CN102897330A - Method for reliably connecting flexible thin-film solar cell and airship envelop - Google Patents
Method for reliably connecting flexible thin-film solar cell and airship envelop Download PDFInfo
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- CN102897330A CN102897330A CN2012104033683A CN201210403368A CN102897330A CN 102897330 A CN102897330 A CN 102897330A CN 2012104033683 A CN2012104033683 A CN 2012104033683A CN 201210403368 A CN201210403368 A CN 201210403368A CN 102897330 A CN102897330 A CN 102897330A
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- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
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- Y02E10/50—Photovoltaic [PV] energy
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Abstract
The invention discloses a method for reliably connecting a flexible thin-film solar cell and an airship envelop. According to the method, solar cells are interconnected through brocade silk ropes which penetrate through stainless steel buttonholes, thereby realizing assembly in an array manner; the solar cells and lateral connecting cord fabrics welded on the airship envelop are connected with each other through the brocade silk ropes which penetrate through the stainless steel buttonholes, thereby realizing the reliable connection between a solar cell array and the envelop; and a multi-layer thermal insulation assembly is closely connected with the airship envelop by employing nylon fasteners (groups), thereby realizing the isolation of waste heat of the solar cells and solving the problem of thermal coupling between the solar cells and the airship envelop. The connecting method can be widely applied to various airship platforms which generate power by solar energy and has wide military and civil application prospect.
Description
Technical field
The present invention relates to the interconnection technique of the flexible thin-film solar cell application on dirigible, particularly flexible thin-film solar cell and airship envelope.
Background technology
According to the literature, the connection mode of flexible thin-film solar cell and airship envelope mainly adopts following two kinds: " the ship skin is integrated ", " mounting connection " abroad at present.But the domestic application precedent of flexible thin-film solar cell on dirigible and the report of relevant connection mode of there is no.In the application of solar battery array on dirigible, have the thermal coupling problem of solar cell and airship envelope, solar cell is assembled into the problem of array, the connectivity problem of solar battery array and covering.
Summary of the invention
The present invention is intended to overcome problems of the prior art, the method that provides a kind of flexible thin-film solar cell and airship envelope reliably to be connected, the reliable connection and effective power supply of solar battery array of realizing solar battery array and airship envelope on the dirigible.
In order to achieve the above object, technical scheme provided by the invention is:
A kind of flexible thin-film solar cell and the method that airship envelope reliably is connected comprise following content:
(1) side direction that is provided with A corrosion-resistant steel buttonhole in airship envelope connects cord and A velcro;
(2) at the multilayer insulation assembly B velcro corresponding with the A velcro is set, the multilayer insulation assembly closely is connected with airship envelope with the B velcro by the A velcro;
(3) B corrosion-resistant steel buttonhole is set in the flexible thin-film solar cell both sides of the edge;
(4) with the brocade silk rope that passes B corrosion-resistant steel buttonhole a plurality of flexible thin-film solar cells are connected into solar battery array;
(5) solar battery array is covered on the multilayer insulation assembly, and be connected brocade silk rope with A corrosion-resistant steel buttonhole solar battery array is connected the cord connection with side direction with passing B corrosion-resistant steel buttonhole.
Particularly, described method comprises the steps:
(1) airship envelope is divided into the zone that several need to connect flexible thin-film solar cell, two of each region divisions parallel and connect cord with the side direction of A corrosion-resistant steel buttonhole;
(2) airship envelope need to connect flexible thin-film solar cell region division several be used for connecting A velcros of multilayer insulation assembly;
(3) at the multilayer insulation assembly several B velcros corresponding with the A velcro are set, the multilayer insulation assembly closely is connected with airship envelope with the B velcro by the A velcro;
(4) B corrosion-resistant steel buttonhole is set in the flexible thin-film solar cell both sides of the edge;
(5) pass B corrosion-resistant steel buttonhole on the flexible thin-film solar cell with brocade silk rope, a plurality of flexible thin-film solar cells are coupled together, be assembled into solar battery array;
(6) solar battery array is covered on the multilayer insulation assembly, then the B corrosion-resistant steel buttonhole with the solar battery array both sides connects by brocade silk rope is connected respectively cord with two side direction A corrosion-resistant steel buttonhole, finishes solar battery array is connected cord with side direction connection;
(7) at solar battery array two ends welding end to windproof cord.
Wherein, described side direction connection cord is welded in the airship envelope; Described A velcro is sewed in airship envelope; Described multilayer insulation assembly is comprised of the reflecting horizon of reflected radiation heat and the wall of insulating heat conduction holes heat.
In addition, said method also comprises with the metal bus-bar each flexible thin-film solar cell connection in series-parallel connection in the solar battery array, the step that then the metal bus-bar is connected with dirigible connection box terminal.
The invention will be further described below in conjunction with principle:
In the method for the present invention, the side direction of having riveted the corrosion-resistant steel buttonhole in the welding of airship envelope relevant position with high-frequency welder connects cord; By sewing in the velcro of airship envelope and multilayer insulation assembly, multilayer insulation material is connected with the tight of covering, wherein, the multilayer insulation assembly is one of Main Means of spacecraft passive thermal control, have fabulous heat-proof quality, the equivalent heat conductivity of multilayer insulation material can hang down to 10 in theory
-5W/ (mK), its basic structure is comprised of the reflecting horizon of reflected radiation heat and the wall of insulating heat conduction holes heat; By passing the brocade silk rope of the corrosion-resistant steel buttonhole that is riveted on flexible thin-film solar cell encapsulating film edge, a plurality of solar cells are coupled together, form solar battery array; Be connected the brocade silk rope of the corrosion-resistant steel buttonhole of cord by passing the solar battery array edge with side direction, solar battery array be connected cord with side direction couple together.The multilayer insulation assembly of arranging between solar cell and the airship envelope avoids solar cell used heat that airship envelope is exerted an influence in order to the transmission of isolated heat.The end of coordinating mutually at airship envelope relevant position welding and solar battery array longitudinal size with high-frequency welder can reduce the air incoming flow to the impact of solar battery array to windproof cord.The connection in series-parallel that realizes solar cell by the metal bus-bar connects, and is flowed at last the connection box terminal, with electric power supply to the dirigible load.
Compared with prior art, beneficial effect of the present invention is:
The used heat of solar cell has a significant impact the mechanical property of airship envelope, therefore to avoid the thermal coupling between solar cell and the airship envelope as far as possible, the present invention is firmly isolated with heat by arranging multiplayer insulating assembly between the two, can effectively address this problem; The intensity of solar radiation in high-altitude (height above sea level 20km) is at 1265W/m
2About, daytime, the solar cell temperature can up to 80 ℃, by the gap location between solar cell and solar cell package film edge place stickup thermal control coating, can effectively reduce absorption/transmitting ratio.Solar battery array is comprised of a plurality of solar cells, by passing the brocade silk rope of the corrosion-resistant steel buttonhole that is riveted on the solar cell package film edge, the mutual series winding of a plurality of solar cells is connect, both realized the assembling of solar battery array, guaranteed again in prominent wind load situation, to possess good extension toughness; Be riveted on the solar cell package film edge is connected the corrosion-resistant steel buttonhole of cord with side direction brocade silk rope by passing, both realized that solar cell was connected the reliable connection of cord with side direction, guaranteed again in prominent wind load situation, to possess good extension toughness.By the metal bus-bar each solar cell connection in series-parallel is connected, being flowed at last can be with electric power supply to the dirigible load on the terminal of connection box.In addition, because therefore the characteristic of facining the wind of dirigible will avoid wind to carry impact as far as possible, by effectively avoiding the air incoming flow on the impact of connection structure at the welding of airship envelope relevant position and the end that the solar battery array longitudinal size is coordinated mutually to windproof cord.
In a word, the method that flexible thin-film solar cell of the present invention and airship envelope reliably are connected, it is strong both to have possessed wind loading rating, connect reliable, can realize again effective power supply of solar cell, can be widely used in utilizing the airship platform of solar electrical energy generation, possess extensive military and civilian application prospect.
Description of drawings
Fig. 1 is for adopting the inventive method with flexible thin-film solar cell and structural representation after airship envelope is connected;
Fig. 2 is the partial enlarged drawing at A place among Fig. 1;
Fig. 3 is the partial enlarged drawing at B place among Fig. 1.
Among the figure: the 1-airship envelope, the 2-A velcro, 3-B velcro (mother), the 4-side direction connects cord, 5-multilayer insulation assembly, 6-A corrosion-resistant steel buttonhole, the 7-flexible thin-film solar cell, 8-holds to windproof cord, 9-brocade silk rope, 10-metal bus-bar, 11-connection box, 12-B corrosion-resistant steel buttonhole.
The specific embodiment
Embodiment 1
Referring to Fig. 1 to Fig. 3, a kind of flexible thin-film solar cell comprises the steps: with the method that airship envelope reliably is connected
(1) airship envelope 1 is divided into the zone that several need to connect flexible thin-film solar cell 7, two of each region divisions parallel and connect cord 4 with the side direction of A corrosion-resistant steel buttonhole 6;
(2) airship envelope 1 need to connect flexible thin-film solar cell 7 region division several be used for connecting A velcros 2 of multilayer insulation assembly 5;
(3) at multilayer insulation assembly 5 several are set and take 2 with A nylon and buckle corresponding B velcro 3, multilayer insulation assembly 5 is connected with the B velcro by A velcro 2 closely is connected with airship envelope 1;
(4) in flexible thin-film solar cell 7 both sides of the edge B corrosion-resistant steel buttonhole 12 is set;
(5) with the brocade silk rope 9 B corrosion-resistant steel buttonholes 12 that pass on the flexible thin-film solar cell 7, a plurality of flexible thin-film solar cells 7 are coupled together, be assembled into solar battery array;
(6) solar battery array is covered on the multilayer insulation assembly 5, then the B corrosion-resistant steel buttonhole 12 with the solar battery array both sides connects by brocade silk rope 9 is connected respectively cord 4 with two side direction A corrosion-resistant steel buttonhole 6, finishes solar battery array is connected cord 4 with side direction connection;
(7) at solar battery array two ends welding end to windproof cord 8;
(8) with metal bus-bar 10 each flexible thin-film solar cell 7 connection in series-parallel in the solar battery array are connected, then metal bus-bar 10 is connected with dirigible connection box 11 terminals.
Wherein, described side direction connection cord 4 is welded in the airship envelope 1; Described A velcro 2 is sewed in airship envelope; Described multilayer insulation assembly 5 is comprised of the reflecting horizon of reflected radiation heat and the wall of insulating heat conduction holes heat.
Claims (6)
1. a flexible thin-film solar cell and the method that airship envelope reliably is connected is characterized in that described method comprises following content:
(1) side direction that is provided with A corrosion-resistant steel buttonhole in airship envelope connects cord and A velcro;
(2) at the multilayer insulation assembly B velcro corresponding with the A velcro is set, the multilayer insulation assembly closely is connected with airship envelope with the B velcro by the A velcro;
(3) B corrosion-resistant steel buttonhole is set in the flexible thin-film solar cell both sides of the edge;
(4) with the brocade silk rope that passes B corrosion-resistant steel buttonhole a plurality of flexible thin-film solar cells are connected into solar battery array;
(5) solar battery array is covered on the multilayer insulation assembly, and be connected brocade silk rope with A corrosion-resistant steel buttonhole solar battery array is connected the cord connection with side direction with passing B corrosion-resistant steel buttonhole.
2. the method for claim 1 is characterized in that, described method specifically comprises the steps:
(1) airship envelope is divided into the zone that several need to connect flexible thin-film solar cell, two of each region divisions parallel and connect cord with the side direction of A corrosion-resistant steel buttonhole;
(2) airship envelope need to connect flexible thin-film solar cell region division several be used for connecting A velcros of multilayer insulation assembly;
(3) at the multilayer insulation assembly several B velcros corresponding with the A velcro are set, the multilayer insulation assembly closely is connected with airship envelope with the B velcro by the A velcro;
(4) B corrosion-resistant steel buttonhole is set in the flexible thin-film solar cell both sides of the edge;
(5) pass B corrosion-resistant steel buttonhole on the flexible thin-film solar cell with brocade silk rope, a plurality of flexible thin-film solar cells are coupled together, be assembled into solar battery array;
(6) solar battery array is covered on the multilayer insulation assembly, then the B corrosion-resistant steel buttonhole with the solar battery array both sides connects by brocade silk rope is connected respectively cord with two side direction A corrosion-resistant steel buttonhole, finishes solar battery array is connected cord with side direction connection;
(7) at solar battery array two ends welding end to windproof cord.
3. the method for claim 1 is characterized in that, described side direction connects cord and is welded in the airship envelope.
4. the method for claim 1 is characterized in that, described A velcro is sewed in airship envelope.
5. the method for claim 1 is characterized in that, described multilayer insulation assembly is comprised of the reflecting horizon of reflected radiation heat and the wall of insulating heat conduction holes heat.
6. such as each described method of claim 1 to 5, it is characterized in that, described method also comprises with the metal bus-bar each flexible thin-film solar cell connection in series-parallel connection in the solar battery array, the step that then the metal bus-bar is connected with dirigible connection box terminal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201210403368.3A CN102897330B (en) | 2012-10-22 | 2012-10-22 | Method for reliably connecting flexible thin-film solar cell and airship envelop |
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| CN201210403368.3A CN102897330B (en) | 2012-10-22 | 2012-10-22 | Method for reliably connecting flexible thin-film solar cell and airship envelop |
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| CN102897330A true CN102897330A (en) | 2013-01-30 |
| CN102897330B CN102897330B (en) | 2015-02-11 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104967396A (en) * | 2015-07-23 | 2015-10-07 | 北京天航华创科技股份有限公司 | Flexible solar cell module of hasp connection type, and development scheme therefor |
| CN108163180A (en) * | 2017-11-22 | 2018-06-15 | 北京天恒长鹰科技股份有限公司 | Stratospheric airship solar cell fixing means |
| CN112542526A (en) * | 2020-12-10 | 2021-03-23 | 中国电子科技集团公司第三十八研究所 | Solar cell array combination device for aerostat and installation method |
| CN112636446A (en) * | 2020-12-29 | 2021-04-09 | 中国人民解放军国防科技大学 | Power supply system of quick response small satellite |
| US11541980B2 (en) | 2016-10-24 | 2023-01-03 | Sceye Sa | Airship construction and method where a harness-structure is fastened around a hull |
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| JP2000280988A (en) * | 1999-03-31 | 2000-10-10 | Sanyo Electric Co Ltd | Installing method of solar battery for airship and airship with solar battery |
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| JP2001253392A (en) * | 2000-03-08 | 2001-09-18 | Natl Aerospace Lab | Solar battery attaching structure and method for installing it |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104967396A (en) * | 2015-07-23 | 2015-10-07 | 北京天航华创科技股份有限公司 | Flexible solar cell module of hasp connection type, and development scheme therefor |
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| US11541980B2 (en) | 2016-10-24 | 2023-01-03 | Sceye Sa | Airship construction and method where a harness-structure is fastened around a hull |
| CN108163180A (en) * | 2017-11-22 | 2018-06-15 | 北京天恒长鹰科技股份有限公司 | Stratospheric airship solar cell fixing means |
| CN112542526A (en) * | 2020-12-10 | 2021-03-23 | 中国电子科技集团公司第三十八研究所 | Solar cell array combination device for aerostat and installation method |
| CN112636446A (en) * | 2020-12-29 | 2021-04-09 | 中国人民解放军国防科技大学 | Power supply system of quick response small satellite |
| CN112636446B (en) * | 2020-12-29 | 2022-03-01 | 中国人民解放军国防科技大学 | Power supply system of quick response small satellite |
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| CN102897330B (en) | 2015-02-11 |
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Effective date of registration: 20160517 Address after: Three Hunan province Changsha Fenglin Road 410205 No. 217 Patentee after: HUNAN AEROSPACE YUANWANG SCIENCE & TECHNOLOGY Co.,Ltd. Address before: 585 box 3, box 410205, Changsha City, Hunan Province Patentee before: Hunan Aerospace Electromechanical Equipment and Special Material Institute |
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Effective date of registration: 20230419 Address after: 410205 Building 2, Hunan Space Administration Industrial Zone, No. 217, Fenglin Third Road, Yuelu District, Changsha City, Hunan Province Patentee after: HUNAN AEROSPACE YUANWANG SCIENCE & TECHNOLOGY Co.,Ltd. Patentee after: BEIJING MECHANICAL AND ELECTRICAL ENGINEERING GENERAL DESIGN DEPARTMENT Address before: No.217, Fenglin Third Road, Changsha City, Hunan Province, 410205 Patentee before: HUNAN AEROSPACE YUANWANG SCIENCE & TECHNOLOGY Co.,Ltd. |