CN210123962U - Rigid-flexible solar cell array - Google Patents
Rigid-flexible solar cell array Download PDFInfo
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- CN210123962U CN210123962U CN201921080644.0U CN201921080644U CN210123962U CN 210123962 U CN210123962 U CN 210123962U CN 201921080644 U CN201921080644 U CN 201921080644U CN 210123962 U CN210123962 U CN 210123962U
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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
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- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
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Abstract
The embodiment of the utility model provides a hard and soft solar cell array, this hard and soft solar cell array include flexible solar module and latticed rigid frame, through fixing flexible solar module in latticed rigid frame hollow out construction to constitute the solar cell array that has both rigidity characteristics and flexibility characteristics, flexible solar module has lighter weight for rigid solar module on the one hand, thereby can alleviate the weight of hard and soft solar cell array; on the other hand, the flexible solar cell module is fixed in the grid-shaped rigid frame hollow structure, so that the flexible solar cell module can be prevented from being curled, and the unfolding structure of the flexible solar cell module is simplified.
Description
Technical Field
The embodiment of the utility model provides a relate to space flight technical field, especially relate to a be applied to rigid and flexible solar cell array of spacecraft.
Background
The solar cell array converts solar energy into electric energy through a photovoltaic effect, and provides electric energy for electric devices of the spacecraft. At present, a solar cell array applied to a spacecraft (e.g., a satellite) is a rigid folded solar cell array having a foldable rigid substrate. When the satellite launches, the rigid substrates of the rigid folding solar cell array are folded together in a folding mode, and after the satellite enters the orbit, the folded rigid substrates are unfolded, so that the solar cell array receives solar radiation.
However, rigid solar arrays are generally heavy and not conducive to satellite launch and on-orbit motion; when the rigid solar cell is replaced by the flexible solar cell, although the weight is reduced, the unfolding mechanism of the flexible solar cell array is complex, and when the flexible solar cell array is unfolded from a wound state, a large on-orbit disturbance is generated on a satellite.
SUMMERY OF THE UTILITY MODEL
To the above problem, the embodiment of the utility model provides a hard and soft solar cell battle array can solve among the prior art solar cell battle array weight heavier, is unfavorable for solar cell's application on the spacecraft to and solar cell battle array structure is complicated, the technical problem of incremental cost.
The embodiment of the utility model provides a hard and soft solar cell battle array, include:
a plurality of flexible solar cell assemblies comprising a flexible substrate and at least one flexible solar cell; the flexible solar cell is fixed on one side of the flexible substrate base plate;
a lattice-like rigid frame; the latticed rigid frame comprises hollow structures corresponding to the plurality of flexible solar cell modules; the flexible solar cell module is fixed in the hollow structure.
Optionally, the latticed rigid frame comprises a plurality of first support bars extending along the first direction and arranged along the second direction, and a plurality of second support bars extending along the second direction and arranged along the first direction; the plurality of first supporting rods and the plurality of second supporting rods are arranged in a crossed mode to form a plurality of hollow structures.
Optionally, the first support bar and/or the second support bar have a hollow structure.
Optionally, a plurality of the flexible solar cells are electrically connected through an internal lead;
the wire penetrates through the hollow structures of the first supporting rod and/or the second supporting rod.
Optionally, the rigid-flexible solar cell array includes a plurality of grid-shaped rigid frames;
the first supporting rods of two adjacent latticed rigid frames are connected through a hinge; and/or the second support rods of two adjacent latticed rigid frames are connected through a hinge.
Optionally, the flexible solar cell includes a flexible triple junction gallium arsenide solar cell.
Optionally, the flexible solar cells of the flexible solar cell module are connected in series and/or in parallel by welding.
Optionally, the flexible solar cell module further comprises a transparent film; the transparent film is positioned on one side of the flexible solar cell, which is far away from the flexible substrate base plate, and the transparent film covers all the flexible solar cells of the flexible solar cell module.
Optionally, the flexible solar cell module further includes an adhesive layer for adhering the flexible solar cell and the flexible substrate.
Optionally, the flexible substrate includes any one of a polyimide film and a glass fiber substrate.
The embodiment of the utility model provides a rigid-flexible solar cell array, this rigid-flexible solar cell array include flexible solar module and latticed rigid frame, through fixing flexible solar module in latticed rigid frame's hollow out construction to constitute rigid-flexible solar cell array that has both rigidity characteristics and flexibility characteristics, flexible solar module has lighter weight for rigid solar module on the one hand, thereby can alleviate the weight of rigid-flexible solar cell array; on the other hand, the flexible solar cell module is fixed in the hollow structure of the latticed rigid frame, so that the flexible solar cell module can be prevented from being curled, and the unfolding structure of the flexible solar cell module is simplified.
Drawings
Fig. 1 is a schematic structural diagram of a rigid-flexible solar cell array according to an embodiment of the present invention;
fig. 2 is a schematic top view of a flexible solar cell module according to an embodiment of the present invention;
FIG. 3 is a schematic cross-sectional view of a flexible solar cell module taken along section A-A' of FIG. 2;
fig. 4 is a schematic diagram of a film structure of a flexible solar cell module according to an embodiment of the present invention;
fig. 5 is a schematic structural diagram of a grid-shaped rigid frame according to an embodiment of the present invention;
FIG. 6 is a cross-sectional view of a support rod taken along section B-B' of FIG. 5;
fig. 7 is a schematic structural diagram of another latticed rigid frame according to an embodiment of the present invention;
fig. 8 is a schematic structural diagram of another rigid-flexible solar cell array according to an embodiment of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention. It should be further noted that, for the convenience of description, only some of the structures related to the present invention are shown in the drawings, not all of the structures.
It is known that a rigid solar cell module has a heavier mass than a flexible solar cell module, and when the rigid solar cell array is applied to a spacecraft, the spacecraft is subjected to a larger additional load, which is not favorable for the operation of the spacecraft. The flexible solar cell module has the characteristic of being easy to bend and wind, so that the flexible solar cell module needs a corresponding support structure to support the flexible solar cell module to be unfolded, and the flexible solar cell module has a relatively flat light receiving surface to receive solar radiation energy and perform photoelectric conversion. The existing support structure of the flexible solar cell module has a complex structure, a solar cell array formed by the flexible solar cell module can generate large disturbance due to reasons such as air flow, and when the flexible solar cell array is applied to a spacecraft, large resistance can be caused to the movement of the spacecraft.
Based on the technical problem, the embodiment of the utility model provides a hard and soft solar cell array is provided, this solar cell array can carry out photoelectric conversion, can be applied to in the spacecraft, provides the electric energy for the power consumption device of spacecraft. Fig. 1 is a schematic structural diagram of a rigid-flexible solar cell array provided by the embodiment of the present invention, and fig. 2 is a schematic structural diagram of a flexible solar cell module provided by the embodiment of the present invention looking down. With reference to fig. 1 and fig. 2, a rigid-flexible solar cell array 100 provided by the embodiment of the present invention includes a plurality of flexible solar cell modules 10 and a grid-shaped rigid frame 20.
The flexible solar cell module 10 comprises a flexible substrate 11 and at least one flexible solar cell 12; the flexible solar cell 12 is fixed to one side of the flexible substrate 11; the grid-shaped rigid frame 20 includes a plurality of hollow structures 25 corresponding to the plurality of flexible solar cell modules 10 one by one, and the flexible solar cell modules 10 are fixed in the hollow structures 25 of the grid-shaped rigid frame 20.
The material of the grid-shaped rigid frame 20 may be, for example, carbon fiber. The lattice-like rigid frame 20 made of carbon fibers has many excellent properties, high strength and modulus, low density, no creep, and good ultra-high temperature resistance and fatigue resistance in a non-oxidizing environment, so that the lattice-like rigid frame 20 has dual characteristics of rigidity and flexibility. The lattice-like rigid frame 20 is lighter in weight than metal aluminum of the same structure, but the strength of the lattice-like rigid frame 20 is higher than that of steel.
The flexible substrate 11 of the flexible solar cell module 10 may be any one of a polyimide film and a glass fiber substrate. When the flexible substrate 11 of the flexible solar cell module 10 is a polyimide film, the flexible substrate 11 may have excellent thermal stability, chemical resistance, and mechanical properties; when the flexible substrate 11 of the flexible solar cell module 10 is a glass fiber substrate, the flexible substrate 11 has the characteristics of good insulation, strong heat resistance, good corrosion resistance, high mechanical strength, and the like, and the material of the glass fiber substrate may include glass fiber and other organic materials, so that the flexible substrate has both the flexibility characteristic and the high strength.
By adopting the grid-shaped rigid frame 20 as the support structure of the flexible solar cell modules 10, on one hand, the rigid-flexible solar cell array 100 composed of a plurality of flexible solar cell modules 10 has a simple structure, so that the cost of the rigid-flexible solar cell array 100 is reduced; on the other hand, compared with the supporting structure of the flexible solar cell module 10 in the prior art, the latticed rigid frame 20 has lighter mass and higher strength, so that on the premise of satisfying the supporting effect on the solar cell module, the rigid-flexible solar cell array 100 has lighter mass, and the rigid-flexible solar cell array 100 is convenient to apply to a spacecraft and the like.
Alternatively, fig. 3 is a schematic cross-sectional view of a flexible solar cell module taken along the section a-a' in fig. 2. Referring to fig. 2 and 3, the flexible solar cell module 10 includes at least one flexible solar cell 12 and a flexible substrate 11. An adhesive layer 13 is arranged between the flexible solar cell 12 and the flexible substrate 11, and the adhesive layer 13 can adhere the flexible solar cell 12 and the flexible substrate 11 together. The adhesive layer 13 may be, for example, silicon rubber, which has high and low temperature resistance and can be applied to a spacecraft, and when the rigid-flexible solar cell array is applied to a spacecraft, the silicon rubber may be a space-grade silicon rubber, so as to meet the application of the rigid-flexible solar cell array in the field of aviation. The flexible solar cells 12 of the flexible solar cell module 10 can be connected in series and/or in parallel by welding, so as to meet the power consumption requirements of different electric devices. And the soldering of each flexible solar cell 12 may be selected as resistive soldering.
It should be noted that fig. 1, fig. 2 and fig. 3 are exemplary drawings of the embodiment of the present invention. In fig. 1, the number of the flexible solar cell modules 10 of the rigid-flexible solar cell array 100 and the number of the hollow structures of the latticed rigid frame 20 are not specifically limited; fig. 2 shows an exemplary flexible solar cell module 10 including 6 flexible solar cells 12, but the embodiment of the present invention is not limited to the number of flexible solar cells in the flexible solar cell module; in fig. 3, the flexible solar cell 12 is adhered to the flexible substrate 11 through the block-shaped adhesive layer 13, the adhesive layer 13 may also be planar, and for increasing the adhesiveness, the surface of the adhesive layer 13 may also be specially treated, and the embodiment of the present invention does not specifically limit the shape of the adhesive layer 13.
Alternatively, with continuing reference to fig. 2 and 3 in combination, the flexible solar cell 12 may comprise a flexible triple junction gallium arsenide solar cell.
Specifically, the gallium arsenide solar cell has a wide working temperature range and excellent space irradiation resistance, and compared with a single-junction gallium arsenide solar cell, the gallium arsenide solar cell with the triple junction can absorb solar radiation energy in different spectral ranges by using different band gap widths, so that the utilization rate of the solar radiation energy can be improved. When the flexible solar cell 12 of the flexible solar cell module 10 in the rigid-flexible solar cell array is a flexible triple junction gallium arsenide solar cell, the rigid-flexible solar cell array can be applied to a severe environment and has high photoelectric conversion efficiency.
Optionally, fig. 4 is a schematic diagram of a film structure of a flexible solar cell module according to an embodiment of the present invention. As shown in fig. 4, the flexible solar cell module 10 further includes a transparent film 14; the transparent film 14 is located on the side of the flexible solar cell 12 facing away from the flexible base substrate 11, and the transparent film 14 covers all the flexible solar cells 12 of the flexible solar cell assembly 10.
Specifically, the light receiving surface of the flexible solar cell 12 of the flexible solar cell module 10 is covered with a transparent film 14 to protect the flexible solar cell 12. The transparent film 14 may be an encapsulation structure of the flexible solar cell module 10, such that the flexible solar cell module 10 has a transparent encapsulation structure, so that solar radiation can reach the light receiving surface of the flexible solar cell 12 through the transparent film to perform photoelectric conversion on the flexible solar cell 12. Meanwhile, the transparent film 14 covering all the flexible solar cells 12 in the flexible solar cell module 10 can reduce the influence of spatial ultraviolet rays, particles, and the like on the light receiving surface 101 of the flexible solar cells 12.
Optionally, fig. 5 is a schematic structural diagram of a grid-shaped rigid frame according to an embodiment of the present invention. As shown in fig. 5, the lattice-shaped rigid frame 20 includes a plurality of first support bars 21 extending in the first direction X and arranged in the second direction Y, and a plurality of second support bars 22 extending in the second direction Y and arranged in the first direction X; the plurality of first support bars 21 and the plurality of second support bars 22 are arranged in a crossed manner to form a plurality of hollow structures 205.
Specifically, the first support bar 21 and the second support bar 22 are criss-cross to form a plurality of hollow structures 205, and the flexible solar cell module can be fixed in the hollow structures 205. The first support rod 21 and the second support rod 22 can be pressed together in a woven manner to form a grid-shaped rigid frame 20, and the flexible solar cell module can also be fixed in the hollow-out structure 205 of the grid-shaped rigid frame 20 in a woven manner; the first support bar 21 and the second support bar 22 may be fixed together by welding or riveting.
Alternatively, with continued reference to fig. 5, the first support bar 21 and/or the second support bar 22 may have an openwork structure. On one hand, the first support bar 21 and/or the second support bar 22 of the latticed rigid frame 20 are/is provided with hollow structures, so that the weight of the latticed rigid frame 20 can be further reduced; on the other hand, the first support bar 21 and/or the second support bar 22 of the grid-shaped rigid frame 20 are/is provided with a hollow structure, so that the confluence of the flexible solar cell sets can be facilitated.
Illustratively, FIG. 6 is a cross-sectional view of a support rod taken along section B-B' of FIG. 5. With reference to fig. 5 and 6, the second support rod 22 of the grid-shaped rigid frame 20 is a hollow cylindrical structure, and the mass of the second support rod 22 of the grid-shaped rigid frame 20 is lighter than that of a solid cylindrical structure; and when the adjacent flexible solar cell modules are electrically connected through the internal lead, the lead can penetrate through the second support rod 22 to be converged and connected, and is led out to supply power to the corresponding power utilization device. In addition, the structure of the first supporting rod 21 may be the same as that of the second supporting rod 22, and will not be described herein.
Exemplarily, fig. 7 is a schematic structural diagram of another grid-shaped rigid frame provided in the embodiment of the present invention. As shown in fig. 7, the first support bar 21 and the second support bar 22 may include strip-shaped hollow structures. At this time, the weight of the grid-shaped rigid frame 20 can also be reduced, and when the adjacent flexible solar cell modules are electrically connected through the conducting wires, the conducting wires can be combined together along the hollowed-out shape, so that the current combination of the flexible solar cell modules is realized, and the corresponding power utilization device is supplied with power.
It should be noted that fig. 6 and fig. 7 are only exemplary drawings of the embodiment of the present invention, and on the premise of meeting the strength and rigidity requirements of the solar cell array, the hollow structures of the first support rod and/or the second support rod of the grid-shaped rigid frame may be any shape, which is not specifically limited by the embodiment of the present invention.
Optionally, fig. 8 is a schematic structural diagram of another rigid-flexible solar cell array provided in an embodiment of the present invention. As shown in fig. 8, the rigid-flexible solar cell array 100 includes a plurality of grid-shaped rigid frames 20, and the first support rods 21 of two adjacent grid-shaped rigid frames 20 are connected by a hinge 23; and/or the second support bars 22 of two adjacent grid rigid shape frames 20 are connected by a hinge 23.
Specifically, the first support bars 21 of the lattice-shaped rigid frame 20 extend along the first direction X and are arranged along the second direction Y, and the second support bars 22 of the lattice-shaped rigid frame 20 extend along the second direction Y and are arranged along the second direction X. In the first direction X, the first support bars 21 of two adjacent latticed rigid frames 20 are connected through the hinge 23, so that the first support bars 21 of the latticed rigid frames 20 can support the flexible solar cell modules 10 in the hollow structures of the same latticed rigid frame 20 to be unfolded, and thus the flexible solar cell modules 10 in the hollow structures of the same latticed rigid frame 20 can be kept flat in the first direction X, and each latticed rigid frame 20 of the solar cell array can be folded along the second direction Y, so that the rigid-flexible solar cell array has a folding function, and the rigid-flexible solar cell array is convenient to transport.
Correspondingly, in the second direction Y, the second support rods 22 of the grid-shaped rigid frames 20 of the two adjacent grid-shaped rigid frames 20 can support the flexible solar cell modules 10 in the hollow structures of the same grid-shaped rigid frame 20 to be unfolded, so that the flexible solar cell modules 10 in the hollow structures of the same grid-shaped rigid frame 20 can be kept flat in the second direction Y and can be folded along the first direction X, so that the solar cells also have a folding function, and the transportation of the rigid and flexible solar cell array is facilitated.
Therefore, on one hand, each flexible solar cell module of the rigid-flexible solar cell array can keep a flat state, so that the rigid-flexible solar cell array can have a simple folding structure similar to a rigid solar cell array, the structure of the rigid-flexible solar cell array is simplified, and the preparation cost of the solar cell array is reduced; on the other hand, the flexible solar cell module in the rigid-flexible solar cell array is supported by the latticed rigid frame, so that the disturbance effect of the flexible solar cell module can be reduced; meanwhile, the flexible solar cell has light weight, and can be conveniently transported and applied.
It should be noted that the foregoing is only a preferred embodiment of the present invention and the technical principles applied. It will be understood by those skilled in the art that the present invention is not limited to the particular embodiments described herein, but is capable of various obvious modifications, rearrangements, combinations and substitutions as will now become apparent to those skilled in the art without departing from the scope of the invention. Therefore, although the present invention has been described in greater detail with reference to the above embodiments, the present invention is not limited to the above embodiments, and may include other equivalent embodiments without departing from the scope of the present invention.
Claims (10)
1. A rigid-flexible solar cell array, comprising:
a plurality of flexible solar cell assemblies comprising a flexible substrate and at least one flexible solar cell; the flexible solar cell is fixed on one side of the flexible substrate base plate;
a lattice-like rigid frame; the latticed rigid frame comprises hollow structures corresponding to the plurality of flexible solar cell modules; the flexible solar cell module is fixed in the hollow structure.
2. A rigid-flexible solar cell array as claimed in claim 1, wherein the lattice-like rigid frame comprises a plurality of first support rods extending in a first direction and aligned in a second direction, and a plurality of second support rods extending in the second direction and aligned in the first direction; the plurality of first supporting rods and the plurality of second supporting rods are arranged in a crossed mode to form a plurality of hollow structures.
3. The rigid-flexible solar cell array according to claim 2, wherein the first support bar and/or the second support bar has a hollow structure.
4. The rigid-flexible solar cell array of claim 3, wherein a plurality of the flexible solar cells are electrically connected by internal wires;
the wire penetrates through the hollow structures of the first supporting rod and/or the second supporting rod.
5. The rigid-flexible solar cell array according to claim 2, wherein the rigid-flexible solar cell array comprises a plurality of grid-like rigid frames;
the first supporting rods of two adjacent latticed rigid frames are connected through a hinge; and/or the second support rods of two adjacent latticed rigid frames are connected through a hinge.
6. The rigid-flexible solar cell array according to any one of claims 1 to 5, wherein the flexible solar cell comprises a flexible triple junction gallium arsenide solar cell.
7. The rigid-flexible solar cell array according to any one of claims 1 to 5, wherein the flexible solar cells of the flexible solar cell module are connected in series and/or in parallel by welding.
8. The rigid-flexible solar cell array according to any one of claims 1 to 5, wherein the flexible solar cell module further comprises a transparent film; the transparent film is positioned on one side of the flexible solar cell, which is far away from the flexible substrate base plate, and the transparent film covers all the flexible solar cells of the flexible solar cell module.
9. The rigid-flexible solar cell array according to any one of claims 1 to 5, wherein the flexible solar cell module further comprises an adhesive layer for adhering the flexible solar cell and the flexible substrate.
10. The rigid-flexible solar cell array according to any one of claims 1 to 5, wherein the flexible substrate comprises any one of a polyimide film and a glass fiber substrate.
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| CN201921080644.0U CN210123962U (en) | 2019-07-11 | 2019-07-11 | Rigid-flexible solar cell array |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110277958A (en) * | 2019-07-11 | 2019-09-24 | 苏州馥昶空间技术有限公司 | A kind of hard and soft solar battery array and preparation method thereof |
| CN112537464A (en) * | 2020-12-03 | 2021-03-23 | 上海空间电源研究所 | Flexible solar cell wing |
-
2019
- 2019-07-11 CN CN201921080644.0U patent/CN210123962U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110277958A (en) * | 2019-07-11 | 2019-09-24 | 苏州馥昶空间技术有限公司 | A kind of hard and soft solar battery array and preparation method thereof |
| CN112537464A (en) * | 2020-12-03 | 2021-03-23 | 上海空间电源研究所 | Flexible solar cell wing |
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