CN202423344U - Solar battery and unmanned aerial vehicle applying same - Google Patents
Solar battery and unmanned aerial vehicle applying same Download PDFInfo
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- CN202423344U CN202423344U CN2012200275424U CN201220027542U CN202423344U CN 202423344 U CN202423344 U CN 202423344U CN 2012200275424 U CN2012200275424 U CN 2012200275424U CN 201220027542 U CN201220027542 U CN 201220027542U CN 202423344 U CN202423344 U CN 202423344U
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- solar cell
- solar battery
- unmanned plane
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- 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
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- 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
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Abstract
The embodiment of the utility model discloses a solar battery and an unmanned aerial vehicle applying the same. The solar battery comprises a solar battery bunch formed by a solar battery piece with a preset thickness through a laser welding technology, wherein the solar battery bunch comprises a welding belt and a confluence belt, and the section plane of the welding belt has an arc-shaped structure. The solar battery provided by the utility model can meet the requirement that the unmanned aerial vehicle requires a power source with smaller weight because the solar battery piece is thinner, and the flexibility of the solar battery is improved to some extent; the laser welding technology is adopted to reduce the welding stress of the surface of the solar battery, so as to meet the bending requirement when the solar battery is applied to the unmanned aerial vehicle; and the welding belt in the solar battery bunch and the section plane of the confluence belt both have arc-shaped structures, thereby meeting the loading requirement of the unmanned aerial vehicle. Therefore, the solar battery provided by the utility model has the advantages that the weight is smaller, and the loading requirement of the unmanned aerial vehicle can be met.
Description
Technical field
The utility model relates to technical field of solar cell manufacturing, relates in particular to a kind of solar cell and uses the unmanned plane of this solar cell.
Background technology
The major impetus of conventional unmanned plane is the common energy, but when carrying out work high above the ground, receives its load-carrying quantitative limitation, can not carry a large amount of fuel, thereby cause its work of can't leaving a blank for a long time.And along with the development of solar battery technology with reach its maturity, and people are to the understanding of new forms of energy, the application of solar cell is more and more widely.No matter be application at aviation field; Still the application in Ground Power Generation System; To application, the development of solar battery technology all is the most rapidly from generating speed, technology maturation property, thereby is impelling the development of solar battery technology on unmanned vehicle virtually.
But; Solar cell of the prior art, thickness is bigger, can not satisfy the lighter demand of its power source weight of unmanned plane requirement; And receive the influence of its packaging technology; General employing electric welding welding forms welding stress in solar cell surface easily in welding process, causes it can not be applicable to the bending needs on the unmanned plane.
The utility model content
For solving the problems of the technologies described above, the utility model embodiment provides a kind of solar cell and has used the unmanned plane of this solar cell, and this solar cell is not only in light weight, and good bending property, can satisfy the demand of unmanned plane.
For addressing the above problem, the utility model embodiment provides following technical scheme:
A kind of solar cell, this solar cell comprises:
The solar cell string that forms through laser welding technology by solar battery sheet with preset thickness; And this solar cell string comprises the welding of the curved structure of section and the band that confluxes.
Preferably, in the above-mentioned solar cell, said preset thickness is 0.1～0.2mm.
Preferably, in the above-mentioned solar cell, said solar cell is divided into a plurality of zones, and each zone is independently battery unit.
The utility model also provides a kind of unmanned plane of using above-mentioned solar cell as power source.
Preferably, in the above-mentioned unmanned plane, the concrete mode that said solar cell is installed on the unmanned plane is: through vacuumizing heating said solar cell integral lamination is encapsulated on the unmanned plane.
Preferably, in the above-mentioned unmanned plane, said unmanned plane utilizes power supply partition management technology, said solar cell is divided into several zones manages, and makes the solar battery cell in each zone be independently electricity generation system.
Compared with prior art, technique scheme has the following advantages:
The solar cell that the utility model embodiment is provided; Solar cell string on it is formed through laser welding technology by the solar battery sheet with preset thickness; Thereby reduced the weight of said solar cell; Make it can satisfy the lighter demand of its power source weight of unmanned plane requirement, and improve the flexibility of said solar cell to a certain extent; And adopt laser welding technology can reduce the welding stress of solar cell surface, the crooked requirement when satisfying it and being used in unmanned plane; Welding in the said solar cell string is arranged again and all curved structure of section of the band that confluxes, this has also satisfied the carriage requirement of unmanned plane, therefore; The solar cell that the utility model provided; Not only weight is lighter, and bending property is wanted, and can satisfy the carriage requirement of unmanned plane.
Description of drawings
In order to be illustrated more clearly in the utility model embodiment or technical scheme of the prior art; To do to introduce simply to the accompanying drawing of required use in embodiment or the description of the Prior Art below; Obviously, the accompanying drawing in describing below only is some embodiment of the utility model, for those of ordinary skills; Under the prerequisite of not paying creative work, can also obtain other accompanying drawing according to these accompanying drawings.
Fig. 1 is the structural representation of the solar cell that the utility model provided;
Fig. 2 is the method for packing schematic flow sheet of the solar cell that the utility model provided.
Illustrated among Fig. 1: backboard 1, EVA glue 2, solar cell string 3, EVA glue 4, substrate 5, arc welding 6.
Embodiment
To combine the accompanying drawing among the utility model embodiment below, the technical scheme among the utility model embodiment is carried out clear, intactly description, obviously, described embodiment only is the utility model part embodiment, rather than whole embodiment.Based on the embodiment in the utility model, those of ordinary skills are not making the every other embodiment that is obtained under the creative work prerequisite, all belong to the scope of the utility model protection.
A lot of details have been set forth in the following description so that make much of the utility model; But the utility model can also adopt other to be different from alternate manner described here and implement; Those skilled in the art can do similar popularization under the situation of the utility model intension, so the utility model does not receive the restriction of following disclosed specific embodiment.
Along with the development of solar-photovoltaic technology, solar-photovoltaic technology has bigger development space at aviation field, thereby makes the development of solar energy unmanned plane become possibility.Conventional relatively unmanned plane, the advantage of solar energy unmanned plane is self-evident.But, said as the background technology part, solar cell of the prior art; Thickness is bigger; Can not satisfy the lighter demand of its power source weight of unmanned plane requirement, and receive the influence of its packaging technology, general employing electric welding welding in welding process; Form welding stress in solar cell surface easily, cause it can not be applicable to the bending needs on the unmanned plane.
In view of this, the utility model provides a kind of solar cell, and is as shown in Figure 1, and the solar cell that the utility model embodiment is provided comprises: the backboard 1 that lays successively, EVA glue 2, solar cell string 3, EVA glue 4 and substrate 5; Wherein, said solar cell string 3 is formed through laser welding technology by the solar battery sheet with preset thickness; And this solar cell string comprises the welding 6 of the curved structure of section and the band that confluxes.
In the solar cell that the utility model provided, the preset thickness of its solar battery sheet is 0.1～0.2mm.Compared to existing technologies, this solar battery sheet is thinner, therefore can satisfy the demand that requires power source lighter on the unmanned plane.And when forming the solar cell string, adopting laser welding technology, said laser welding technology can reduce the welding stress of solar cell surface, the crooked requirement when satisfying it and being used in unmanned plane; Have again, all curved structure of section of the welding 6 between solar battery sheet and the band that confluxes, this has also satisfied the carriage requirement of unmanned plane.
The solar cell that the utility model provided can also be divided into a plurality of independently battery units, and each unit all can independently be generated electricity, thereby damages the phenomenon of whole solar cell electricity generation system can avoid the solar cell local damage time because of local overheating.
As shown in Figure 2, the method for packing of the solar cell that the utility model provided is specially:
Step S1: solar battery sheet is provided.
Because the randomness of solar battery sheet manufacturing conditions; The solar cell piece performance of producing is not quite similar; So, should pass through the solar cell built-in testing, thereby classify according to its performance parameter in order effectively performance unanimity or close battery sheet to be combined.Wherein, The solar cell built-in testing is the output parameter (electric current and voltage) that draws solar battery sheet through test; Big I according to said output parameter is classified to said solar battery sheet, can pick out satisfactory solar battery sheet after the classification, can scrap or recycle for undesirable; This not only can improve the utilance of battery sheet, and can also improve the qualification rate of product.
Step S2: said solar battery sheet is carried out thinning handle, form solar battery sheet with preset thickness.
After said solar battery sheet classified; Utilize ultramicrotomy and etch, the satisfactory solar battery sheet of screen is carried out thinning handle, form solar battery sheet with preset thickness; Wherein, The preset thickness of said solar battery sheet is 0.1～0.2mm, reaching the weight that reduces said solar battery sheet, and improves the purpose of said solar battery sheet flexibility.
Step S3: adopt laser welding technology to weld said solar battery sheet to form the solar cell string, all curved structure of section of the welding in the said solar cell string and the band that confluxes.
After obtaining having the solar battery sheet of preset thickness; Adopt laser welding technology to weld said solar battery sheet to form the solar cell string; Detailed process comprises: with the scolding tin place between the main grid line of bombardment with laser beams to adjacent solar battery sheet front; Said scolding tin absorbs heat and the fusing that laser beam transforms, and the welding between the adjacent solar battery sheet is accomplished in cooling afterwards, between the adjacent solar battery sheet, forms welding; Still adopt as previously mentioned afterwards laser welding technology with the welding of a plurality of weldings with the formation band that confluxes, the solar cell string that final formation is arranged in array.
Through the shape of scolding tin between the adjacent solar battery sheet is set in advance; Make that the cross-section structure of final formed welding is curved; And make the cross-section structure of being with confluxing of final formation curved through relative set, this is in order to satisfy final formed solar cell to be installed to the demand on the unmanned plane.
Adopt laser welding technology to form the solar cell string, compare existing electric welding welding, not only can reduce welding stress, improve the bending property of solar cell; And can make welding on the battery strings, the band that confluxes reaches high accuracy, low distortion, high efficiency compile electric current purpose.
Step S4: said solar cell string is embedded in the EVA glue.
Serial connection is good and lay according to certain level through after the assay was approved solar cell string, substrate, EVA glue, backboard, form solar module, for lamination is prepared.
Concrete laid processes is: with reference to figure 1; One backboard 1 (being generally toughened glass) at first is provided, on backboard 1, is coated with EVA glue 2 then, certainly; Also can between backboard 1 and EVA glue 2, increase one deck flexible polymer in this step, to increase the adhesive strength between backboard 1 and the EVA glue 2; Afterwards solar cell string 3 is embedded in the EVA glue 2; On said solar cell string 3, be coated with EVA glue 4 again; On EVA glue 4, lay substrate 5 (being generally glass) at last.
It should be noted that when laying, guarantee the relative position of storerooms such as said solar cell string 3 and backboard 1, substrate 5, and will adjust the distance of 3 of said solar cell strings, for lamination is laid a good foundation.
Step S5: form solar cell through laminating technology.
The solar cell string assembly that lays is put into laminating machine, through vacuumizing the air in the assembly is extracted out, heating makes the fusing of EVA glue then, thereby solar cell string, backboard and substrate are bonded together; Solar module is taken out in cooling at last, forms solar cell.
The method for packing of the solar cell that the utility model embodiment is provided; Also comprise formed solar cell is divided into a plurality of independently battery units; Carry out partition management; Preventing causing local overheating under the part solar cell damaged condition, and damage the whole solar cell electricity generation system.
By on can know; The method for packing of the solar cell that the utility model embodiment is provided; Adopting solar energy slimline battery process technology, laser welding technology and section to be that the welding of arc and the band that confluxes are technological improves and optimizes solar cell; Guarantee its under unmanned plane particular job condition use and farthest bring into play the efficient of solar cell; Simultaneously can adapt to the bending needs of solar cell on unmanned plane, under the condition of maximum performance solar cell power generation and charge efficiency, alleviate the weight of unmanned plane.And; The method for packing of the solar cell that the utility model embodiment is provided; Also can carry out partition management, preventing causing local overheating under the part solar cell damaged condition, and damage the whole solar cell electricity generation system formed solar cell.
Adopt the formed solar cell of said method; Its thinner thickness, weight is lighter, and has good bendability; What can be used for multiple model is on the unmanned plane or other equipment of power with the photovoltaic generation, has with low cost, in light weight, intensity advantages of higher.
Above-mentioned solar cell is installed on the unmanned plane surface, has just processed a kind of unmanned plane that utilizes said solar cell as power source.Said solar cell produces electric weight through solar light irradiation, for the power supply of unmanned plane carries out boost charge, thereby can make unmanned plane flight for a long time substantially, for unmanned plane flies with security and stability the supply of electric power guarantee is provided.
Therefore, the utility model embodiment also provides a kind of unmanned plane, and the concrete mode that wherein said solar cell is installed on the unmanned plane is: through vacuumizing heating, said solar cell integral lamination is encapsulated on the unmanned plane.And the unmanned plane power supply partition management also capable of using that the utility model embodiment is provided is technological; A plurality of independent batteries unit in the solar cell is carried out partition management; Making the solar battery cell in each zone all is electricity generation system independently, thereby prevents to cause local overheating under the part photovoltaic cell damaged condition and damage whole unmanned plane solar cell power generation system.
Utilize the unmanned plane of described solar cell as power source; Compare with manned aircraft; Have that volume is little, cost is low, easy to use, low, advantage such as battlefield survival is stronger to the operational environment requirement; And the unmanned plane that the utility model embodiment is provided has efficient, nimble investigation effect and stronger antijamming capability, is adapted at using under the various conditions such as war.
Various piece adopts the mode of going forward one by one to describe in this specification, and what each part stressed all is and the difference of other parts that identical similar part is mutually referring to getting final product between the various piece.
Need to prove; " comprising " among the utility model embodiment, " comprising " or its any other variant are intended to contain comprising of nonexcludability; Thereby make and comprise that process, method, article or the equipment of a series of key elements not only comprise those key elements; But also comprise other key elements of clearly not listing, or also be included as this process, method, article or equipment intrinsic key element.Under the situation that do not having much more more restrictions, the key element that limits by statement " comprising ... ", and be not precluded within process, method, article or the equipment that comprises said key element and also have other identical element.
To the above-mentioned explanation of the disclosed embodiments, make this area professional and technical personnel can realize or use the utility model.Multiple modification to these embodiment will be conspicuous concerning those skilled in the art, and defined General Principle can realize under the situation of spirit that does not break away from the utility model or scope in other embodiments among this paper.Therefore, the utility model will can not be restricted to embodiment illustrated herein, but will meet and principle disclosed herein and features of novelty the wideest corresponding to scope.
Claims (6)
1. a solar cell is characterized in that, this solar cell comprises:
The solar cell string that forms through laser welding technology by solar battery sheet with preset thickness; And this solar cell string comprises the welding of the curved structure of section and the band that confluxes.
2. solar cell according to claim 1 is characterized in that, said preset thickness is 0.1～0.2mm.
3. solar cell according to claim 1 is characterized in that said solar cell is divided into a plurality of zones, and each zone is independently battery unit.
4. an application rights requires the unmanned plane of each described solar cell of 1-3 as power source.
5. unmanned plane according to claim 4 is characterized in that, the concrete mode that said solar cell is installed on the unmanned plane is:
Through vacuumizing heating said solar cell integral lamination is encapsulated on the unmanned plane.
6. unmanned plane according to claim 4 is characterized in that, said unmanned plane utilizes power supply partition management technology, said solar cell is divided into several zones manages, and makes the solar battery cell in each zone be independently electricity generation system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012200275424U CN202423344U (en) | 2012-01-20 | 2012-01-20 | Solar battery and unmanned aerial vehicle applying same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012200275424U CN202423344U (en) | 2012-01-20 | 2012-01-20 | Solar battery and unmanned aerial vehicle applying same |
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| Publication Number | Publication Date |
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| CN202423344U true CN202423344U (en) | 2012-09-05 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2012200275424U Expired - Lifetime CN202423344U (en) | 2012-01-20 | 2012-01-20 | Solar battery and unmanned aerial vehicle applying same |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2014173331A1 (en) * | 2013-04-27 | 2014-10-30 | Shenzhen Byd Auto R&D Company Limited | Welding strip for solar battery and solar battery assembly |
| CN105392701A (en) * | 2013-06-28 | 2016-03-09 | 空客集团有限公司 | Aircraft structure with solar energy capture capacity |
-
2012
- 2012-01-20 CN CN2012200275424U patent/CN202423344U/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2014173331A1 (en) * | 2013-04-27 | 2014-10-30 | Shenzhen Byd Auto R&D Company Limited | Welding strip for solar battery and solar battery assembly |
| CN105392701A (en) * | 2013-06-28 | 2016-03-09 | 空客集团有限公司 | Aircraft structure with solar energy capture capacity |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20120905 |