in claim 1, which is characterized in that the wing is divided into the inner segment wing, the outer section of wing；It is described
The inner segment wing is straight wing, and the outer section of wing includes flat segments, tilting section；The flat segments be straight wing, the tilting section
Equipped with 5 ° -8 ° of the upper counterangle.
8. solar energy unmanned plane as claimed in claim 7, which is characterized in that the length of the tilting section accounts for the wing overall length
The 1/3~1/2 of degree.
9. solar energy unmanned plane as described in claim 1, which is characterized in that the solar energy unmanned plane is equipped with bracing device,
It includes fuselage connecting pin, wing connecting pin, supporting rod；The supporting rod connects the fuselage by the fuselage connecting pin,
The supporting rod connects the wing by the wing connecting pin.
10. solar energy unmanned plane as described in claim 1, which is characterized in that the solar energy unmanned plane is equipped with the dress that rises and falls
It puts, the take-off and landing device is first three point type take-off and landing device, and including undercarriage after nose-gear, two, the nose-gear is set
In the lower section of the fuselage head, two rear undercarriages are relatively arranged below the wing；It is set on the take-off and landing device
There is damping.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711402232.XA CN108116656A (en) | 2017-12-20 | 2017-12-20 | A kind of solar energy unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711402232.XA CN108116656A (en) | 2017-12-20 | 2017-12-20 | A kind of solar energy unmanned plane |
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| Publication Number | Publication Date |
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| CN108116656A true CN108116656A (en) | 2018-06-05 |
Family
ID=62231022
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| CN201711402232.XA Pending CN108116656A (en) | 2017-12-20 | 2017-12-20 | A kind of solar energy unmanned plane |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110576963A (en) * | 2019-09-19 | 2019-12-17 | 西北工业大学 | Solar unmanned aerial vehicle wing structure |
| CN111907087A (en) * | 2020-07-10 | 2020-11-10 | 航天特种材料及工艺技术研究所 | Forming assembly tool and manufacturing method for composite unmanned aerial vehicle horizontal tail |
| CN112061373A (en) * | 2019-06-11 | 2020-12-11 | 波音公司 | Energy subsystem integrated into a structural component of an aircraft |
| CN112644686A (en) * | 2020-12-25 | 2021-04-13 | 中国航天空气动力技术研究院 | Tandem wing overall arrangement solar energy unmanned aerial vehicle |
| CN113788143A (en) * | 2021-11-15 | 2021-12-14 | 中国航天空气动力技术研究院 | Tail sitting type vertical take-off and landing solar unmanned aerial vehicle |
| CN114408159A (en) * | 2021-12-08 | 2022-04-29 | 中航西安飞机工业集团股份有限公司 | Rapid connecting structure and connecting method for tail wing of unmanned aerial vehicle |
| CN117516538A (en) * | 2023-11-08 | 2024-02-06 | 广东翼景信息科技有限公司 | Unmanned aerial vehicle route planning method, unmanned aerial vehicle route planning device, computing equipment and storage medium |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102774490A (en) * | 2012-04-10 | 2012-11-14 | 北京航空航天大学 | Novel long-endurance solar unmanned aerial vehicle |
| KR20130059022A (en) * | 2011-11-28 | 2013-06-05 | 한국과학기술연구원 | Wing structure having a solar battery and manufacturing method thereof |
| CN205150216U (en) * | 2015-11-24 | 2016-04-13 | 中国航天时代电子公司 | Unmanned aerial vehicle's foam presss from both sides core wing |
| CN106184697A (en) * | 2016-09-14 | 2016-12-07 | 北京航空航天大学 | A kind of straight line penetrating construction formula composite fuselage construction |
| CN106379516A (en) * | 2016-09-14 | 2017-02-08 | 中国电子科技集团公司第四十八研究所 | Solar-powered airplane wing and manufacturing method thereof |
| CN107161318A (en) * | 2016-03-07 | 2017-09-15 | 上海奥科赛飞机有限公司 | The stressed-skin construction and its preparation technology of a kind of solar powered aircraft |
-
2017
- 2017-12-20 CN CN201711402232.XA patent/CN108116656A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20130059022A (en) * | 2011-11-28 | 2013-06-05 | 한국과학기술연구원 | Wing structure having a solar battery and manufacturing method thereof |
| CN102774490A (en) * | 2012-04-10 | 2012-11-14 | 北京航空航天大学 | Novel long-endurance solar unmanned aerial vehicle |
| CN205150216U (en) * | 2015-11-24 | 2016-04-13 | 中国航天时代电子公司 | Unmanned aerial vehicle's foam presss from both sides core wing |
| CN107161318A (en) * | 2016-03-07 | 2017-09-15 | 上海奥科赛飞机有限公司 | The stressed-skin construction and its preparation technology of a kind of solar powered aircraft |
| CN106184697A (en) * | 2016-09-14 | 2016-12-07 | 北京航空航天大学 | A kind of straight line penetrating construction formula composite fuselage construction |
| CN106379516A (en) * | 2016-09-14 | 2017-02-08 | 中国电子科技集团公司第四十八研究所 | Solar-powered airplane wing and manufacturing method thereof |
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|---|---|---|---|---|
| CN112061373A (en) * | 2019-06-11 | 2020-12-11 | 波音公司 | Energy subsystem integrated into a structural component of an aircraft |
| CN110576963A (en) * | 2019-09-19 | 2019-12-17 | 西北工业大学 | Solar unmanned aerial vehicle wing structure |
| CN110576963B (en) * | 2019-09-19 | 2023-03-24 | 西北工业大学 | Solar unmanned aerial vehicle wing structure |
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| CN114408159A (en) * | 2021-12-08 | 2022-04-29 | 中航西安飞机工业集团股份有限公司 | Rapid connecting structure and connecting method for tail wing of unmanned aerial vehicle |
| CN114408159B (en) * | 2021-12-08 | 2023-09-05 | 中航西安飞机工业集团股份有限公司 | Rapid connection structure and connection method for tail wings of unmanned aerial vehicle |
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