CN106585956A - Integrated shaping method and structure for thin silicon solar cell module of large-size wing - Google Patents
Integrated shaping method and structure for thin silicon solar cell module of large-size wing Download PDFInfo
- Publication number
- CN106585956A CN106585956A CN201610957607.8A CN201610957607A CN106585956A CN 106585956 A CN106585956 A CN 106585956A CN 201610957607 A CN201610957607 A CN 201610957607A CN 106585956 A CN106585956 A CN 106585956A
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- China
- Prior art keywords
- thin silicon
- silicon solar
- solar module
- large scale
- wing
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/20—Integral or sandwich constructions
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
-
- 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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/50—On board measures aiming to increase energy efficiency
Abstract
The invention relates to an integrated shaping method and structure for a thin silicon solar cell module of a large-size wing. The integrated shaping method for the thin silicon solar cell module of the large-size wing comprises the following steps of A) laying a thin silicon solar cell module on the curved surface of the wing; B) packaging the thin silicon solar cell module by using a wing surface skin; and C) extracting air in the package; and under a negative pressure effect, exerting the thin silicon solar cell module to be laminated with the curved surface of the wing in a sealed way and exerting the wing surface skin to be laminated with the thin silicon solar cell module and the curved surface of the wing so that integrated shaping of the thin silicon solar cell module is realized. The invention relates to the integrated shaping method and structure for the thin silicon solar cell module of the large-size wing; and technical problems that the laying difficulty of the thin silicon solar cell module of the large-size wing is great and the laying process is easy to damage are solved.
Description
Technical field
The present invention relates to large scale（More than 50cm × 50cm）The pavement technique of thin silicon solar module on wing, specifically
It is related to the thin silicon solar module integration shaping method and structure of a kind of large scale wing.
Background technology
Solar energy unmanned plane is by the use of solar radiation can in high-altitude non-stop flight, more than several weeks nobody drives as power
Aircraft is sailed, it is converted solar energy into electrical energy using photocell, flying power is produced by the rotation of motor-driven screw.
The solar energy unmanned plane cruise time is long, and flying height is high, and overlay area is wide, multiple-task can be performed, with conventional aircraft
Irreplaceable advantage.Thin silicon solar cell due to its lightweight, efficiently, cost it is relatively low, in unmanned plane and stratospheric airship
It is quite varied using in, it is a new focus of various countries' aircraft industry research.
Thin silicon solar cell is mated formation extremely difficult on body platform.Thin silicon solar cell thickness is little, poor rigidity, easily
It is broken easily to split, during larger for the less wing curved surface of chord length of mating formation or wing flexural deformation position, thin silicon solar battery sheet
It is easy to hidden the splitting of generation even to rupture, directly contributes the decline of solar array power output.
The content of the invention
It is an object of the invention to provide a kind of large scale wing thin silicon solar module integration shaping method and
Structure, solves large scale wing thin silicon solar module and mats formation difficulty greatly, the flimsy technical problem of pavement process.
To achieve the above object, the present invention provides a kind of thin silicon solar module integration tax of large scale wing
Shape method, including：A）Thin silicon solar module is layered on wing curved surface；B）Encapsulated with aerofoil surface covering described thin
Silicon solar cell component；C）Extract the air in encapsulation, under suction function, the thin silicon solar module and wing curved surface out
Surface, aerofoil surface covering and the thin silicon solar module and wing curved surface palette, realize thin silicon sun electricity
Pond component integration figuration.
The thin silicon solar module integration shaping method of above-mentioned large scale wing, wherein, spread thin silicon solar cell
Before component, the integrated shaping method also includes that large scale wing curved surface clears up smooth, free from admixture.
The thin silicon solar module integration shaping method of above-mentioned large scale wing, wherein, step A）In, thin silicon
Solar module face down, the i.e. front of thin silicon solar module are contacted with the curved surface of large scale wing.
The thin silicon solar module integration shaping method of above-mentioned large scale wing, wherein, step B）Including：
Thin silicon solar module is away from uniform coating packaging plastic on the surface of large scale wing curved surface；By aerofoil surface covering
It is covered on the thin silicon solar module for applying packaging plastic；On aerofoil surface covering, thin silicon solar module four
Week installs sealing strip.
The thin silicon solar module integration shaping method of above-mentioned large scale wing, wherein, the chi of aerofoil surface covering
The very little size more than thin silicon solar module.
The thin silicon solar module integration shaping method of above-mentioned large scale wing, wherein, step C）Including：
A position punching is taken on aerofoil surface covering, between thin silicon solar module and sealing strip；Pass through machine in punch position
Tool pumping gas, makes encapsulation be internally formed negative pressure.
Another technical scheme that the present invention is provided is a kind of large scale wing thin silicon solar module integration figuration knot
Structure, including thin silicon solar module, aerofoil surface covering and sealing strip；The thin silicon solar module is layered on big chi
On the curved surface of very little wing, the thin silicon solar module is sealed under suction function with large scale wing curved surface
Laminating；The aerofoil surface covering is covered on the thin silicon solar module, and the aerofoil surface covering is made in negative pressure
With lower and thin silicon solar module and large scale wing curved surface palette；The sealing strip is arranged on the wing
On skin, the surrounding of the thin silicon solar module；In the aerofoil surface covering and the thin silicon solar-electricity
Fluid sealant is coated between the component of pond.
Above-mentioned large scale wing thin silicon solar module integration figuration structure, wherein, the thin silicon solar cell
The front of component contacts with the curved surface of large scale wing.
Above-mentioned large scale wing thin silicon solar module integration figuration structure, wherein, the packaging plastic is insulating cement.
Compared with prior art, the solution have the advantages that：
1）Large area can be met to mat formation thin silicon solar cell, can ensure that what thin silicon solar cell was combined with unmanned plane covering again
During uniform force, at utmost reduce battery module during thin silicon solar cell is attached it is hidden split, the situation of fragmentation, so as to
Technology difficulty is greatly reduced, processing quality is improve；
2）The thin silicon solar module integration shaping method of the large scale wing of the present invention, it is relatively low to equipment requirement and thin
Silicon solar cell component figuration is quick, quality is high.
Description of the drawings
The thin silicon solar module integration shaping method of the large scale wing of the present invention and structure are by following enforcement
Example and accompanying drawing are given.
Fig. 1 is the thin silicon solar module integration shaping method side of large scale wing in present pre-ferred embodiments
Schematic diagram.
Fig. 2 is the thin silicon solar module integration shaping method front of large scale wing in present pre-ferred embodiments
Schematic diagram.
Fig. 3 is that the thin silicon solar module integration shaping method of large scale wing in present pre-ferred embodiments is completed
Trailing flank schematic diagram.
Specific embodiment
Below with reference to thin silicon solar module integration figuration sides of Fig. 1～Fig. 3 to the large scale wing of the present invention
Method and structure are described in further detail.
The thin silicon solar module integration shaping method of the large scale wing of the present invention is applied in large scale wing
Curved surface is mated formation thin silicon solar module.
The thin silicon solar module integration shaping method of the large scale wing of the present invention includes：By thin silicon solar cell
Component is layered on wing curved surface；The thin silicon solar module is encapsulated with aerofoil surface covering；Extract the sky in encapsulation out
Gas, under suction function, the thin silicon solar module and wing curved surface, aerofoil surface covering and the thin silicon sun
Battery component and wing curved surface palette, realize thin silicon solar module integration figuration.
The thin silicon solar module integration shaping method of the large scale wing of the present invention can ensure that thin silicon sun electricity
Pond component combined with wing cover during uniform force, at utmost reduce thin silicon solar module pavement process in electricity
Pond module is hidden to be split, the situation of fragmentation.
The thin silicon solar module integration for now describing the large scale wing of the present invention in detail with a preferred embodiment is assigned
Shape method.
The present embodiment is mated formation thin silicon solar module in large scale wing concave surface.
Referring to Fig. 1 and Fig. 2, the thin silicon solar module integration shaping method of the large scale wing of the present embodiment includes
Following steps：
1）The face down of thin silicon solar module 2 is layered in the concave surface of large scale wing 1, i.e. thin silicon solar cell
The front of component 2 contacts with the concave surface of large scale wing 1；
Before paving thin silicon solar module 2, the concave surface of large scale wing 1 should clear up smooth, free from admixture；
2）Packaging plastic 3 is evenly coated in into the back side of thin silicon solar module 2；
The packaging plastic 3 is insulating cement；
3）Aerofoil surface covering 4 is covered on the thin silicon solar module for applying packaging plastic；
, more than the size of thin silicon solar module 2, aerofoil surface covering 4 is by the thin silicon sun for the size of aerofoil surface covering 4
Energy battery component 2 is covered all；
4）On aerofoil surface covering 4, the surrounding of thin silicon solar module 2 installation sealing strip 6；
Sealing strip 6 should fully encase the surrounding of thin silicon solar module 2, to prevent gas leakage around；
To step 4）It is achieved that encapsulation of the aerofoil surface covering 4 to thin silicon solar module 2；
5）A position punching 5, hole depth are taken on aerofoil surface covering 4, between thin silicon solar module 2 and sealing strip 6
Through aerofoil surface covering 4；
6）It is evacuated by mechanical pump in punch position, makes encapsulation be internally formed negative pressure, promotes aerofoil surface covering 4 and the thin silicon sun
Can battery component 2 attach smooth, and fit naturally with large scale wing concave surface, promote thin silicon solar module 2 with it is big
Size wing concave surface is fitted naturally, keeps completing the thin silicon solar panel of large scale wing after negative pressure state certain hour
Part integration figuration, as shown in Figure 3.
The method can by the speed of exhaust and pumpdown time control thin silicon solar module figuration pressure and when
Between, to greatest extent reduce curved surface wing thin silicon solar module fragment rate and it is hidden split appearance, greatly improve the thin silicon sun
Can battery component mat formation quality.
Another technical scheme that the present embodiment is provided is a kind of large scale wing thin silicon solar module integration figuration
Structure, including thin silicon solar module 2, aerofoil surface covering 4 and sealing strip 6；The thin silicon solar module 2 spreads
In the concave surface of large scale wing 1, under suction function, the thin silicon solar module 2 and the recessed table of large scale wing
Face palette；The aerofoil surface covering 4 is covered on the thin silicon solar module 2, the aerofoil surface covering 4
With thin silicon solar module 2 and large scale wing concave surface palette under suction function；The sealing strip 6 is arranged on
On the aerofoil surface covering 4, the surrounding of the thin silicon solar module 2；It is thin with described in the aerofoil surface covering 4
Fluid sealant 3 is coated between silicon solar battery assembly 2.
Claims (9)
1. large scale wing thin silicon solar module integration shaping method, it is characterised in that include：A）By the thin silicon sun
Battery component is layered on wing curved surface；B）The thin silicon solar module is encapsulated with aerofoil surface covering；C）Extract envelope out
Air in dress, under suction function, the thin silicon solar module and wing curved surface, aerofoil surface covering with it is described
Thin silicon solar module and wing curved surface palette, realize thin silicon solar module integration figuration.
2. large scale wing as claimed in claim 1 thin silicon solar module integration shaping method, it is characterised in that
Before paving thin silicon solar module, the integrated shaping method also includes that large scale wing curved surface clears up smooth, nothing
Impurity.
3. large scale wing as claimed in claim 1 thin silicon solar module integration shaping method, it is characterised in that
Step A）In, thin silicon solar module face down, the i.e. front of thin silicon solar module and large scale wing
Curved surface contact.
4. large scale wing as claimed in claim 1 thin silicon solar module integration shaping method, it is characterised in that
Step B）Including：The uniform coating encapsulation on surface of the thin silicon solar module away from large scale wing curved surface
Glue；Aerofoil surface covering is covered on the thin silicon solar module for applying packaging plastic；On aerofoil surface covering, thin silicon
Solar module surrounding installs sealing strip.
5. large scale wing as claimed in claim 1 thin silicon solar module integration shaping method, it is characterised in that
Size of the size of aerofoil surface covering more than thin silicon solar module.
6. large scale wing as claimed in claim 4 thin silicon solar module integration shaping method, it is characterised in that
Step C）Including：A position punching is taken on aerofoil surface covering, between thin silicon solar module and sealing strip；
It is evacuated by mechanical pump in punch position, makes encapsulation be internally formed negative pressure.
7. large scale wing thin silicon solar module integration figuration structure, it is characterised in that including thin silicon solar cell
Component, aerofoil surface covering and sealing strip；The thin silicon solar module is layered on the curved surface of large scale wing, institute
State thin silicon solar module under suction function with large scale wing curved surface palette；The aerofoil surface covering
Be covered on the thin silicon solar module, the aerofoil surface covering under suction function with thin silicon solar battery group
Part and large scale wing curved surface palette；The sealing strip be arranged on the aerofoil surface covering on, the thin silicon too
The surrounding of positive energy battery component；Sealing is coated between the aerofoil surface covering and the thin silicon solar module
Glue.
8. large scale wing thin silicon solar module as claimed in claim 7 integration figuration structure, it is characterised in that institute
The front for stating thin silicon solar module contacts with the curved surface of large scale wing.
9. large scale wing thin silicon solar module as claimed in claim 7 integration figuration structure, it is characterised in that institute
Packaging plastic is stated for insulating cement.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610957607.8A CN106585956B (en) | 2016-11-03 | 2016-11-03 | The thin silicon solar module integration shaping method and structure of large scale wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610957607.8A CN106585956B (en) | 2016-11-03 | 2016-11-03 | The thin silicon solar module integration shaping method and structure of large scale wing |
Publications (2)
| Publication Number | Publication Date |
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| CN106585956A true CN106585956A (en) | 2017-04-26 |
| CN106585956B CN106585956B (en) | 2019-04-12 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201610957607.8A Active CN106585956B (en) | 2016-11-03 | 2016-11-03 | The thin silicon solar module integration shaping method and structure of large scale wing |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
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| CN101665153A (en) * | 2009-09-24 | 2010-03-10 | 南昌航空大学 | Plane wing with solar battery |
| KR20130059022A (en) * | 2011-11-28 | 2013-06-05 | 한국과학기술연구원 | Wing structure having a solar battery and manufacturing method thereof |
| CN103332290A (en) * | 2013-05-28 | 2013-10-02 | 北京航空航天大学 | Wing structure-solar cell integrated module and development method thereof |
| US20140224298A1 (en) * | 2011-07-18 | 2014-08-14 | James L. Grimsley | Solar Assembly and Method of Forming Same |
| CN104210647A (en) * | 2014-09-22 | 2014-12-17 | 北京航空航天大学 | Wing structure-meshed solar wing design and development scheme |
| CN104229120A (en) * | 2014-09-22 | 2014-12-24 | 北京航空航天大学 | Solar wing structure of aircraft based on photothermal integrated composite energy |
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2016
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Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101665153A (en) * | 2009-09-24 | 2010-03-10 | 南昌航空大学 | Plane wing with solar battery |
| US20140224298A1 (en) * | 2011-07-18 | 2014-08-14 | James L. Grimsley | Solar Assembly and Method of Forming Same |
| KR20130059022A (en) * | 2011-11-28 | 2013-06-05 | 한국과학기술연구원 | Wing structure having a solar battery and manufacturing method thereof |
| CN103332290A (en) * | 2013-05-28 | 2013-10-02 | 北京航空航天大学 | Wing structure-solar cell integrated module and development method thereof |
| CN104210647A (en) * | 2014-09-22 | 2014-12-17 | 北京航空航天大学 | Wing structure-meshed solar wing design and development scheme |
| CN104229120A (en) * | 2014-09-22 | 2014-12-24 | 北京航空航天大学 | Solar wing structure of aircraft based on photothermal integrated composite energy |
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|---|---|---|---|---|
| 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 |
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| CN106585956B (en) | 2019-04-12 |
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