CN219351572U - Solar cell mounting structure and stratospheric airship - Google Patents
Solar cell mounting structure and stratospheric airship Download PDFInfo
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- CN219351572U CN219351572U CN202222945727.XU CN202222945727U CN219351572U CN 219351572 U CN219351572 U CN 219351572U CN 202222945727 U CN202222945727 U CN 202222945727U CN 219351572 U CN219351572 U CN 219351572U
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- solar cell
- zipper
- stratospheric airship
- mounting structure
- cell mounting
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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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Abstract
The utility model discloses a solar cell installation structure and a stratospheric airship, wherein the solar cell installation structure comprises a solar cell (1), an elastic transition belt (2) and an opening zipper (3), the elastic transition belt (2) is arranged around the edge of the solar cell (1) in a closed loop manner, and the opening zipper (3) is arranged at the outer edge of the elastic transition belt (2). The solar cell mounting structure and the stratospheric airship overcome the defects of mounting and using of the conventional large-area flexible solar cell on the stratospheric airship and reduce the difficulty of mounting and dismounting the solar cell.
Description
Technical Field
The utility model relates to a flexible solar cell mounting structure and a stratospheric airship, and belongs to the field of lighter-than-air aircrafts.
Background
The stratospheric airship is an aircraft capable of executing flight tasks in the earth atmosphere stratosphere space domain for a long time, has the advantages of higher flight altitude, low cost, long dead time and the like compared with other types of aircraft, and can realize application purposes such as meteorological environment monitoring, regional communication, homeland general survey, urban traffic monitoring, earth detection, astronomical observation, high-altitude exploration travel and the like by utilizing the stratosphere airship to carry corresponding working loads.
In order to better realize controllable flying of the stratospheric airship over the day and night for a long time, a well designed energy supply/circulation system is a key technology in the design and development process of the stratospheric airship. Currently, in the technical field of stratospheric airships at home and abroad, the design technology of an energy supply/circulation system adopting a flexible solar battery and a storage battery has become the mainstream of technical development, and the energy supply/circulation system utilizes the advantages of light weight and relatively high conversion efficiency of the flexible solar battery, so that the energy density of the battery is continuously improved.
However, the installation structure and the laying technology of the flexible solar cell on the airship greatly influence the installation, disassembly, collection and replacement efficiency of the solar cell, and simultaneously influence the safety of the solar cell and the airship in the stratospheric airship flying process.
Currently, a flexible solar cell is directly installed on the surface of a stratospheric airship capsule body in a mode of tying or sticking, and the cell is contacted or attached with the surface of the airship capsule body. Wherein:
the flexible solar battery adopts a rope-tying type mounting structure, a large number of ropes or binding belts are needed to connect and fix limit holes (loops) around the battery with connecting holes (loops) on the capsule body one by one, the mounting and dismounting efficiency is low, deformation or damage of the flexible solar battery is easily caused in the stratospheric airship flying process due to inconsistent rope-tying tightness, a large gap exists between the flexible solar battery and the airship capsule body after pavement is inevitably caused by the rope-tying type, and unstable air flow passes through the gap in the airship flying process, so that the battery is easy to shake and damage;
the flexible solar cell is arranged on the surface of the stratospheric airship capsule body in a sticking mode, so that the installation efficiency is greatly improved, but the flexible solar cell is fixed by means of the adhesive force of the sticking button, and the risk of great loss exists due to uneven and unreliable adhesive force. In the process that the stratospheric airship ascends from the ground, the wind speed can exceed 40m/s at most, and the factors such as aerodynamic resistance generated by the flexible solar cell, large deformation of the surface of the airship bag body, high-frequency vibration and the like easily cause gradual failure of adhesion between the sticking buckles, so that the flexible solar cell is scraped or scratched by wind.
Moreover, in the conventional mounting structure and mounting mode, the flexible solar cell is closely adhered to the airship capsule body, and on one hand, the flexible solar cell is relatively small in deformation and can be damaged due to rapid expansion of the volume of the airship capsule body; on the other hand, because the flexible solar cell generates a large amount of heat in the energy conversion process, the structural strength of the airship capsule body is reduced or the structure is damaged due to the temperature rise caused by heat accumulation generated on the back surface of the flexible solar cell.
Therefore, the installation of large-area flexible solar cells on stratospheric airships needs to solve several technical problems:
1) The flexible solar cell is quickly installed and disassembled;
2) The flexible solar cell effectively dissipates heat;
3) The flexible solar cell and the stratospheric airship capsule body are reliably installed and fixed;
4) The flexible solar cell and the stratospheric airship capsule have good deformation adaptability.
Disclosure of Invention
In order to solve the problems of low installation efficiency, unreliable installation and the like of a flexible solar cell on a stratospheric airship, the utility model provides a solar cell installation structure, and the specific technical scheme is as follows.
A solar cell mounting structure, characterized in that: the solar cell comprises a solar cell, an elastic transition belt and an opening zipper, wherein the elastic transition belt is arranged around the edge of the solar cell in a closed loop manner, and the opening zipper is arranged at the outer edge of the elastic transition belt.
By adopting the technical scheme, the mounting and dismounting difficulty of the solar cell is greatly reduced, and the solar cell can be well adapted to the deformation of the stratospheric airship capsule body. The elastic transition belt wraps the outer edge of the whole solar cell to form a closed loop, and stress concentration of the local edge profile of the solar cell is not easy to occur, so that the stability and durability of the solar cell mounting structure can be improved.
Further, the elastic transition zone adopts polyurethane film or polyester fabric with weather-proof coating. Preferably, the thickness of the elastic transition band is 0.1mm-0.3mm.
Further, the opening zipper is a single-side zipper, and one or two pullers are further arranged on the opening zipper.
Further, the zipper head is also provided with holes or knots for tying ropes;
based on the same conception, the utility model also relates to a stratospheric airship, which comprises the solar cell mounting structure and a solar cell mounting interface matched with the solar cell mounting structure for mounting, wherein the solar cell mounting structure is mounted in the solar cell mounting interface;
the solar cell mounting interface comprises a curtain cloth and an opening zipper, wherein the curtain cloth is fixed on the surface of a bag body of the stratospheric airship, and the opening zipper is fixed on the edge of the curtain cloth; the open zipper of the solar cell mounting interface is matched with the open zipper of the solar cell mounting structure.
The open zipper of the solar cell installation interface is completely matched with the specification model and the length of the open zipper on the solar cell installation structure, and the open zipper can be combined into a closed and complete zipper through the zipper head, so that the solar cell can be rapidly installed and disassembled.
Further, the open zipper of the solar cell mounting structure is provided with a pulling head, and the pulling cable heads of the adjacent solar cell mounting structures are connected in series and fixed through a tether.
Further, the solar cell mounting interface further comprises a supporting structure, the supporting structure is arranged on the outer surface of the bag body of the stratospheric airship and located in the area surrounded by the curtain cloth, and the supporting structure comprises strips protruding out of the outer surface of the bag body, and a plurality of strips are distributed in parallel or interweaved with each other to form a net structure.
Further, the support structure is made of foamed plastic. Preferably, the height of the strips is 4-10 mm, and the distance between two adjacent strips is 10-40 cm.
Compared with the prior art, the utility model has the following beneficial effects.
1) The zipper is provided with the unilateral opening on the periphery of the flexible solar cell and the periphery of the solar cell installation interface of the stratospheric airship, so that the flexible solar cell can be installed on the stratospheric airship in a zipper pulling and closing mode, and the flexible solar cell has the advantages of reliability in fixation and good sealing performance, and the problem of damage to the flexible solar cell caused by air flow disturbance is solved;
2) The solar cell mounting interface of the stratospheric airship is internally provided with the supporting structure, the flexible solar cell is mounted in the stratospheric airship capsule body mounting interface by virtue of the supporting structure, the influence on the capsule body structure under the condition of high temperature of the flexible solar cell is avoided, and the generated heat is dissipated through the isolation groove (a gap between adjacent strips), so that the technical scheme realizes the effective heat dissipation of the flexible solar cell on the stratospheric airship;
3) Through the elastic transition zone around the flexible solar cell installation structure and the curtain cloth around the stratospheric airship solar cell installation interface, the characteristics of high strength and high extensibility of the elastic transition zone and the curtain cloth material are utilized, so that the shape of the flexible solar cell can adapt to the deformation outside the airship capsule body, and the flexible solar cell can be well attached to the surface of the airship capsule body.
Drawings
Fig. 1 is a schematic view of a solar cell mounting structure of the present utility model;
FIG. 2 is a schematic view of the installation of the solar cell installation structure of the present utility model on a stratospheric airship;
FIG. 3 is a schematic view of a solar cell mounting interface on a stratospheric airship;
fig. 4 is a schematic view of a support structure within a solar cell mounting interface on a stratospheric airship, fig. 4 (a) being a schematic view in cross section and fig. 4 (b) being a schematic plan view;
fig. 5 is a schematic view of another support structure within a solar cell mounting interface on a stratospheric airship, fig. 5 (a) being a schematic view in cross section and fig. 5 (b) being a schematic plan view;
fig. 6 is an enlarged view of a partial structure in fig. 2.
In the figure: 10-solar cell mounting structure, 1-solar cell, 2-elastic transition belt, 3-opening zipper, 4-tapered end, 5-curtain cloth, 6-zipper mounting notch, 7-strip, 8-isolation groove, 9-tether, 20-stratospheric airship, 30-solar cell mounting interface, 40-supporting structure and 50-tether.
Detailed Description
The utility model is described in further detail below with reference to the accompanying drawings.
For the purpose of making the objects, technical solutions and advantages of the present utility model more apparent, the technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings, and it is apparent that the described embodiments are some embodiments of the present utility model, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
The solar cell mounting structure and the stratospheric airship of the present utility model are described below with reference to fig. 1 to 6.
As shown in fig. 1, the utility model provides a novel flexible solar cell mounting structure 10, which comprises a flexible solar cell 1, an elastic transition belt 2 and an opening zipper 3. The elastic transition belt 2 is arranged along the peripheral edge of the flexible solar cell 1, and the open zipper 3 is arranged at the outer edge of the elastic transition belt 2.
Specifically, the flexible solar cell 1 may be a full-flexible solar cell using a polymer plastic film as a substrate, or may be a semi-flexible solar cell using a metal film or other polymer materials as a substrate;
the elastic transition belt 2 is of a closed annular sheet structure, is made of a flexible composite material with high strength and good ductility, and is arranged around the substrate of the flexible solar cell 1 in a sewing, gluing or heat sealing mode;
further, the elastic transition belt 2 is made of polyurethane film with the thickness of 0.1-0.3 mm or polyester fabric with weather-proof coating;
the open zipper 3 is a unilateral zipper and is arranged at the outer edge of the elastic transition belt 2 in an end-to-end connection manner through sewing, cementing or heat sealing; and one or two zipper heads 4 are also arranged on the opening zipper 3;
with reference to fig. 6, the zipper head 4 is further provided with holes or knots for tying ropes.
Referring to fig. 2-3, the stratospheric airship of the utility model comprises a plurality of groups of flexible solar cell mounting structures 10 and solar cell mounting interfaces 30 matched with the flexible solar cell mounting structures for mounting, wherein the flexible solar cell mounting structures 10 are mounted in the solar cell mounting interfaces 30.
Specifically, the solar cell mounting interface 30 mainly includes an open zipper 3, a curtain fabric 5 and a supporting structure 40, wherein the open zipper 3 is a single-side zipper and is mounted at the edge of the annular curtain fabric 5 by sewing, gluing or heat sealing;
the open zipper 3 of the solar cell mounting interface 30 is completely matched with the specification model and the length of the open zipper 3 on the flexible solar cell mounting structure 10, and can be combined into a closed and complete zipper through the zipper head 4;
further, a zipper mounting notch 6 is formed in the curtain cloth 5 of the solar cell mounting interface 30, and the zipper locking head 4 of the zipper is connected and closed with the opening zipper 3 on the solar cell mounting interface 30 through the zipper mounting notch 6, so that the opening zipper 3 on the flexible solar cell mounting structure 10 is connected and closed with the opening zipper 3 on the solar cell mounting interface 30.
The curtain cloth 5 is of a flexible composite material structure and is arranged on the outer surface of the top of the bag body of the stratospheric airship 20 in a sewing, gluing or heat sealing mode, the curtain cloth 5 is enclosed into a closed annular area, and the shape and the size of the curtain cloth are matched with those of the flexible solar cell installation structure 10;
further, in order to improve the deformation adaptability between the flexible solar cell 10 and the balloon of the stratospheric airship 20, the curtain cloth 5 may be made of the same flexible composite material as the elastic transition band 2 of the flexible solar cell mounting structure 10.
Referring to fig. 4-5, a stratospheric airship is provided according to the utility model, the support structure 40 being provided within the stratospheric airship solar battery mounting interface 30;
the supporting structure 40 includes strips 7 protruding from the outer surface of the hull of the stratospheric airship 20, and a plurality of the strips 7 are distributed in parallel (as shown in fig. 5) or interweaved with each other to form a net structure (as shown in fig. 4), and the strips 7 are formed by adopting a high-temperature resistant and lightweight foaming plastic material. The strips 7 are uniformly distributed on the outer surface of the bag body, and the isolation grooves 8 (i.e. gaps between the adjacent strips 7) formed between the strips 7 provide good heat shielding and heat dissipation channels for the flexible solar cell;
further, to improve the heat dissipation effect on the flexible solar cell 1, the weight increase caused by the heat dissipation material is controlled, and the height of the strip 7 of the supporting structure 40 is set as follows: 4 mm-10 mm, isolation groove 8 width: 10 cm-40 cm.
Referring to fig. 1 and 6, the utility model provides a novel flexible solar cell installation structure 10, wherein a zipper head 4 is respectively arranged at the front end and the rear end of an open zipper 3 of the flexible solar cell installation structure 10, so that the connection installation with a solar cell installation interface 30 of a stratospheric airship 20 can be realized clockwise or anticlockwise, and the installation and the disassembly efficiency of the flexible solar cell installation structure 10 are improved;
after the large-area flexible solar cell 1 is installed on the stratospheric airship 20 through the zipper head 4 on the opening zipper, the zipper heads 4 of adjacent solar cell installation structures are fixedly connected in series by adopting the tether 50, so that the zipper heads 4 are prevented from being disturbed by airflow to slide, and the installation reliability of the flexible solar cell 1 is improved; when the flexible solar cell mounting structure 10 needs to be recovered and detached, the tether 50 is detached or cut off, and the pullers 4 can be pulled apart, and the flexible solar cell mounting structure 10 can be removed from the stratospheric airship 20.
The flexible solar cell mounting structure and the stratospheric airship overcome the defects of mounting and using a conventional large-area flexible solar cell on the stratospheric airship, solve the existing technical problems in a simpler way, and provide effective technical support for the design scheme of the stratospheric airship energy supply/circulation system of the flexible solar cell and the storage battery.
The embodiments of the present utility model have been described above with reference to the accompanying drawings, and the embodiments of the present utility model and the features of the embodiments may be combined with each other without conflict. The present utility model is not limited to the above-described embodiments, which are merely illustrative and not restrictive, and many forms may be made by those of ordinary skill in the art without departing from the spirit of the utility model and the scope of the appended claims, which are all within the scope of the utility model.
Claims (10)
1. A solar cell mounting structure, characterized in that: the solar cell comprises a solar cell (1), an elastic transition belt (2) and an opening zipper (3), wherein the elastic transition belt (2) is arranged around the edge of the solar cell (1) in a closed loop mode, and the opening zipper (3) is arranged at the outer edge of the elastic transition belt (2).
2. The solar cell mounting structure according to claim 1, wherein the elastic transition band (2) is made of polyurethane film or polyester fabric with weather-resistant coating.
3. A solar cell mounting structure according to claim 1, characterized in that the thickness of the elastic transition band (2) is 0.1mm-0.3mm.
4. The solar cell mounting structure according to claim 1, wherein the open zipper (3) is a single-sided zipper, and one or two pullers (4) are further provided on the open zipper (3).
5. The solar cell mounting structure according to claim 4, wherein the zipper head (4) is further provided with holes or knots for tying ropes.
6. Stratospheric airship characterized by comprising a solar cell mounting structure (10) according to any one of claims 1-5 and a solar cell mounting interface (30) for matching mounting therewith, the solar cell mounting structure (10) being mounted in the solar cell mounting interface (30);
the solar cell mounting interface (30) comprises a curtain cloth (5) and an opening zipper (3), wherein the curtain cloth (5) is fixed on the surface of a bag body of the stratospheric airship, and the opening zipper (3) is fixed at the edge of the curtain cloth (5); the opening zipper (3) of the solar cell mounting interface (30) and the opening zipper (3) of the solar cell (1) mounting structure are matched with each other.
7. The stratospheric airship according to claim 6, characterized in that the open zippers (3) of the solar cell (1) mounting structure are provided with pullers (4), and the pullers of adjacent solar cell (1) mounting structures are serially fixed by tethers.
8. The stratospheric airship according to claim 6, characterized in that the solar cell mounting interface (30) further comprises a supporting structure (40), the supporting structure (40) is arranged on the outer surface of the capsule of the stratospheric airship and is located in the area surrounded by the curtain cloth (5), the supporting structure (40) comprises strips (7) protruding from the outer surface of the capsule, and a plurality of strips (7) are distributed in parallel or interweaved with each other to form a net structure.
9. Stratospheric airship as claimed in claim 8, characterized in that the supporting structure (40) is made of foamed plastic.
10. Stratospheric airship according to claim 8, characterized in that the height of the strips (7) is 4-10 mm and the distance between two adjacent strips (7) is 10-40 cm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222945727.XU CN219351572U (en) | 2022-11-03 | 2022-11-03 | Solar cell mounting structure and stratospheric airship |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222945727.XU CN219351572U (en) | 2022-11-03 | 2022-11-03 | Solar cell mounting structure and stratospheric airship |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219351572U true CN219351572U (en) | 2023-07-14 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222945727.XU Active CN219351572U (en) | 2022-11-03 | 2022-11-03 | Solar cell mounting structure and stratospheric airship |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219351572U (en) |
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- 2022-11-03 CN CN202222945727.XU patent/CN219351572U/en active Active
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