CN106379516A - Solar-powered airplane wing and manufacturing method thereof - Google Patents

Solar-powered airplane wing and manufacturing method thereof Download PDF

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Publication number
CN106379516A
CN106379516A CN201610823517.XA CN201610823517A CN106379516A CN 106379516 A CN106379516 A CN 106379516A CN 201610823517 A CN201610823517 A CN 201610823517A CN 106379516 A CN106379516 A CN 106379516A
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China
Prior art keywords
wing
solar cell
skeleton
assembly
powered aircraft
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CN201610823517.XA
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CN106379516B (en
Inventor
周洪彪
张建国
杨晓生
黄齐鸣
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CETC 48 Research Institute
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CETC 48 Research Institute
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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C3/00Wings
    • HELECTRICITY
    • H01BASIC ELECTRIC ELEMENTS
    • H01LSEMICONDUCTOR DEVICES; ELECTRIC SOLID STATE DEVICES NOT OTHERWISE PROVIDED FOR
    • H01L31/00Semiconductor devices sensitive to infra-red 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
    • H01L31/04Semiconductor devices sensitive to infra-red 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
    • H01L31/042PV modules or arrays of single PV cells
    • HELECTRICITY
    • H01BASIC ELECTRIC ELEMENTS
    • H01LSEMICONDUCTOR DEVICES; ELECTRIC SOLID STATE DEVICES NOT OTHERWISE PROVIDED FOR
    • H01L31/00Semiconductor devices sensitive to infra-red 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
    • H01L31/04Semiconductor devices sensitive to infra-red 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
    • H01L31/042PV modules or arrays of single PV cells
    • H01L31/0445PV modules or arrays of single PV cells including thin film solar cells, e.g. single thin film a-Si, CIS or CdTe solar cells
    • HELECTRICITY
    • H01BASIC ELECTRIC ELEMENTS
    • H01LSEMICONDUCTOR DEVICES; ELECTRIC SOLID STATE DEVICES NOT OTHERWISE PROVIDED FOR
    • H01L31/00Semiconductor devices sensitive to infra-red 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
    • H01L31/04Semiconductor devices sensitive to infra-red 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
    • H01L31/042PV modules or arrays of single PV cells
    • H01L31/048Encapsulation of modules
    • HELECTRICITY
    • H01BASIC ELECTRIC ELEMENTS
    • H01LSEMICONDUCTOR DEVICES; ELECTRIC SOLID STATE DEVICES NOT OTHERWISE PROVIDED FOR
    • H01L31/00Semiconductor devices sensitive to infra-red 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
    • H01L31/18Processes or apparatus specially adapted for the manufacture or treatment of these devices or of parts thereof
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02EREDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00Energy generation through renewable energy sources
    • Y02E10/50Photovoltaic [PV] energy
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02PCLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P70/00Climate change mitigation technologies in the production process for final industrial or consumer products
    • Y02P70/50Manufacturing or production processes characterised by the final manufactured product

Abstract

The invention discloses a solar-powered airplane wing and a manufacturing method thereof. The solar-powered airplane wing comprises a wing framework and a flexible solar cell module, wherein the middle part of the upper surface of the wing framework is provided with a groove; the flexible solar cell module comprises a packaging skin and an assembly framework arranged on the lower surface of the packaging skin; the assembly framework is arranged in the groove; the packaging skin extends outwards along the two sides of the wing framework in the spanwise direction to form a coating side; and the coating side is coated on the wing framework. The manufacturing method comprises the following steps: S1: preparing the wing framework; S2: preparing the flexible solar cell module; and S3: assembling. The solar-powered airplane wing has the advantages of favorable conformal effects between the solar cell module and wing framework, high surface smoothness, excellent aerodynamic performance, light weight and the like. The preparation method has the advantages of convenient assembly, weight reduction and favorable reliability.

Description

Solar powered aircraft wing and its manufacture method
Technical field
The invention belongs to technical field of solar batteries, more particularly, to a kind of solar powered aircraft wing and its manufacture method.
Background technology
HAE solar energy unmanned plane have flying height height, longevity of service, overlay area wide, using flexibly, Operating cost is low and the advantages of non-environmental-pollution, becomes the desired air of the tasks such as execution information, scoutings, supervision and communication relay Platform, has boundless application prospect.It can be as power in HAE non-stop flight by the use of solar radiation Unmanned vehicle, it is converted solar energy into electrical energy using photocell, is produced by the rotation of motor-driven screw and flies Action edge.On daytime, solar energy unmanned plane relies on the solar cell of body surface laying can be converted to the solar radiation of absorption Electric energy, maintains the operation of dynamical system, avionic device and payload, airborne secondary power supply is charged simultaneously.If white The ability of its storage disclosure satisfy that the needs of night flying, then solar energy unmanned plane can realize " permanent " flight in theory.
In order to ensure that solar powered aircraft has enough flying powers, generally require to lay on its wing, fuselage more Solar module, mounting process on solar powered aircraft for the solar cell is technological difficulties.At present, on unmanned plane The solar cell of laying is mostly rigid solar cell, due to being limited by solar energy Unmanned Aerial Vehicle Airfoil radian and mounting structure System, the rigid and frangible solar battery array plane easily split is difficult to adapt to the laminating at the big position of Curvature varying and installation on wing.When During the deformation of wing stand under load, battery may be badly damaged.This requires to solve the problems, such as the encapsulation to solar cell, solar energy Aircraft itself provides good laying platform for battery again.For ensureing pneumatic efficiency, solar cell not only will ensure to install When conformal with aircraft skin, and to ensure in whole flight course with the fitting tightly of covering, so solar cell Pliability is most important.Traditional rigid solar module typically adopts PET light-transmissive film(About 200 μ m-thick)+ EVA layer(About 500 μ m-thick)+ monocrystalline silicon piece or polysilicon chip(About 180 μ m-thick)+ TPE backlight, its surface density is usually 2.0~2.5 kg/ m2, lead to solar module to lack pliability, and the quality of itself be larger, do not simply fail to adapt to the patch with airfoil camber Close, and reduce the load of solar powered aircraft it is difficult to meet the application demand of solar powered aircraft.
At present, in disclosed solar energy unmanned plane wing technology of preparing, such as CN 203659894 U and All solar module is prepared using rigid solar cell in CN201510680597, in order to ensure that in battery component, rigidity is too Positive electricity pond is not chipping in BENDING PROCESS, and assembly can not carry out big flexural deformation, is difficult to adapt to Curvature varying on wing The laminating at big position.And, the solar module in these patents is complicated with wing skeleton laying mounting process, and installs Structure is difficult to meet the demand to aerofoil surface high glossy for the pneumatic property of unmanned plane.In addition, as in CN 203659894 U patent Though more traditional solar module surface density mitigates more than 35%, surface density still reaches 1.2Kg/m2More than;Meanwhile, in this patent The solar module of preparation lacks pliable and tough support substrate and is difficult to ensure that solar module and unmanned plane wing skeleton general character Effect and solar cell piece reliability.
Content of the invention
The technical problem to be solved in the present invention is to overcome the deficiencies in the prior art, provides a kind of solar module and machine The conformal effect of wing skeleton is good, surface flatness is high, aeroperformance is excellent and the solar powered aircraft wing of light weight, in addition also corresponding The preparation method of a kind of offer convenient, loss of weight of assembling and reliably above-mentioned solar powered aircraft wing.
For solving above-mentioned technical problem, the present invention employs the following technical solutions:
A kind of solar powered aircraft wing, including wing skeleton and flexible solar cell assembly, in described wing skeleton upper surface Portion is provided with groove, and described flexible solar cell assembly includes encapsulating covering and the assembly skeleton located at encapsulation covering lower surface, institute State assembly skeleton in described groove, described encapsulation covering stretches out and formed along the both sides of described wing skeleton spanwise Coated side, described coated side is coated on wing skeleton.
Improvement further as technique scheme:
The depth of described groove and the consistency of thickness of described assembly skeleton.
Described encapsulation covering is heat shrinkage film.
Described 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 thickness of described heat shrinkage film is 20 μm~60 μm, and transmitance is 80%~100%.
Described assembly skeleton include successively from top to bottom the first packaging adhesive film, flexible solar cell array, the second packaging adhesive film, Inside panel, the 3rd packaging adhesive film and support member;Or described assembly skeleton includes the first packaging adhesive film, flexibility too from bottom to up successively Positive cell array, the second packaging adhesive film, support member, the 3rd packaging adhesive film and inside panel.
Described support member is polymethacrylimide foam plate.
The thickness of described polymethacrylimide foam plate is 0.2mm~3mm, and density is 30 Kg/m3~100Kg/ m3.
Described flexible solar cell array includes multiple solar cell pieces and photovoltaic welding belt, and adjacent solar cell piece passes through described Photovoltaic welding belt connects.
It is thin that described solar cell piece includes flexible crystal silicon solar battery piece, thin film gallium arsenide solar cell piece, CIGS Film solar cell piece or amorphous silicon film solar battery piece.
The thickness of described photovoltaic welding belt is 0.03mm~0.3mm.
As a total inventive concept, the present invention also provides a kind of manufacture method of solar powered aircraft wing, including with Lower step:
S1:Prepare wing skeleton, and the groove that the middle part processing in described wing skeleton upper surface is coordinated with described assembly skeleton;
S2:Prepare flexible solar cell assembly, described flexible solar cell assembly includes encapsulating covering and under encapsulation covering The assembly skeleton on surface, described encapsulation covering stretches out formation coated side along the both sides of described assembly skeleton;
S3:Assembly skeleton is placed in groove, described coated side is along the spanwise arrangement of wing skeleton, and will be wrapped with bonding agent Cover the surface that side is fixed on wing skeleton.
Improvement further as technique scheme:
Described encapsulation covering is heat shrinkage film, and described manufacture method is further comprising the steps of:
S4:Coated side is heated, so that coated side is shunk and be tensioned to the surface of wing skeleton.
Described heating-up temperature is 60 DEG C~200 DEG C.
In described step S2, the preparation method of described flexible solar cell assembly is as follows:
First press is encapsulation covering, the first packaging adhesive film, flexible solar cell array, the second packaging adhesive film, inside panel from top to bottom Order carry out lamination after, carry out first step laminating technology, laminating temperature be 80 DEG C~150 DEG C, lamination pressure be 15 kPa~ 100kPa, lamination times are 5min~30min;Cooling, obtains intermediate module, then by from top to bottom for intermediate module, the 3rd envelope After the order of dress glued membrane and support member carries out lamination, carry out second step laminating technology, laminating temperature is 50 DEG C~120 DEG C, lamination Pressure is 10 kPa~50kPa, and lamination times are 5min~20min.
In described step S2, the preparation method of described flexible solar cell assembly can also be as follows:
First press be from top to bottom encapsulation covering, the first packaging adhesive film, flexible solar cell array, the second packaging adhesive film, support member, the The order of three packaging adhesive films and inside panel carries out lamination, then is laminated, and laminating temperature is 80 DEG C~150 DEG C, and lamination pressure is 15 kPa~100kPa, lamination times are 5min~30min.
In described step S3, described bonding agent includes silicon rubber, polyurethane or epoxy resin, the solidification temperature of described bonding agent Spend for 25 DEG C~80 DEG C, 15 minutes~7 days hardening time.
Compared with prior art, it is an advantage of the current invention that:
1st, the solar powered aircraft wing of the present invention, the assembly skeleton of flexible solar cell assembly is placed in the wing skeleton slotted in advance Groove in, encapsulation covering coated side be then coated on wing skeleton, define the skin of wing skeleton, this structure Greatly improve conformal effect and the surface flatness of solar module and wing skeleton, solar energy is greatly improved unmanned The flight aeroperformance of machine and reliability.
2nd, the solar powered aircraft wing of the present invention, can be by carrying out to coated side it is preferred that encapsulation covering adopts heat shrinkage film Heating is tensioned to wing skeleton surface so as to shrink, further the pneumatic safety effect of lifting wing skeleton surface and covering.
3rd, the solar powered aircraft wing of the present invention is it is preferred that adopt flexible(I.e. thinning)Solar cell as battery pack Solar cell piece in part, and be welded into cell array with ultra-thin welding, thinning after solar cell array have necessarily soft Toughness and bending property are it is ensured that flexible solar cell assembly is fitted with the perfection of wing skeleton.
Although 4 thinning after solar cell array there is certain bending property, fragility increases, uneven in flexural loading Easily fragmentation in the case of even, is particularly more easy to fragmentation in the similar application having large curved structure such as solar energy unmanned plane, Thus the requirement of its packaging protection is higher than common rigid battery.In order to ensure that assembly both had good pliability and bending Property, and be not destroyed in BENDING PROCESS, that is, require encapsulating material and packaging technology are improved, make the electricity of the sun after encapsulation The flexibility of pond assembly and rigidity reach optimum balance, obtain optimal spreading property.Wherein, support member in solar module Select particularly critical, be the most crucial part whether whole solar module has optimal spreading property.Applicant is through excessive The test of amount is attempted, and finally preferably polymethacrylimide foam plate is as the support member of flexible solar cell assembly, test Show, the flexible solar cell assembly after encapsulation has extraordinary spreading property.
5th, the manufacture method of the solar powered aircraft wing of the present invention, by the middle part processing in wing skeleton upper surface and electricity The groove of pond assembly skeleton cooperation, and when preparing flexible solar cell assembly, by encapsulation covering along assembly skeleton both sides to Outer extension certain length forms coated side, during assembling, assembly skeleton is placed in groove, coated side is along the span side of wing skeleton To arrangement, and with bonding agent, coated side is fixed on the surface of wing skeleton, that is, completes the manufacture of solar powered aircraft wing.This The packaged type of kind of integration with conventional by frame for movements such as rivet, pin, hasps by solar module and wing skeleton The manufacture assembly method being locked is compared, and enormously simplify the erector in solar energy unmanned plane for the solar module Skill, and fixed weight is installed greatly reduces, thus the load-carrying ability of solar energy unmanned plane is greatly improved.In addition, flexibility is too Positive battery component shares covering with wing skeleton it is achieved that flexible solar cell assembly is fitted with wing skeleton perfection, can be significantly Lifting wing skeleton surface and the pneumatic safety effect of covering.
6th, the manufacture method of the solar powered aircraft wing of the present invention, encapsulates the preferred heat shrinkage film of covering, coated side is carried out add Heat, the surface that coated side can be made to shrink and be tensioned to wing skeleton lifts the pneumatic insurance on wing skeleton surface and covering further Effect.
Brief description
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 perspective view of the solar powered aircraft wing of the embodiment of the present invention.
Fig. 3 is the structural representation of the flexible solar cell assembly in the embodiment of the present invention.
Marginal data:1st, wing skeleton;11st, groove;2nd, flexible solar cell assembly;21st, encapsulate covering;211st, coat Side;22nd, assembly skeleton;221st, the first packaging adhesive film;222nd, flexible solar cell array;2221st, solar cell piece;2222nd, photovoltaic Welding;223rd, the second packaging adhesive film;224th, inside panel;225th, the 3rd packaging adhesive film;226th, support member.
Specific embodiment
Below in conjunction with Figure of description and concrete preferred embodiment, the invention will be further described, but not therefore and Limit 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 assembly 2, The middle part of wing skeleton 1 upper surface is provided with groove 11, and flexible solar cell assembly 2 includes encapsulating covering 21 and located at encapsulation covering The assembly skeleton 22 of 21 lower surfaces, in groove 11, encapsulation covering 21 is along wing skeleton 1 spanwise for assembly skeleton 22(As Shown in the arrow of Fig. 1)Both sides stretch out formation coated side 211, coated side 211 is coated on wing skeleton 1.I.e. flexibility is too The skin of positive battery component 2 extends to the skin of wing skeleton 1, and this structure greatly improves solar battery group Part and the conformal effect of wing skeleton and the surface flatness of wing, are greatly improved the flight aeroperformance of solar energy unmanned plane And reliability.
In the present embodiment, the depth of groove 11 is consistent with the thickness H of assembly skeleton 1, improves solar cell further Assembly and the conformal effect of wing skeleton and the surface flatness of wing.
In the present embodiment, encapsulation covering 21 is PET heat shrinkage film, and thickness is 25 μm, and transmitance is 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, assembly skeleton 22 includes the first packaging adhesive film 221, flexibility too from top to bottom successively Positive cell array 222, the second packaging adhesive film 223, inside panel 224, the 3rd packaging adhesive film 225 and support member 226;
In other examples, assembly skeleton 22 can also be to include the first packaging adhesive film 221, flexibility from bottom to up successively too Positive cell array 222, the second packaging adhesive film 223, support member 226, the 3rd packaging adhesive film 225 and inside panel 224.
In the present embodiment, support member 226 is polymethacrylimide foam plate, and thickness is 0.5mm, and density is 50 Kg/ m3, the flexibility of flexible solar cell assembly 2 after encapsulation 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, and thickness is 100 microns, The thickness of photovoltaic welding belt 2222 is 0.08mm, and the gap between cell piece is 0.5mm.
The flexible solar cell array 222 of the present embodiment, crucial preparation flow is as follows:(1)By wafer thinning technique and super Thin silicon wafer preparation technology prepares multiple crystal silicon solar battery pieces that thickness is 100 microns, this ultra-thin crystal silicon solar battery Piece possesses certain flexibility, and single flexible crystal silicon solar battery chip size size is 40mm × 156mm;(2)Using thickness it is 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 forms flexible solar cell array 222.Solar battery array after thinning Row have certain pliability and bending property it is ensured that flexible solar cell assembly is fitted with the perfection of wing skeleton.
In other examples, solar cell piece 2221 can be that thin film gallium arsenide solar cell piece, CIGS are thin 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 manufacture method of the solar powered aircraft wing of the present embodiment, comprises the following steps:
S1:Prepare wing skeleton 1, and the groove 11 that the middle part processing in wing skeleton 1 upper surface is coordinated with assembly skeleton 22, recessed Groove depth is 0.8mm;
S2:Prepare flexible solar cell assembly 2, flexible solar cell assembly 2 includes encapsulating covering 21 and located at encapsulation covering 21 The assembly skeleton 22 of lower surface, encapsulation covering 21 is heat shrinkage film, and encapsulation covering 21 stretches out shape along the both sides of assembly skeleton 22 Become coated side 211;
In the present embodiment, the preparation method of flexible solar cell assembly is as follows:
First press is encapsulation covering 21, the first packaging adhesive film 221, flexible solar cell array 222, the second packaging adhesive film from top to bottom 223rd, the order of inside panel 224 carries out lamination, carries out first step laminating technology, and laminating temperature is 130 DEG C, and lamination pressure is 80kPa, lamination times are 10min;Then, be cooled to after room temperature after it, by from top to bottom for the first step lamination obtain assembly, After the order lamination of the 3rd packaging adhesive film 225 and support member 226, carry out second step laminating technology, laminating temperature is 80 DEG C, lamination Pressure is 40kPa, and lamination times are 8min.Applicant finds during flexible solar cell assembly one step packaging by hot pressing, gathers Methacrylimide cystosepiment is placed in the bottom of battery component, because material percent thermal shrinkage each in assembly is different, leads to electricity There is slight warpage in pond assembly, reliability becomes poor.By two step laminating technologies, releasably because material percent thermal shrinkage difference is made The assembly warping phenomenon becoming.
In other examples, the preparation method of flexible solar cell assembly can also be as follows:
First press is encapsulation covering 21, the first packaging adhesive film 221, flexible solar cell array 222, the second packaging adhesive film from top to bottom 223rd, the order of support member 226, the 3rd packaging adhesive film 225 and inside panel 224 carries out lamination, then is laminated, and laminating temperature is 80 DEG C~150 DEG C, lamination pressure is 15 kPa~100kPa, and lamination times are 5min~30min.
S3:Assembly skeleton 22 is placed in groove 11, coated side 211 is arranged along the spanwise of wing skeleton 1, by opening Tight mechanism makes flexible solar cell assembly 2 be in tensioning state, and with polyurethane adhesive, coated side 211 is fitted in wing skeleton 1 Curved surfaces on, polyurethane adhesive is heating and curing, solidification temperature be 80 DEG C, hardening time 60min.After adhesive curing, Flexible solar cell assembly 2 has been fixed on the surface of wing skeleton 1 it is achieved that flexible solar cell assembly 2 exists by coated side 211 The perfect laminating on wing skeleton 1 surface, improves the pneumatic safety effect on wing skeleton surface and covering.And, with existing Solar powered aircraft wing manufacturing process is compared, and enormously simplify the installation procedure in solar energy unmanned plane for the solar module, And fixed weight is installed greatly reduce, thus the load-carrying ability of solar energy unmanned plane is greatly improved.
In the present embodiment, the coated side 211 positioned at assembly skeleton 22 both sides extends to from the upper surface of wing skeleton 1 respectively Lower surface simultaneously contacts, namely the upper and lower surface of whole wing skeleton 1 is coated by encapsulation covering 21, improves wing further Skeleton surface and the pneumatic safety effect of covering.
S4:Coated side 211 is heated, heating-up 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 on wing skeleton surface and covering.
In other examples, heating-up temperature can also be 60 DEG C~200 DEG C, can reach same or analogous 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, 15 minutes~7 days hardening time.
The above is only the preferred embodiment of the present invention, and protection scope of the present invention is not limited merely to above-mentioned enforcement Example.All technical schemes belonging under thinking of the present invention belong to protection scope of the present invention.It is noted that for the art Those of ordinary skill for, improvements and modifications under the premise without departing from the principles of the invention, these improvements and modifications also should It is considered as protection scope of the present invention.

Claims (17)

1. a kind of solar powered aircraft wing, including wing skeleton(1)With flexible solar cell assembly(2)It is characterised in that it is described Wing skeleton(1)The middle part of upper surface is provided with groove(11), described flexible solar cell assembly(2)Including encapsulation covering(21)With Located at encapsulation covering(21)The assembly skeleton of lower surface(22), described assembly skeleton(22)Located at described groove(11)Interior, described Encapsulation covering(21)Along described wing skeleton(1)The both sides of spanwise stretch out formation coated side(211), described coated side (211)It is coated on wing skeleton(1)On.
2. solar powered aircraft wing according to claim 1 is it is characterised in that described groove(11)Depth with described group Part skeleton(22)Consistency of thickness.
3. solar powered aircraft wing according to claim 1 is it is characterised in that described encapsulation covering(21)For heat shrinkage film.
4. solar powered aircraft wing according to claim 1 it is characterised in that described 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 is it is characterised in that the thickness of described heat shrinkage film is 20 μm~60 μm, transmitance is 80%~100%.
6. the solar powered aircraft wing according to any one of Claims 1 to 5 is it is characterised in that described assembly skeleton(22) Include the first packaging adhesive film from top to bottom successively(221), flexible solar cell array(222), the second packaging adhesive film(223), Inner Mongol Skin(224), the 3rd packaging adhesive film(225)And support member(226);Or described assembly skeleton(22)Include first from bottom to up successively Packaging adhesive film(221), flexible solar cell array(222), the second packaging adhesive film(223), support member(226), the 3rd packaging adhesive film (225)And inside panel(224).
7. solar powered aircraft wing according to claim 6 is it is characterised in that described support member(226)For poly- methyl-prop Alkene acid imide foam plate.
8. solar powered aircraft wing according to claim 7 is it is characterised in that described polymethacrylimide foam plate Thickness be 0.2mm~3mm, density be 30 Kg/m3~100Kg/m3.
9. solar powered aircraft wing according to claim 6 is it is characterised in that described flexible solar cell array(222)Bag Include multiple solar cell pieces(2221)And photovoltaic welding belt(2222), adjacent solar cell piece(2221)By described photovoltaic welding belt (2222)Connect.
10. solar powered aircraft wing according to claim 9 is it is characterised in that described solar cell piece(2221)Including 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 wings according to claim 10 are it is characterised in that described photovoltaic welding belt(2222)Thickness For 0.03mm~0.3mm.
A kind of 12. manufacture methods of solar powered aircraft wing, comprise the following steps:
S1:Prepare wing skeleton(1), and in described wing skeleton(1)Middle part processing and the described assembly skeleton of upper surface(22) The groove of cooperation(11);
S2:Prepare flexible solar cell assembly(2), described flexible solar cell assembly(2)Including encapsulation covering(21)With located at Encapsulation covering(21)The assembly skeleton of lower surface(22), described encapsulation covering(21)Along described assembly skeleton(22)Both sides outside Extend and form coated side(211);
S3:By assembly skeleton(22)It is placed in groove(11)Interior, described coated side(211)Along wing skeleton(1)Spanwise cloth Put, and with bonding agent by coated side(211)It is fixed on wing skeleton(1)Surface.
The manufacture method of 13. solar powered aircraft wings according to claim 12 is it is characterised in that described encapsulation covering (21)For heat shrinkage film, described manufacture method is further comprising the steps of:
S4:To coated side(211)Heated, made coated side(211)Shrink and be tensioned to wing skeleton(1)Surface.
The manufacture method of 14. solar powered aircraft wings according to claim 13 is it is characterised in that described heating-up temperature is 60 DEG C~200 DEG C.
The manufacture method of the 15. solar powered aircraft wings according to claim 12~14 is it is characterised in that described step S2 In, the preparation method of described flexible solar cell assembly is as follows:
First pressing is encapsulation covering from top to bottom(21), the first packaging adhesive film(221), flexible solar cell array(222), second encapsulation Glued membrane(223), inside panel(224)Order 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;Cooling, obtains intermediate module, then by from upper To lower for intermediate module, the 3rd packaging adhesive film(225)And support member(226)Order carry out lamination after, carry out second step lamination Technique, laminating temperature is 50 DEG C~120 DEG C, and lamination pressure is 10 kPa~50kPa, and lamination times are 5min~20min.
The manufacture method of the 16. solar powered aircraft wings according to claim 12~14 is it is characterised in that described step S2 In, the preparation method of described flexible solar cell assembly is as follows:
First pressing is encapsulation covering from top to bottom(21), the first packaging adhesive film(221), flexible solar cell array(222), second encapsulation Glued membrane(223), support member(226), the 3rd packaging adhesive film(225)And inside panel(224)Order carry out lamination, then carry out layer Pressure, laminating temperature is 80 DEG C~150 DEG C, and lamination pressure is 15 kPa~100kPa, and lamination times are 5min~30min.
The manufacture method of the 17. solar powered aircraft wings according to claim 12~14 is it is characterised in that described step S3 In, described bonding agent includes silicon rubber, polyurethane or epoxy resin, and the solidification temperature of described bonding agent is 25 DEG C~80 DEG C, Gu 15 minutes~7 days change time.
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