CN111193472A - Flexible solar cell array for near space airship - Google Patents
Flexible solar cell array for near space airship Download PDFInfo
- Publication number
- CN111193472A CN111193472A CN201811359808.3A CN201811359808A CN111193472A CN 111193472 A CN111193472 A CN 111193472A CN 201811359808 A CN201811359808 A CN 201811359808A CN 111193472 A CN111193472 A CN 111193472A
- Authority
- CN
- China
- Prior art keywords
- solar cell
- cell array
- thin film
- rope
- flexible solar
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 239000010409 thin film Substances 0.000 claims abstract description 40
- 239000000463 material Substances 0.000 claims description 6
- 229920002334 Spandex Polymers 0.000 claims description 3
- 238000004026 adhesive bonding Methods 0.000 claims description 3
- 229910021419 crystalline silicon Inorganic materials 0.000 claims description 3
- 239000002657 fibrous material Substances 0.000 claims description 3
- 238000007789 sealing Methods 0.000 claims description 3
- 238000009958 sewing Methods 0.000 claims description 3
- 239000004759 spandex Substances 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 4
- 238000004146 energy storage Methods 0.000 abstract description 2
- 238000010030 laminating Methods 0.000 abstract 1
- 230000003139 buffering effect Effects 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 238000013329 compounding Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005286 illumination Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000000725 suspension Substances 0.000 description 2
- ICXAPFWGVRTEKV-UHFFFAOYSA-N 2-[4-(1,3-benzoxazol-2-yl)phenyl]-1,3-benzoxazole Chemical compound C1=CC=C2OC(C3=CC=C(C=C3)C=3OC4=CC=CC=C4N=3)=NC2=C1 ICXAPFWGVRTEKV-UHFFFAOYSA-N 0.000 description 1
- HBBGRARXTFLTSG-UHFFFAOYSA-N Lithium ion Chemical compound [Li+] HBBGRARXTFLTSG-UHFFFAOYSA-N 0.000 description 1
- 238000003491 array Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000012634 fragment Substances 0.000 description 1
- 229910001416 lithium ion Inorganic materials 0.000 description 1
Images
Classifications
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02S—GENERATION OF ELECTRIC POWER BY CONVERSION OF INFRARED RADIATION, VISIBLE LIGHT OR ULTRAVIOLET LIGHT, e.g. USING PHOTOVOLTAIC [PV] MODULES
- H02S30/00—Structural details of PV modules other than those related to light conversion
- H02S30/20—Collapsible or foldable PV modules
-
- 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
Landscapes
- Photovoltaic Devices (AREA)
Abstract
The invention relates to a flexible solar cell array for an airship in a near space, which comprises a thin film solar cell module (1), a power supply quick connector, a leading-out cable and a semi-rigid fastening cable (3), wherein the flexible solar cell array is formed by splicing a plurality of thin film solar cell modules (1), the spliced thin film solar cell modules (1) are fixed on the surface of the airship in the near space through the semi-rigid fastening cable (3), the thin film solar cell modules (1) are connected in series and in parallel through the power supply quick connector to form the flexible solar cell array, and the power output of the flexible solar cell array is led out through the leading-out cable. Compared with the prior art, the invention has the advantages of better curved surface laminating effect, lightness, high energy storage efficiency and the like.
Description
Technical Field
The invention relates to the field of solar cell arrays, in particular to a flexible solar cell array for an airship in a near space.
Background
The adjacent space is generally higher than a common aviation aircraft internationally, is lower than an airspace of an orbit aircraft running space, is about 20 km-100 km above the earth surface, and in recent years, due to the huge strategic value of the adjacent space, the adjacent space is more and more emphasized by various international major countries, particularly by traditional aerospace strong countries such as the United states, Israel, Europe, Japan, Russia and the like, and in recent years, China also gradually emphasizes on the research of the adjacent space and steps into the true orbit.
The near space airship has great effect in the fields of military affairs, communication, earth observation and the like in the future. For the airship in the near space with long dead time, the control of the energy system is a brand new topic, and the large-area high-reliability control of the solar battery array, the large-current charging and discharging control of the novel energy storage power supply and the like are in research stages.
The airship in the near space is powered by the thin film solar cell adhered to the surface of the airship in the daytime, and is powered by the lithium ion storage battery at night to keep working for 24 hours.
Most of the surfaces of the bodies of the near space airship are of cambered surface structures, the areas are large, the illumination conditions are good, and the solar cell array is required to have certain flexibility during compounding. At present, the traditional solar cell array is large in area and poor in bending performance, hidden cracks and fragments of cells are easily caused when the solar cell array is laid in a large area, so that the whole electrical performance of the airship cell array in the adjacent space is reduced, the broken cell part has potential safety hazards for the whole airship, and the large-area solar cell array is easily damaged during assembly and airship inflation and deflation.
The flexible solar cell array for the airship not only needs to have good fitting degree with the surface of the airship, but also can meet the requirements of wind resistance, light weight and environmental temperature change close to the space of the airship in the flying process.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide a flexible solar cell array for an adjacent space airship.
The purpose of the invention can be realized by the following technical scheme:
a flexible solar cell array for an airship close to space comprises a thin film solar cell module, a power supply quick connector, a leading-out cable and a semi-rigid fastening cable, wherein the flexible solar cell array is formed by splicing a plurality of thin film solar cell modules, the spliced thin film solar cell modules are fixed on the surface of the airship in space through the semi-rigid fastening cable, the thin film solar cell modules are connected in series and in parallel through the power supply quick connector to form the flexible solar cell array, and the power output of the flexible solar cell array is led out through the leading-out cable.
Furthermore, the thin film solar cell modules are connected in series into a row through the power quick connectors, and then the rows after being connected in series are connected in parallel to form the flexible solar cell array.
And further, a buffer strip is arranged between two adjacent columns of thin film solar cell modules after series connection.
Furthermore, the buffer zone is an elastic rubber material with the width gradually narrowed from the middle part to the two ends, namely, the willow-leaf-shaped buffer zone has the effect of buffering the stress between the thin-film solar cell modules on one hand, and on the other hand, the flexible solar cell array is provided with an arc line so as to be matched with the surface of the airship body in the adjacent space of the arc-shaped structure.
Furthermore, the buffer strip is connected with two adjacent columns of thin film solar cell modules in a gluing or sewing or heat sealing mode.
The thin film solar cell module is formed by splicing a plurality of thinned crystalline silicon solar cells.
The semi-rigid fastening rope comprises a rigid rope, an elastic rope, a hanging ring a, a hanging ring b, a rigid connection rope a and a rigid connection rope b, the rigid rope and the elastic rope are arranged between the hanging ring a and the hanging ring b side by side, a plurality of grippers are arranged on two sides of the outer surface of the airship close to the space, one end of the rigid connection rope a is connected to the hanging ring b, the other end of the rigid connection rope b is connected to the grippers, one end of the rigid connection rope b is connected to the hanging ring a, and the other end of the rigid connection rope b is connected to the side edge of the spliced thin film solar cell module.
Furthermore, the length of the elastic rope in a natural state is 2/3 of the length of the rigid rope, wherein the elastic rope is used for buffering stress on the flexible solar cell array, and the rigid rope is used for limiting and fixing the flexible solar cell array when the elastic rope reaches an elastic limit.
Furthermore, the elastic rope is made of spandex materials.
Further, the rigid rope is made of PBO fiber materials, namely poly-p-phenylene benzobisoxazole fibers, so that the modulus of the rigid rope is 280 GPa.
Compared with the prior art, the invention has the following advantages:
1. the airship body surface in the near space is mostly of an arc surface structure, the splicing technology of a plurality of thin film solar cell modules is adopted, so that the thin film solar cell modules are arranged on the airship body surface in the form of arc surfaces and have good fitting degree with the airship surface, the received sunlight area is large, the illumination effect is good, the solar cell array has certain flexibility during compounding, the arc surface bending angle can reach 120 degrees, and the large-area solar cell array is not easy to damage during assembling and airship inflation and deflation.
2. A willowleaf-shaped buffer zone is adopted among each row of thin film solar cell modules, so that the thin film solar cell modules are well protected.
3. The solar cell array is light and thin, has high output power, and the density of the solar cell array surface is 500g/m2The specific power of the solar cell array is 195W/m2～250W/m2。
4. The whole solar cell array is fixed on the surface of the airship hull by the semi-rigid fastening rope, the fixation is reliable, and the solar cell array is fully protected by the buffering effect of the elastic rope.
Drawings
FIG. 1 is a schematic structural diagram of a use state of a flexible solar cell array for an adjacent space airship according to the present invention;
FIG. 2 is a schematic plan view of a flexible solar array for an adjacent space airship according to the present invention;
FIG. 3 is a schematic diagram of a hanging structure of a flexible solar cell array for an adjacent space airship according to the present invention;
fig. 4 is a schematic structural view of a semi-rigid fastening cable according to the present invention.
In the figure: 1. the thin-film solar cell module 2 and the willow-leaf-shaped buffer strip are 3, a semi-rigid fastening rope 31, a rigid rope 32, an elastic rope 33, hanging rings a and 34, rigid connecting ropes a and 35, rigid connecting ropes b and 36 and a hanging ring b.
Detailed Description
The invention is described in detail below with reference to the figures and specific embodiments.
Examples
The flexible solar cell array for the near space airship comprises a thin film solar cell module 1, a power supply quick connector, a leading-out cable and a semi-rigid fastening rope 3, wherein the flexible solar cell array is formed by splicing a plurality of thin film solar cell modules 1, referring to the figures 1 and 2, the spliced thin film solar cell modules 1 are fixed on the surface of the near space airship through the semi-rigid fastening rope 3, the thin film solar cell modules 1 are connected in series and in parallel through the power supply quick connectors to form the flexible solar cell array, and the power output of the flexible solar cell array is led out through the leading-out cable. And then connecting the multiple series of solar cells in parallel to form a flexible solar cell array. And a buffer zone 2 is arranged between two adjacent columns of thin film solar cell modules 1 after series connection. The buffer belt is made of elastic rubber materials 2, and the width of the buffer belt is gradually narrowed from the middle part to the two ends. The buffer belt 2 is connected with two adjacent rows of thin film solar cell modules 1 in a mode of passing through. The thin film solar cell module 1 is formed by splicing a plurality of thinned crystalline silicon solar cells. The semi-rigid fastening rope 3 comprises a rigid rope 31, an elastic rope 32, a suspension loop a 33, a suspension loop b 36, a rigid connecting rope a 34 and a rigid connecting rope b 35, and is shown in fig. 3. A plurality of grippers 5 are arranged on two sides of the outer surface of the airship close to the space, the length of the elastic rope 32 is 2/3 of that of the rigid rope 31, the elastic rope 32 is made of spandex materials, and the rigid rope 31 is made of PBO fiber materials.
In the specific splicing process, firstly, the thin film solar cell modules 1 are connected in series into a plurality of rows through power quick connectors, then the buffer strips 2 are added among the plurality of rows of thin film solar cell modules 1, the two adjacent rows of thin film solar cell modules 1 are connected in a gluing or sewing or heat sealing mode, and then the power output of the flexible solar cell array is led out through the leading-out cables and is connected with the load. And then, the solar cell module is fixed through a semi-rigid fastening rope 3, specifically referring to fig. 3 and 4, a rigid rope 31 and an elastic rope 32 are arranged between a hanging ring a 33 and a hanging ring b 36 side by side, a plurality of grippers 5 are arranged on two sides of the outer surface of the airship near the space, one end of a rigid connecting rope a 34 is connected to the hanging ring b 36, the other end of the rigid connecting rope is connected to the grippers 5, and then one end of a rigid connecting rope b 35 is connected to the hanging ring a 33, and the other end of the rigid connecting rope is connected to the side edge of the spliced thin film solar cell module 1.
Claims (10)
1. The flexible solar cell array is characterized by comprising a thin film solar cell module (1), a power supply quick connector, a leading-out cable and a semi-rigid fastening cable (3), wherein the flexible solar cell array is formed by splicing a plurality of thin film solar cell modules (1), the spliced thin film solar cell modules (1) are fixed on the surface of a space airship through the semi-rigid fastening cable (3), the thin film solar cell modules (1) are connected in series and in parallel through the power supply quick connector to form the flexible solar cell array, and the power output of the flexible solar cell array is led out through the leading-out cable.
2. The flexible solar cell array for the close-space airship as claimed in claim 1, wherein the thin film solar cell modules (1) are connected in series into a row through a power quick connector, and then the series-connected rows are connected in parallel to form the flexible solar cell array.
3. The flexible solar cell array for the close-space airship as claimed in claim 2, wherein a buffer strip (2) is arranged between two adjacent columns of thin film solar cell modules (1) after series connection.
4. A flexible solar cell array for an adjacent space airship as claimed in claim 3, wherein the buffer zone is (2) an elastic rubber material with a width gradually narrowing from the middle to the two ends.
5. A flexible solar cell array for an adjacent space airship according to claim 4, wherein the buffer strip (2) is connected with two adjacent columns of the thin film solar cell modules (1) through gluing or sewing or heat sealing.
6. The flexible solar cell array for the close-space airship as claimed in claim 1, wherein the thin film solar cell module (1) is formed by splicing a plurality of thinned crystalline silicon solar cells.
7. The flexible solar cell array for the near space airship as claimed in claim 1, wherein the semi-rigid fastening rope (3) comprises a rigid rope (31), an elastic rope (32), a hanging ring a (33), a hanging ring b (36), a rigid connecting rope a (34) and a rigid connecting rope b (35), the rigid rope (31) and the elastic rope (32) are arranged between the hanging ring a (33) and the hanging ring b (36) side by side, a plurality of grippers (5) are arranged on two sides of the outer surface of the near space airship, one end of the rigid connecting rope a (34) is connected to the hanging ring b (36), the other end of the rigid connecting rope b (35) is connected to the grippers (5), one end of the rigid connecting rope b (35) is connected to the hanging ring a (33), and the other end of the rigid connecting rope b is connected to the side edge of the spliced thin film solar cell module (1).
8. The close space airship flexible solar cell array as claimed in claim 7, wherein the natural length of the elastic rope (32) is 2/3 of the length of the rigid rope (31).
9. The close-space airship flexible solar cell array as claimed in claim 8, wherein the elastic rope (32) is made of spandex material.
10. The close-space airship flexible solar cell array as claimed in claim 8, wherein the rigid rope (31) is of PBO fiber material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811359808.3A CN111193472B (en) | 2018-11-15 | 2018-11-15 | Flexible solar cell array for near space airship |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811359808.3A CN111193472B (en) | 2018-11-15 | 2018-11-15 | Flexible solar cell array for near space airship |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111193472A true CN111193472A (en) | 2020-05-22 |
| CN111193472B CN111193472B (en) | 2023-03-03 |
Family
ID=70707042
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811359808.3A Active CN111193472B (en) | 2018-11-15 | 2018-11-15 | Flexible solar cell array for near space airship |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111193472B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110100437A1 (en) * | 2008-07-02 | 2011-05-05 | Naoki Takahashi | Solar battery module and solar battery array |
| CN102270682A (en) * | 2010-06-03 | 2011-12-07 | 上海空间电源研究所 | Ultra-light solar cell array and method for manufacturing same |
| CN103280472A (en) * | 2013-05-28 | 2013-09-04 | 北京航空航天大学 | Flexible netlike solar battery array for stratospheric aerostat |
| CN105680775A (en) * | 2014-11-18 | 2016-06-15 | 上海空间电源研究所 | Semi-flexible solar cell array for stratospheric airship |
| JP2016122770A (en) * | 2014-12-25 | 2016-07-07 | 京セラ株式会社 | Solar battery module and solar battery array using the same |
| CN106816479A (en) * | 2016-12-27 | 2017-06-09 | 中国电子科技集团公司第十八研究所 | Flexible solar cell array suitable for near space ultra-long time-of-flight aircraft |
-
2018
- 2018-11-15 CN CN201811359808.3A patent/CN111193472B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110100437A1 (en) * | 2008-07-02 | 2011-05-05 | Naoki Takahashi | Solar battery module and solar battery array |
| CN102270682A (en) * | 2010-06-03 | 2011-12-07 | 上海空间电源研究所 | Ultra-light solar cell array and method for manufacturing same |
| CN103280472A (en) * | 2013-05-28 | 2013-09-04 | 北京航空航天大学 | Flexible netlike solar battery array for stratospheric aerostat |
| CN105680775A (en) * | 2014-11-18 | 2016-06-15 | 上海空间电源研究所 | Semi-flexible solar cell array for stratospheric airship |
| JP2016122770A (en) * | 2014-12-25 | 2016-07-07 | 京セラ株式会社 | Solar battery module and solar battery array using the same |
| CN106816479A (en) * | 2016-12-27 | 2017-06-09 | 中国电子科技集团公司第十八研究所 | Flexible solar cell array suitable for near space ultra-long time-of-flight aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111193472B (en) | 2023-03-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103606580B (en) | Flexible solar plate and preparation method thereof, dirigible | |
| US20180212087A1 (en) | Mobile power system | |
| US20130285440A1 (en) | Integration of high-efficiency, lightweight solar sheets onto unmanned aerial vehicle for increased endurance | |
| CN103840745A (en) | Solar energy system for unmanned plane to use | |
| CA2936127A1 (en) | Balloon equipped with a concentrated solar generator and employing an optimised arrangement of solar cells to power said balloon in flight | |
| CN203491953U (en) | Solar energy system for unmanned plane | |
| CN106816479A (en) | Flexible solar cell array suitable for near space ultra-long time-of-flight aircraft | |
| CN107994086B (en) | Photovoltaic blanket | |
| CN102709372A (en) | Photovoltaic module | |
| CN101665153A (en) | Plane wing with solar battery | |
| CN111193472B (en) | Flexible solar cell array for near space airship | |
| CN108820178A (en) | A kind of foldable solar energy wing sail of solar sailor | |
| CN111261739B (en) | Ultra-light flexible thin film solar cell module for near space airship | |
| CN202237261U (en) | Solar toy airplane | |
| CN105235890A (en) | Aircraft wing structure capable of realizing rapid disassembly and assembly for cell array | |
| CN205801499U (en) | Flying wing type solar powered aircraft | |
| CN209441681U (en) | A kind of near space unmanned plane semi-rigid solar cell array | |
| CN205378951U (en) | Photovoltaic power generation component and photovoltaic power generation sunshade instrument | |
| CN109606623A (en) | Intelligent modularized solar energy unmanned plane | |
| CN202374019U (en) | Portable emergency solar energy power supply | |
| KR20130034083A (en) | Helideck having solar cell | |
| CN207664052U (en) | A kind of photovoltaic blanket | |
| CN207818591U (en) | flexible photovoltaic energy storage assembly | |
| CN208979092U (en) | A kind of mixed layout unmanned plane | |
| CN111284670A (en) | Foldable solar wing sail for solar sailing boat |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |