CN106379516B - Solar powered aircraft wing and its manufacturing method - Google Patents
Solar powered aircraft wing and its manufacturing method Download PDFInfo
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- CN106379516B CN106379516B CN201610823517.XA CN201610823517A CN106379516B CN 106379516 B CN106379516 B CN 106379516B CN 201610823517 A CN201610823517 A CN 201610823517A CN 106379516 B CN106379516 B CN 106379516B
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- 238000004806 packaging method and process Methods 0.000 claims description 39
- 239000010408 film Substances 0.000 claims description 37
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- 238000003475 lamination Methods 0.000 claims description 28
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- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims description 11
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01L—SEMICONDUCTOR DEVICES NOT COVERED BY CLASS H10
- H01L31/00—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof
- H01L31/04—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof adapted as photovoltaic [PV] conversion devices
- H01L31/042—PV modules or arrays of single PV cells
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01L—SEMICONDUCTOR DEVICES NOT COVERED BY CLASS H10
- H01L31/00—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof
- H01L31/04—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof adapted as photovoltaic [PV] conversion devices
- H01L31/042—PV modules or arrays of single PV cells
- H01L31/0445—PV modules or arrays of single PV cells including thin film solar cells, e.g. single thin film a-Si, CIS or CdTe solar cells
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01L—SEMICONDUCTOR DEVICES NOT COVERED BY CLASS H10
- H01L31/00—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof
- H01L31/04—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof adapted as photovoltaic [PV] conversion devices
- H01L31/042—PV modules or arrays of single PV cells
- H01L31/048—Encapsulation of modules
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01L—SEMICONDUCTOR DEVICES NOT COVERED BY CLASS H10
- H01L31/00—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof
- H01L31/18—Processes or apparatus specially adapted for the manufacture or treatment of these devices or of parts thereof
-
- 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
-
- 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
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
- Y02P70/50—Manufacturing or production processes characterised by the final manufactured product
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- Engineering & Computer Science (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Electromagnetism (AREA)
- General Physics & Mathematics (AREA)
- Condensed Matter Physics & Semiconductors (AREA)
- Computer Hardware Design (AREA)
- Physics & Mathematics (AREA)
- Power Engineering (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
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- Photovoltaic Devices (AREA)
Abstract
The invention discloses a kind of solar powered aircraft wing and its manufacturing methods, solar powered aircraft wing includes wing skeleton and flexible solar cell component, the middle part of wing skeleton upper surface is equipped with groove, flexible solar cell component includes encapsulating covering and the component skeleton set on encapsulation covering lower surface, component skeleton is set in groove, it encapsulates covering and extends outward to form coated side along the both sides of wing skeleton spanwise, coated side is coated on wing skeleton.Manufacturing method includes: S1: preparing wing skeleton；S2: flexible solar cell component is prepared；S3: assembly.The solar powered aircraft wing has many advantages, such as that solar cell module and the conformal effect of wing skeleton are good, surface flatness is high, aeroperformance is excellent and light, which assembles convenient, loss of weight and good reliability.
Description
Technical field
The invention belongs to technical field of solar batteries more particularly to a kind of solar powered aircraft wing and its manufacturing methods.
Background technique
High altitude long time solar energy unmanned plane have flying height height, longevity of service, overlay area extensively, using flexible,
The advantages that operating cost is low and non-environmental-pollution becomes the desired air for executing the tasks such as information, scouting, monitoring and communication relay
Platform has boundless application prospect.It using solar radiation energy as power in high altitude long time non-stop flight
Unmanned vehicle, it is converted solar energy into electrical energy using photocell, is generated and is flown by the rotation of motor drive propeller
Action edge.Daytime, solar energy unmanned plane are converted to the solar radiation energy of absorption by the solar cell that body surface is laid with
Electric energy maintains the operation of dynamical system, avionic device and payload, while charging to airborne secondary power supply.If white
The ability of its storage can satisfy the needs of night flying, then theoretically " permanent " flight may be implemented in solar energy unmanned plane.
In order to guarantee that solar powered aircraft has enough flying powers, generally require to be laid on its wing, fuselage more
Solar cell module, mounting process of the solar battery on solar powered aircraft is technological difficulties.Currently, on unmanned plane
The solar cell of laying is mostly rigid solar cell, due to the limit by solar energy Unmanned Aerial Vehicle Airfoil radian and mounting structure
System, rigid and frangible solar battery array plane easy to crack are difficult to adapt to the fitting and installation at the big position of Curvature varying on wing.When
When the loaded deformation of wing, battery may be badly damaged.This requires should solve the problems, such as the encapsulation to solar battery, solar energy
Aircraft itself provides good laying platform again for battery.To guarantee that pneumatic efficiency, solar battery will not only guarantee to install
When it is conformal with aircraft skin, and to guarantee to fit closely with covering in the entire flight course, so solar battery
Flexibility is most important.Traditional rigid solar cell module generally uses PET light-transmissive film (about 200 μ m-thick), and+EVA layer is (about
500 μ m-thicks)+monocrystalline silicon piece or polysilicon chip (about 180 μ m-thick)+TPE backlight, surface density is usually 2.0~2.5 kg/
m2, cause solar cell module to lack flexibility, and the quality of itself is larger, do not simply fail to adapt to the patch with airfoil camber
It closes, and reduces the load of solar powered aircraft, it is difficult to meet the application demand of solar powered aircraft.
Currently, in the solar energy unmanned plane wing technology of preparing having disclosed, such as 203659894 U of CN and
It is all made of rigid solar cell in CN201510680597 and prepares solar module, in order to guarantee that rigidity is too in battery component
Positive electricity pond is not chipping during bending, and component not can be carried out big bending deformation, is difficult to adapt to Curvature varying on wing
The fitting at big position.Moreover, the solar module and wing skeleton in these patents are laid with mounting process complexity, and install
Structure is difficult to meet the needs of pneumatic property of unmanned plane is to aerofoil surface high glossy.In addition, as in 203659894 U patent of CN
Though more traditional solar module surface density mitigates 35% or more, surface density still reaches 1.2Kg/m2More than；Meanwhile in the patent
The solar module of preparation lacks flexible support substrate and is difficult to ensure solar module and unmanned plane wing skeleton general character
Effect and solar cell piece reliability.
Summary of the invention
The technical problem to be solved by the present invention is to overcome the deficiencies in the prior art, a kind of solar cell module and machine are provided
The conformal effect of wing skeleton is good, surface flatness is high, aeroperformance is excellent and light solar powered aircraft wing, in addition also corresponding
A kind of preparation method assembling convenient, loss of weight and reliable above-mentioned solar powered aircraft wing is provided.
In order to solve the above technical problems, the invention adopts the following technical scheme:
A kind of solar powered aircraft wing, including wing skeleton and flexible solar cell component, the wing skeleton upper surface
Middle part be equipped with groove, the flexible solar cell component include encapsulate covering and set on encapsulation covering lower surface component bone
Frame, the component skeleton are set in the groove, and the encapsulation covering is along the both sides of the wing skeleton spanwise to extension
It stretches to form coated side, the coated side is coated on wing skeleton.
As a further improvement of the above technical scheme:
The consistency of thickness of the depth of the groove and the component skeleton.
The encapsulation covering is heat shrinkage film.
The heat shrinkage film includes PET heat shrinkage film, PVC heat shrinkage film, OPS heat shrinkage film, PE heat shrinkage film or POF heat shrinkage film.
The heat shrinkage film with a thickness of 20 μm~60 μm, transmitance is 80%~100%.
The component skeleton from top to bottom successively include the first packaging adhesive film, flexible solar cell array, the second packaging adhesive film,
Inside panel, third packaging adhesive film and supporting element；Or the component skeleton successively include from bottom to up the first packaging adhesive film, it is flexible too
Positive cell array, the second packaging adhesive film, supporting element, third packaging adhesive film and inside panel.
The supporting element is polymethacrylimide foam plate.
The polymethacrylimide foam plate with a thickness of 0.2mm~3mm, density is 30 Kg/m3~100Kg/
m3。
The flexible solar cell array includes multiple solar cell pieces and photovoltaic welding belt, and adjacent solar cell piece passes through described
Photovoltaic welding belt connection.
The solar cell piece is thin including flexible crystal silicon solar battery piece, thin film gallium arsenide solar cell piece, copper indium gallium selenide
Film solar cell piece or amorphous silicon film solar battery piece.
The photovoltaic welding belt with a thickness of 0.03mm~0.3mm.
The inventive concept total as one, the present invention also provides a kind of manufacturing methods of solar powered aircraft wing, including with
Lower step:
S1: wing skeleton is prepared, and in the processing of the middle part of the wing skeleton upper surface and component skeleton cooperation
Groove；
S2: preparing flexible solar cell component, and the flexible solar cell component includes encapsulation covering and covers set on encapsulation
The component skeleton of subcutaneous surface, the encapsulation covering extend outward to form coated side along the both sides of the component skeleton；
S3: component skeleton is placed in groove, and the coated side is arranged along the spanwise of wing skeleton, and uses bonding agent
Coated side is fixed on to the surface of wing skeleton.
As a further improvement of the above technical scheme:
The encapsulation covering is heat shrinkage film, and the manufacturing method is further comprising the steps of:
S4: heating coated side, shrinks coated side and is tensioned to the surface of wing skeleton.
The heating temperature is 60 DEG C~200 DEG C.
In the step S2, the flexible solar cell component the preparation method is as follows:
It first presses from top to bottom as encapsulation covering, the first packaging adhesive film, flexible solar cell array, the second packaging adhesive film, Inner Mongol
After the sequence of skin carries out lamination, first step laminating technology is carried out, laminating temperature is 80 DEG C~150 DEG C, and lamination pressure is 15 kPa
~100kPa, lamination times are 5min~30min；It is cooling, intermediate module is obtained, then press is intermediate module, third from top to bottom
After the sequence of packaging adhesive film and supporting element carries out lamination, second step laminating technology is carried out, laminating temperature is 50 DEG C~120 DEG C, layer
Pressure pressure is 10 kPa~50kPa, and lamination times are 5min~20min.
In the step S2, the preparation method of the flexible solar cell component also be can be such that
It first presses from top to bottom as encapsulation covering, the first packaging adhesive film, flexible solar cell array, the second packaging adhesive film, support
The sequence of part, third packaging adhesive film and inside panel carries out lamination, then is laminated, and laminating temperature is 80 DEG C~150 DEG C, lamination pressure
Power is 15 kPa~100kPa, and lamination times are 5min~30min.
In the step S3, the bonding agent includes silicon rubber, polyurethane or epoxy resin, the solidification temperature of the bonding agent
Degree is 25 DEG C~80 DEG C, curing time 15 minutes~7 days.
Compared with the prior art, the advantages of the present invention are as follows:
1, solar powered aircraft wing of the invention, the component skeleton of flexible solar cell component are placed in the wing slotted in advance
In the groove of skeleton, the coated side for encapsulating covering is then coated on wing skeleton, forms the skin of wing skeleton, this
Structure greatly improves the conformal effect and surface flatness of solar cell module and wing skeleton, and solar energy greatly improved
The flight aeroperformance and reliability of unmanned plane.
2, solar powered aircraft wing of the invention, it is preferred that encapsulation covering uses heat shrinkage film, can be by carrying out to coated side
Heating, makes its contraction be tensioned to wing skeleton surface, further promotes the pneumatic safety effect on wing skeleton surface and covering.
3, solar powered aircraft wing of the invention, it is preferred that using the solar cell of flexible (being thinned) as battery pack
Solar cell piece in part, and it is welded into cell array with ultra-thin welding, the solar cell array after being thinned has certain soft
Toughness and bending property, it is ensured that flexible solar cell component is bonded with the perfection of wing skeleton.
Although the solar cell array after 4, being thinned has certain bending property, brittleness increases, in bending force unevenness
Easily fragmentation in the case where even is especially easier to fragmentation in the similar application for having large curved structure such as solar energy unmanned plane,
Thus its packaging protection requires higher than common rigid battery.There is good flexibility and bending in order to guarantee component both
Property, and be not destroyed during bending, that is, it requires to improve encapsulating material and packaging technology, the sun electricity after making encapsulation
The flexibility and rigidity of pond component reach optimum balance, obtain optimal spreading property.Wherein, supporting element in solar module
It selects particularly critical, is the most crucial component whether entire solar module has best spreading property.Applicant is through excessive
The test of amount is attempted, final preferably supporting element of the polymethacrylimide foam plate as flexible solar cell component, test
Flexible solar cell component after showing encapsulation has extraordinary spreading property.
5, the manufacturing method of solar powered aircraft wing of the invention, by the middle part processing of wing skeleton upper surface and electricity
The groove of pond component skeleton cooperation, and when preparing flexible solar cell component, will encapsulation covering along the both sides of component skeleton to
Outer extension certain length forms coated side, when assembly, component skeleton is placed in groove, coated side is along the span side of wing skeleton
To arrangement, and coated side is fixed on to bonding agent the surface of wing skeleton, that is, completes the manufacture of solar powered aircraft wing.This
The integrated packaged type of kind leans on the mechanical structures such as rivet, pin, hasp by solar module and wing skeleton with conventional
The manufacture assembly method being locked is compared, and enormously simplifies solar cell module in the erector of solar energy unmanned plane
Skill, and fixed weight is installed greatly reduces, so that the load-carrying ability of solar energy unmanned plane greatly improved.In addition, flexibility is too
Positive battery component and wing skeleton share covering, realize flexible solar cell component and are bonded with wing skeleton perfection, can be substantially
Promote the pneumatic safety effect on wing skeleton surface and covering.
6, the manufacturing method of solar powered aircraft wing of the invention encapsulates the preferred heat shrinkage film of covering, adds to coated side
Heat, can be such that coated side shrinks and the surface for being tensioned to wing skeleton further promotes the pneumatic insurance of wing skeleton surface and covering
Effect.
Detailed description of the invention
Fig. 1 is the cross section structure schematic diagram of the solar powered aircraft wing of the embodiment of the present invention.
Fig. 2 is the schematic perspective view of the solar powered aircraft wing of the embodiment of the present invention.
Fig. 3 is the structural schematic diagram of the flexible solar cell component in the embodiment of the present invention.
Marginal data: 1, wing skeleton；11, groove；2, flexible solar cell component；21, covering is encapsulated；211, it coats
Side；22, component skeleton；221, the first packaging adhesive film；222, flexible solar cell array；2221, solar cell piece；2222, photovoltaic
Welding；223, the second packaging adhesive film；224, inside panel；225, third packaging adhesive film；226, supporting element.
Specific embodiment
Below in conjunction with Figure of description and specific preferred embodiment, the invention will be further described, but not therefore and
It limits the scope of the invention.
Embodiment 1:
As depicted in figs. 1 and 2, the solar powered aircraft wing of the present embodiment, including wing skeleton 1 and flexible solar cell group
Part 2, the middle part of 1 upper surface of wing skeleton are equipped with groove 11, and flexible solar cell component 2 includes encapsulating covering 21 and being set to encapsulate
The component skeleton 22 of 21 lower surface of covering, component skeleton 22 are set in groove 11, encapsulate covering 21 along 1 spanwise of wing skeleton
(as direction of the arrows shown in fig) both sides extend outward to form coated side 211, and coated side 211 is coated on wing skeleton 1.It is i.e. soft
The skin of property solar module 2 extends to the skin of wing skeleton 1, and this structure greatly improves solar-electricity
The surface flatness of the conformal effect and wing of pond component and wing skeleton, the flight that solar energy unmanned plane greatly improved are pneumatic
Performance And Reliability.
In the present embodiment, the depth of groove 11 and the thickness H of component skeleton 1 are consistent, further improve solar battery
The surface flatness of the conformal effect and wing of component and wing skeleton.
In the present embodiment, encapsulation covering 21 is PET heat shrinkage film, with a thickness of 25 μm, transmitance 95%.
In other embodiments, heat shrinkage film can be PET heat shrinkage film, PVC heat shrinkage film, OPS heat shrinkage film, PE heat shrinkage film or
POF heat shrinkage film.The thickness of heat shrinkage film is preferably 20 μm~60 μm, and transmitance is preferably 80%~100%.
In the present embodiment, as shown in figure 3, component skeleton 22 successively include from top to bottom the first packaging adhesive film 221, it is flexible too
Positive cell array 222, the second packaging adhesive film 223, inside panel 224, third packaging adhesive film 225 and supporting element 226；
In other examples, it successively includes the first packaging adhesive film 221 that component skeleton 22 is also possible to from bottom to up, soft
Property solar battery array 222, the second packaging adhesive film 223, supporting element 226, third packaging adhesive film 225 and inside panel 224.
In the present embodiment, supporting element 226 is polymethacrylimide foam plate, and with a thickness of 0.5mm, density is 50 Kg/
m3, the flexibility of the flexible solar cell component 2 after encapsulating and rigidity can be made to reach optimum balance, obtain optimal spreading property.
The thickness of polymethacrylimide foam plate is preferably 0.2mm~3mm, and density is preferably 30 Kg/m3~
100Kg/m3。
In the present embodiment, flexible solar cell array 222 includes multiple solar cell pieces 2221 and photovoltaic welding belt 2222, adjacent
Solar cell piece 2221 is connected by photovoltaic welding belt 2222, finally constitutes flexible solar cell array 222.Solar cell piece 2221 is
Flexible crystal silicon solar battery piece, single flexible crystal silicon solar battery chip size size is 40mm × 156mm, with a thickness of 100 microns,
Photovoltaic welding belt 2222 with a thickness of 0.08mm, the gap between cell piece is 0.5mm.
The flexible solar cell array 222 of the present embodiment, crucial preparation flow are as follows: (1) passing through wafer thinning technique and surpass
Multiple crystal silicon solar battery pieces that thin silicon wafer preparation process prepares with a thickness of 100 microns, this ultra-thin crystal silicon solar battery
Piece has certain flexibility, and single flexible crystal silicon solar battery chip size size is 40mm × 156mm；(2) using with a thickness of
The ultra-thin photovoltaic welding belt of 0.08mm, by crystal silicon solar battery welding procedure, by adjacent crystal silicon solar battery piece (adjacent crystal silicon
Gap between solar cell piece is 0.5mm) interconnection, ultimately form flexible solar cell array 222.Solar battery array after being thinned
Column have certain flexibility and bending property, it is ensured that flexible solar cell component is bonded with the perfection of wing skeleton.
In other examples, it is thin to can be thin film gallium arsenide solar cell piece, copper indium gallium selenide for solar cell piece 2221
Film solar cell piece or amorphous silicon film solar battery piece.The thickness of photovoltaic welding belt 2222 is preferably 0.03mm~0.3mm.
A kind of manufacturing method of the solar powered aircraft wing of the present embodiment, comprising the following steps:
S1: wing skeleton 1, and the groove cooperated in the processing of the middle part of 1 upper surface of wing skeleton with component skeleton 22 are prepared
11, depth of groove 0.8mm；
S2: preparing flexible solar cell component 2, and flexible solar cell component 2 includes encapsulation covering 21 and covers set on encapsulation
The component skeleton 22 of 21 lower surface of skin, encapsulation covering 21 are heat shrinkage film, and encapsulation covering 21 is along the both sides of component skeleton 22 to extension
It stretches to form coated side 211；
In the present embodiment, flexible solar cell component the preparation method is as follows:
It first presses from top to bottom as encapsulation covering 21, the first packaging adhesive film 221, flexible solar cell array 222, the second packaging plastic
The sequence progress lamination of film 223, inside panel 224, carries out first step laminating technology, laminating temperature is 130 DEG C, and lamination pressure is
80kPa, lamination times 10min；Then, after it is cooled to room temperature, by from top to bottom be the first step lamination obtain component,
After the sequence lamination of third packaging adhesive film 225 and supporting element 226, second step laminating technology is carried out, laminating temperature is 80 DEG C, lamination
Pressure is 40kPa, lamination times 8min.Applicant has found during one step packaging by hot pressing of flexible solar cell component, gathers
Methacrylimide cystosepiment is placed in the bottom of battery component, since material percent thermal shrinkage each in component is different, leads to electricity
For pond component there are slight warpage, reliability becomes poor.By two step laminating technologies, releasably since material percent thermal shrinkage difference is made
At component warping phenomenon.
In other examples, the preparation method of flexible solar cell component is also possible to as follows:
It first presses from top to bottom as encapsulation covering 21, the first packaging adhesive film 221, flexible solar cell array 222, the second packaging plastic
Film 223, supporting element 226, third packaging adhesive film 225 and inside panel 224 sequence carry out lamination, then be laminated, laminating temperature
It is 80 DEG C~150 DEG C, lamination pressure is 15 kPa~100kPa, and lamination times are 5min~30min.
S3: component skeleton 22 is placed in groove 11, and coated side 211 is arranged along the spanwise of wing skeleton 1, by opening
Tight mechanism makes flexible solar cell component 2 be in tensioning state, and coated side 211 is fitted in wing skeleton 1 with polyurethane adhesive
Curved surfaces on, be heating and curing to polyurethane adhesive, solidification temperature be 80 DEG C, curing time 60min.After adhesive curing,
Flexible solar cell component 2 has been fixed on the surface of wing skeleton 1 by coated side 211, is realized flexible solar cell component 2 and is existed
The perfect fitting on 1 surface of wing skeleton, improves the pneumatic safety effect of wing skeleton surface and covering.Also, with it is existing
Solar powered aircraft wing manufacturing process is compared, and enormously simplifies solar cell module in the installation procedure of solar energy unmanned plane,
And installing fixed weight greatly reduces, so that the load-carrying ability of solar energy unmanned plane greatly improved.
In the present embodiment, the coated side 211 positioned at 22 two sides of component skeleton is extended to from the upper surface of wing skeleton 1 respectively
Lower surface simultaneously contacts, namely encapsulation covering 21 gets up the upper and lower surface cladding of entire wing skeleton 1, further improves wing
The pneumatic safety effect on skeleton surface and covering.
S4: heating coated side 211, and heating temperature is 150 DEG C, and coated side 211 can be made to shrink and be tensioned to wing
The surface of skeleton 1 further improves the pneumatic safety effect of wing skeleton surface and covering.
In other examples, heating temperature is also possible to 60 DEG C~200 DEG C, can reach the same or similar effect.
In other examples, polyurethane adhesive can be replaced with silicon rubber or epoxide-resin glue, solidification temperature be 25 DEG C~
80 DEG C, curing time 15 minutes~7 days.
The above is only a preferred embodiment of the present invention, protection scope of the present invention is not limited merely to above-mentioned implementation
Example.All technical solutions belonged under thinking of the present invention all belong to the scope of protection of the present invention.It is noted that for the art
Those of ordinary skill for, improvements and modifications without departing from the principle of the present invention, these improvements and modifications are also answered
It is considered as protection scope of the present invention.
Claims (17)
1. a kind of solar powered aircraft wing, including wing skeleton (1) and flexible solar cell component (2), which is characterized in that described
The middle part of wing skeleton (1) upper surface be equipped with groove (11), the flexible solar cell component (2) include encapsulation covering (21) and
Component skeleton (22) set on encapsulation covering (21) lower surface, the component skeleton (22) is set in the groove (11), described
It encapsulates covering (21) and extends outward to form coated side (211), the coated side along the both sides of the wing skeleton (1) spanwise
(211) it is coated on wing skeleton (1).
2. solar powered aircraft wing according to claim 1, which is characterized in that the depth of the groove (11) and described group
The consistency of thickness of part skeleton (22).
3. solar powered aircraft wing according to claim 1, which is characterized in that the encapsulation covering (21) is heat shrinkage film.
4. solar powered aircraft wing according to claim 3, which is characterized in that the heat shrinkage film include PET heat shrinkage film,
PVC heat shrinkage film, OPS heat shrinkage film, PE heat shrinkage film or POF heat shrinkage film.
5. solar powered aircraft wing according to claim 4, which is characterized in that the heat shrinkage film with a thickness of 20 μm~60
μm, transmitance is 80%~100%.
6. described in any item solar powered aircraft wings according to claim 1~5, which is characterized in that the component skeleton (22)
It from top to bottom successively include the first packaging adhesive film (221), flexible solar cell array (222), the second packaging adhesive film (223), Inner Mongol
Skin (224), third packaging adhesive film (225) and supporting element (226)；Or the component skeleton (22) successively includes first from bottom to up
Packaging adhesive film (221), flexible solar cell array (222), the second packaging adhesive film (223), supporting element (226), third packaging adhesive film
(225) and inside panel (224).
7. solar powered aircraft wing according to claim 6, which is characterized in that the supporting element (226) is poly- methyl-prop
Alkene acid imide foam plate.
8. solar powered aircraft wing according to claim 7, which is characterized in that the polymethacrylimide foam plate
With a thickness of 0.2mm~3mm, density is 30 Kg/m3~100Kg/m3。
9. solar powered aircraft wing according to claim 6, which is characterized in that flexible solar cell array (222) packet
Multiple solar cell pieces (2221) and photovoltaic welding belt (2222) are included, adjacent solar cell piece (2221) passes through the photovoltaic welding belt
(2222) it connects.
10. solar powered aircraft wing according to claim 9, which is characterized in that the solar cell piece (2221) includes
Flexible crystal silicon solar battery piece, thin film gallium arsenide solar cell piece, CIGS thin-film solar cell piece or amorphous silicon membrane are too
Positive cell piece.
11. solar powered aircraft wing according to claim 10, which is characterized in that the thickness of the photovoltaic welding belt (2222)
For 0.03mm~0.3mm.
12. a kind of manufacturing method of solar powered aircraft wing, comprising the following steps:
S1: preparing wing skeleton (1), and cooperates in the processing of the middle part of the wing skeleton (1) upper surface with component skeleton (22)
Groove (11)；
S2: preparing flexible solar cell component (2), and the flexible solar cell component (2) includes encapsulation covering (21) and is set to
The component skeleton (22) of covering (21) lower surface is encapsulated, encapsulation covering (21) is outside along the both sides of the component skeleton (22)
Extend to form coated side (211)；
S3: component skeleton (22) is placed in groove (11), spanwise cloth of the coated side (211) along wing skeleton (1)
It sets, and coated side (211) is fixed on to the surface of wing skeleton (1) with bonding agent.
13. the manufacturing method of solar powered aircraft wing according to claim 12, which is characterized in that the encapsulation covering
(21) it is heat shrinkage film, the manufacturing method is further comprising the steps of:
S4: heating coated side (211), shrinks coated side (211) and is tensioned to the surface of wing skeleton (1).
14. the manufacturing method of solar powered aircraft wing according to claim 13, which is characterized in that the heating temperature is
60 DEG C~200 DEG C.
15. the manufacturing method of solar powered aircraft wing described in any one of 2~14 according to claim 1, which is characterized in that
In the step S2, the flexible solar cell component the preparation method is as follows:
It first presses from top to bottom as encapsulation covering (21), the first packaging adhesive film (221), flexible solar cell array (222), the second encapsulation
Glue film (223), inside panel (224) sequence carry out lamination after, carry out first step laminating technology, laminating temperature be 80 DEG C~150
DEG C, lamination pressure is 15 kPa~100kPa, and lamination times are 5min~30min；It is cooling, intermediate module is obtained, then press from upper
After carrying out lamination to the lower sequence for intermediate module, third packaging adhesive film (225) and supporting element (226), second step lamination is carried out
Technique, laminating temperature are 50 DEG C~120 DEG C, and lamination pressure is 10 kPa~50kPa, and lamination times are 5min~20min.
16. the manufacturing method of solar powered aircraft wing described in any one of 2~14 according to claim 1, which is characterized in that
In the step S2, the flexible solar cell component the preparation method is as follows:
It first presses from top to bottom as encapsulation covering (21), the first packaging adhesive film (221), flexible solar cell array (222), the second encapsulation
Glue film (223), supporting element (226), third packaging adhesive film (225) and inside panel (224) sequence carry out lamination, then carry out layer
Pressure, laminating temperature are 80 DEG C~150 DEG C, and lamination pressure is 15 kPa~100kPa, and lamination times are 5min~30min.
17. the manufacturing method of solar powered aircraft wing described in any one of 2~14 according to claim 1, which is characterized in that
In the step S3, the bonding agent includes silicon rubber, polyurethane or epoxy resin, and the solidification temperature of the bonding agent is 25 DEG C
~80 DEG C, curing time 15 minutes~7 days.
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| CN108116656A (en) * | 2017-12-20 | 2018-06-05 | 广东翼景信息科技有限公司 | A kind of solar energy unmanned plane |
| CN108820245B (en) * | 2018-06-26 | 2022-04-15 | 北京航空航天大学 | Solar airplane wing surface covering film tensioning and mounting equipment |
| CN109103284A (en) * | 2018-08-02 | 2018-12-28 | 东汉太阳能无人机技术有限公司 | Aircraft, solar cell system, wing and its manufacturing method |
| CN110040239A (en) * | 2019-04-25 | 2019-07-23 | 上海空间电源研究所 | A kind of unmanned plane photovoltaic stressed-skin construction that modularization is replaceable |
| CN111252256B (en) * | 2019-12-31 | 2021-05-04 | 中电科芜湖通用航空产业技术研究院有限公司 | Electric aircraft system based on battery encapsulation |
| CN111661346A (en) * | 2020-07-04 | 2020-09-15 | 河北柒壹壹玖工业自动化技术有限公司 | Unmanned aerial vehicle device based on flexible solar energy thin film battery |
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| CN101665153A (en) * | 2009-09-24 | 2010-03-10 | 南昌航空大学 | Plane wing with solar battery |
| CN102299191A (en) * | 2010-06-22 | 2011-12-28 | 杜邦太阳能有限公司 | Photovoltaic panel and method of manufacturing same |
| KR20130059022A (en) * | 2011-11-28 | 2013-06-05 | 한국과학기술연구원 | Wing structure having a solar battery and manufacturing method thereof |
| CN103035768A (en) * | 2012-12-28 | 2013-04-10 | 浙江大学 | Solar battery assembly and preparing method thereof |
| CN204680677U (en) * | 2015-06-01 | 2015-09-30 | 程雨萱 | A kind of automobile-used flexible solar cell assembly |
| CN105322039B (en) * | 2015-09-29 | 2017-12-15 | 中国电子科技集团公司第四十八研究所 | Ultralight flexible crystalline silicon solar cell modules and preparation method thereof |
| CN113716019B (en) * | 2015-10-19 | 2023-06-06 | 北京航空航天大学 | Battery array capable of being quickly assembled and disassembled, aircraft wing structure and manufacturing method thereof |
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