CN112027118A - Solar cell array structure and unfolding method - Google Patents
Solar cell array structure and unfolding method Download PDFInfo
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- CN112027118A CN112027118A CN202010961486.0A CN202010961486A CN112027118A CN 112027118 A CN112027118 A CN 112027118A CN 202010961486 A CN202010961486 A CN 202010961486A CN 112027118 A CN112027118 A CN 112027118A
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- solar cell
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- cell array
- array structure
- rigid substrate
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- 238000000034 method Methods 0.000 title claims description 11
- 239000000758 substrate Substances 0.000 claims abstract description 67
- 230000007246 mechanism Effects 0.000 claims abstract description 14
- 238000000926 separation method Methods 0.000 claims description 7
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 6
- 239000004917 carbon fiber Substances 0.000 claims description 6
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 6
- 239000002131 composite material Substances 0.000 claims description 4
- 229920001721 polyimide Polymers 0.000 claims description 3
- 230000004044 response Effects 0.000 claims description 2
- 238000010586 diagram Methods 0.000 description 6
- 230000006835 compression Effects 0.000 description 4
- 238000007906 compression Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- 230000005855 radiation Effects 0.000 description 2
- 108091092878 Microsatellite Proteins 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010292 electrical insulation Methods 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
- B64G1/443—Photovoltaic cell arrays
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Photovoltaic Devices (AREA)
Abstract
The invention discloses a solar cell array structure which is arranged on the upper surface of a satellite and comprises a foldable structure formed by at least 1 semi-rigid substrate and a buffer substrate which are alternately arranged, a pressing point positioned on the foldable structure and a scissor-type unfolding and locking mechanism. Wherein the first surface of the semi-rigid substrate has a solar cell circuit disposed thereon.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a solar cell array structure and a deployment method thereof.
Background
The Solar cell Array is called Solar Array for short, is an Array formed by Solar cells on a spacecraft, and is formed by a plurality of single Solar cells with cover plates in a series-parallel mode according to power supply requirements. The solar energy collector has the advantages of large power, long service life, small mass, simple and reliable structure and the like, and can absorb the solar radiation energy and convert the solar radiation energy into electric energy in the space to provide a power source for the on-orbit spacecraft. In order to increase the area of the solar array to a greater extent and increase the power-to-mass ratio to achieve higher power without increasing the burden on the spacecraft, the solar array usually adopts an expandable structure.
But traditional expansion solar cell array structure generally uses the aluminium honeycomb panel of carbon fiber covering as the base plate to provide through the hinge between the torsional spring inter-plate and expand drive power and realize the locking, realize compressing tightly the release through setting up compressing tightly pole and firer cutterbar. However, the conventional solution has the following disadvantages:
1. the thickness of the substrate is as follows: the thickness of the base plate is about 25mm, and a gap of 20-30mm is left between every two base plates, so that the furled thickness of the whole wing is thicker. For a microsatellite with high power demand, the sailboard is even thicker and heavier than the satellite body, and occupies precious fairing space; meanwhile, for the single-wing unfolding-type star, the center of gravity of the traditional sailboard is greatly deviated after being unfolded, the unfolding fundamental frequency is low, and the difficulty is increased for the design of the attitude and orbit control scheme;
2. the demand of the compression point is more: the traditional solar cell array structure adopts a compression rod and a cutter to realize the folding and the release of the solar cell array structure and a mechanism, but in order to ensure the folding rigidity, the number of compression points can be increased along with the increase of the size of a sailboard. The pressing points are required to be provided with cutting devices, and the reliability of the system is reduced and on-board electric energy resources are occupied due to the addition of the cutting devices.
Disclosure of Invention
To solve some or all of the problems in the prior art, an aspect of the present invention provides a solar cell array structure disposed on an upper surface of a satellite, including:
at least one semi-rigid substrate having solar cell circuitry disposed on a first surface thereof;
at least one buffer substrate, which is arranged in a staggered way with the semi-rigid substrate to form a foldable structure;
the pressing points are positioned on the semi-rigid substrate and the buffer substrate and comprise pressing rods and cutters, the pressing points are used for folding and unfolding a foldable structure formed by the semi-rigid substrate and the buffer substrate, the pressing rods are used for ensuring that every two adjacent semi-rigid substrates and buffer substrates are tightly attached to each other when the solar cell array structure is pressed, and the cutters are used for cutting off the pressing rods when the solar cell array structure is required to be unfolded; and
and the unfolding locking mechanism is provided with a scissor-type structure body, the central point of the scissor-type structure body is hinged to the center of the connecting side of the semi-rigid substrate and the buffer substrate, and the tail end of the locking mechanism is fixed on the upper surface of the satellite.
Further, the first edge of the buffer substrate is rotatably connected to the second edge of the upper semi-rigid substrate, and the second edge of the buffer substrate is rotatably connected to the first edge of the lower semi-rigid substrate.
Further, the semi-rigid substrate is made of a carbon fiber composite material.
Further, the thickness of the semi-rigid substrate is 2 mm.
Further, the first surface of the semi-rigid substrate is covered with a polyimide film.
Further, the pinch points may also be used for inter-satellite separation.
In another aspect, the present invention provides a method for unfolding the solar cell array structure, including:
and after receiving a satellite separation response command, releasing the constraint of the pressing point, and unfolding to a preset position and locking under the driving of the unfolding and locking mechanism.
Further, the releasing of the constraint of the pinch point includes: and detonating the cutter, cutting off the pressing rod and releasing the pressing state of the solar cell array structure.
According to the solar cell array structure and the unfolding method provided by the invention, the carbon fiber composite material substrate is used for replacing the traditional carbon fiber aluminum honeycomb substrate, the shear type unfolding locking mechanism is used for driving the substrate to unfold and provide unfolding rigidity, and compared with the traditional rigid solar cell array structure and mechanism, the scheme has the advantages of light weight and small folding thickness. In addition, the solar cell array structure and the inter-satellite separation device can share a compression point, occupy less resources of an initiating explosive device, have low cost and are suitable for a one-rocket multi-satellite stacked satellite configuration.
Drawings
To further clarify the above and other advantages and features of embodiments of the present invention, a more particular description of embodiments of the present invention will be rendered by reference to the appended drawings. It is appreciated that these drawings depict only typical embodiments of the invention and are therefore not to be considered limiting of its scope. In the drawings, the same or corresponding parts will be denoted by the same or similar reference numerals for clarity.
Fig. 1 is a schematic structural diagram of a solar cell array structure according to an embodiment of the present invention;
fig. 2 is a schematic diagram illustrating a solar cell array structure in a folded state according to an embodiment of the invention;
fig. 3 is a schematic diagram showing an expanded state of a solar cell array structure according to an embodiment of the present invention;
fig. 4 is a schematic diagram illustrating a solar cell array structure according to an embodiment of the present invention in a state of being pressed against a satellite; and
fig. 5 is a schematic diagram showing a solar cell array structure according to an embodiment of the present invention in a stacked satellite configuration.
Detailed Description
In the following description, the present invention is described with reference to examples. One skilled in the relevant art will recognize, however, that the embodiments may be practiced without one or more of the specific details, or with other alternative and/or additional methods, materials, or components. In other instances, well-known structures, materials, or operations are not shown or described in detail to avoid obscuring aspects of the invention. Similarly, for purposes of explanation, specific numbers, materials and configurations are set forth in order to provide a thorough understanding of the embodiments of the invention. However, the invention is not limited to these specific details. Further, it should be understood that the embodiments shown in the figures are illustrative representations and are not necessarily drawn to scale.
Reference in the specification to "one embodiment" or "the embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the invention. The appearances of the phrase "in one embodiment" in various places in the specification are not necessarily all referring to the same embodiment.
It should be noted that the embodiment of the present invention describes the process steps in a specific order, however, this is only for the purpose of illustrating the specific embodiment, and does not limit the sequence of the steps. Rather, in various embodiments of the present invention, the order of the steps may be adjusted according to process adjustments.
In order to make up for the defects of the traditional deployable solar cell array structure, the invention provides a solar cell array structure and a deployment method thereof, and the scheme of the invention is further described below by combining with the embodiment drawings.
Fig. 1 is a schematic structural diagram of a solar cell array structure according to an embodiment of the present invention. As shown in fig. 1, a solar cell array structure 001 includes a semi-rigid substrate 101, a buffer substrate 102, a pressing point 103, and a deployment locking mechanism 104.
The semi-rigid substrate 101 has at least one, and a solar cell circuit is disposed on a first surface of the semi-rigid substrate 101. In order to reduce the weight of the solar cell array structure, in one embodiment of the present invention, the material of the semi-rigid substrate 101 is a carbon fiber composite material, and in another embodiment of the present invention, the thickness of the semi-rigid substrate 101 is 2 mm. In order to ensure electrical insulation of the solar cell circuit from the semi-rigid substrate, in one embodiment of the invention, the first surface of the semi-rigid substrate, i.e. the surface on which the solar cell circuit is arranged, is covered with a polyimide film.
At least one of the buffer substrates 102 is provided, and the buffer substrates 102 are arranged in a staggered manner with the semi-rigid substrates 101 to form a foldable structure, specifically, a first side of the buffer substrate 102 is rotatably connected with a second side of the upper semi-rigid substrate, and the second side of the buffer substrate is rotatably connected with the first side of the lower semi-rigid substrate. The buffer substrate 102 is mainly used for protecting the solar cell circuit from being damaged by pressure in a folded state.
The pressing points 103 are located on the semi-rigid substrate 102 and the buffer substrate 103, and in one embodiment of the present invention, there are four pressing points 103 located near four vertices of the semi-rigid substrate 102 and the buffer substrate 103. The pressing points 103 comprise pressing rods and cutters, and the pressing points are used for folding and unfolding a foldable structure formed by the semi-rigid substrate and the buffer substrate, wherein the pressing rods are used for ensuring that every two adjacent semi-rigid substrates and buffer substrates are tightly attached to each other when the solar cell array structure is pressed, as shown in fig. 2; and the cutter is used for cutting off the pressing rod when the solar cell array structure needs to be unfolded. In one embodiment of the present invention, when the solar cell array structure is applied to a stacked satellite configuration of one arrow multi-star as shown in fig. 5, the solar cell array structure 001 is sandwiched between the satellite body 501 and the upper layer satellite 502, and the pressing point 103 can also be used for inter-satellite separation.
The unfolding locking mechanism 104 has a scissor structure, the center point of the scissor structure is hinged to the center of the connecting edge of the semi-rigid substrate and the buffer substrate, the scissor structure can be unfolded to a designated angle and locked, and the unfolded state of the solar cell array structure is shown in fig. 3. The solar cell array structure is fixed on the upper surface of the satellite through the locking mechanism, and the state that the solar cell array structure 001 is folded and pressed on the satellite 501 is shown in fig. 4.
And after a satellite separation instruction is received, the constraint of the pressing point is released, and the solar cell array structure can be unfolded to a preset position and locked under the driving of the unfolding and locking mechanism. In an embodiment of the invention, the releasing of the constraint of the pressing point specifically includes that after a satellite separation instruction is received, the cutter is detonated to cut off the pressing rod, and the pressing state of the solar cell array structure is released.
While various embodiments of the present invention have been described above, it should be understood that they have been presented by way of example only, and not limitation. It will be apparent to persons skilled in the relevant art that various combinations, modifications, and changes can be made thereto without departing from the spirit and scope of the invention. Thus, the breadth and scope of the present invention disclosed herein should not be limited by any of the above-described exemplary embodiments, but should be defined only in accordance with the following claims and their equivalents.
Claims (7)
1. A solar cell array structure disposed on an upper surface of a satellite, comprising:
at least one semi-rigid substrate having solar cell circuitry disposed on a first surface thereof;
at least one buffer substrate, which is arranged in a staggered way with the semi-rigid substrate to form a foldable structure;
the pressing points are positioned on the semi-rigid substrate and the buffer substrate and comprise pressing rods and cutters, and the pressing points are configured to be capable of folding and unfolding a foldable structure formed by the semi-rigid substrate and the buffer substrate; and
and the unfolding locking mechanism is provided with a scissor-type structure body, the central point of the scissor-type structure body is hinged to the center of the connecting side of the semi-rigid substrate and the buffer substrate, and the tail end of the locking mechanism is fixed on the upper surface of the satellite.
2. The solar array structure of claim 1, wherein the first edge of the buffer substrate is rotatably coupled to the second edge of the upper semi-rigid substrate and the second edge of the buffer substrate is rotatably coupled to the first edge of the lower semi-rigid substrate.
3. The solar cell array structure of claim 1, wherein the semi-rigid substrate is a carbon fiber composite material.
4. The solar cell array structure of claim 1, wherein the semi-rigid substrate has a thickness of 2 mm.
5. The solar cell array structure of claim 1, wherein the first surface of the semi-rigid substrate is covered with a polyimide film.
6. A method of deploying a solar cell array structure as claimed in any one of claims 1 to 5, comprising:
and after receiving a satellite separation response command, releasing the constraint of the pressing point, and unfolding the foldable structure to a preset position and locking the foldable structure under the driving of the unfolding and locking mechanism.
7. The method of unrolling a solar cell array structure according to claim 6, in which the release of the constraint of the pinch points comprises: and detonating the cutter, cutting off the pressing rod and releasing the pressing state of the solar cell array structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010961486.0A CN112027118A (en) | 2020-09-14 | 2020-09-14 | Solar cell array structure and unfolding method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010961486.0A CN112027118A (en) | 2020-09-14 | 2020-09-14 | Solar cell array structure and unfolding method |
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| Publication Number | Publication Date |
|---|---|
| CN112027118A true CN112027118A (en) | 2020-12-04 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010961486.0A Pending CN112027118A (en) | 2020-09-14 | 2020-09-14 | Solar cell array structure and unfolding method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113291494A (en) * | 2021-07-12 | 2021-08-24 | 长光卫星技术有限公司 | High-expansion-ratio flexible solar wing unfolding mechanism |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5785280A (en) * | 1995-07-20 | 1998-07-28 | Space Systems/Loral, Inc. | Hybrid solar panel array |
| US6423895B1 (en) * | 1999-09-20 | 2002-07-23 | Aec-Able Engineering Co., Inc. | Solar array for satellite vehicles |
| US20040094193A1 (en) * | 2001-03-29 | 2004-05-20 | Freddy Geyer | Satellite solar generator structure comprising bracing elements between panels |
| CN103662098A (en) * | 2012-08-31 | 2014-03-26 | 上海宇航系统工程研究所 | Semi-rigid solar battery wing of spacecraft |
| CN105515503A (en) * | 2015-11-26 | 2016-04-20 | 中国电子科技集团公司第十八研究所 | Solar cell module fixation structure of string-tightening type semi-rigid board and fixation method thereof |
-
2020
- 2020-09-14 CN CN202010961486.0A patent/CN112027118A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5785280A (en) * | 1995-07-20 | 1998-07-28 | Space Systems/Loral, Inc. | Hybrid solar panel array |
| US6423895B1 (en) * | 1999-09-20 | 2002-07-23 | Aec-Able Engineering Co., Inc. | Solar array for satellite vehicles |
| US20040094193A1 (en) * | 2001-03-29 | 2004-05-20 | Freddy Geyer | Satellite solar generator structure comprising bracing elements between panels |
| CN103662098A (en) * | 2012-08-31 | 2014-03-26 | 上海宇航系统工程研究所 | Semi-rigid solar battery wing of spacecraft |
| CN105515503A (en) * | 2015-11-26 | 2016-04-20 | 中国电子科技集团公司第十八研究所 | Solar cell module fixation structure of string-tightening type semi-rigid board and fixation method thereof |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113291494A (en) * | 2021-07-12 | 2021-08-24 | 长光卫星技术有限公司 | High-expansion-ratio flexible solar wing unfolding mechanism |
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Application publication date: 20201204 |