CN117699060A - Typical microsatellite solar wing - Google Patents
Typical microsatellite solar wing Download PDFInfo
- Publication number
- CN117699060A CN117699060A CN202311850306.1A CN202311850306A CN117699060A CN 117699060 A CN117699060 A CN 117699060A CN 202311850306 A CN202311850306 A CN 202311850306A CN 117699060 A CN117699060 A CN 117699060A
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- Prior art keywords
- wing
- substrate
- star
- substrate structure
- microsatellite
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- 239000000758 substrate Substances 0.000 claims abstract description 53
- 108091092878 Microsatellite Proteins 0.000 claims abstract description 19
- 230000007246 mechanism Effects 0.000 claims abstract description 15
- 238000009434 installation Methods 0.000 claims abstract description 5
- 229910001285 shape-memory alloy Inorganic materials 0.000 abstract description 9
- 238000012423 maintenance Methods 0.000 abstract description 3
- 229910052751 metal Inorganic materials 0.000 description 4
- 239000002184 metal Substances 0.000 description 4
- 230000006870 function Effects 0.000 description 3
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 description 2
- 230000009471 action Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 229910001092 metal group alloy Inorganic materials 0.000 description 2
- 230000003647 oxidation Effects 0.000 description 2
- 238000007254 oxidation reaction Methods 0.000 description 2
- 229920001721 polyimide Polymers 0.000 description 2
- 229910052709 silver Inorganic materials 0.000 description 2
- 239000004332 silver Substances 0.000 description 2
- JBRZTFJDHDCESZ-UHFFFAOYSA-N AsGa Chemical compound [As]#[Ga] JBRZTFJDHDCESZ-UHFFFAOYSA-N 0.000 description 1
- 241000531116 Blitum bonus-henricus Species 0.000 description 1
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 235000008645 Chenopodium bonus henricus Nutrition 0.000 description 1
- 229910001218 Gallium arsenide Inorganic materials 0.000 description 1
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 239000012939 laminating adhesive Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000007747 plating Methods 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 229910052710 silicon Inorganic materials 0.000 description 1
- 239000010703 silicon Substances 0.000 description 1
- 229920002379 silicone rubber Polymers 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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
-
- 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
-
- 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
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
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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
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Photovoltaic Devices (AREA)
Abstract
The invention discloses a typical microsatellite solar wing, which is arranged on a star body and comprises: the solar cell comprises a star body, a connecting mechanism and a substrate structure, wherein the connecting mechanism is arranged on the star body, the substrate structure is arranged on the connecting structure and used for providing an installation environment for the solar cell, the connecting mechanism comprises a hinge arranged on the star body and used for connecting the substrate structure, and a memory alloy type unlocking device arranged on the star body and used for locking the substrate structure, and the connecting mechanism is used for connecting the star body with the substrate structure. The hinge and the unlocking device are selected as goods shelf products, and then are assembled with the corresponding installation positions of the base plate through screws or pins, so that the satellite solar wing has the advantages of modularization, good operability, easy maintenance and replacement, time and cost saving, basically negligible unlocking impact, contribution to keeping the attitude of the satellite and the like.
Description
Technical Field
The invention relates to the technical field of aerospace power supplies, in particular to a typical microsatellite solar wing.
Background
In recent years, a large number of commercial microsatellites have been launched into space, especially in low orbit. As a primary source of power for satellites during orbit, solar wings are indispensable. At present, most commercial satellite companies focus on the design of low-orbit microsatellites with the level of 50kg and below, and the design tends to be small in envelope, short in production period, simple in structure, flexible in transportation, low in cost, various in functions, small in size and the like. Generally, solar wings used in traditional aerospace are more suitable for large-volume, multifunctional, high-power and long-life satellites, and obviously are not matched with commercial aerospace requirements.
Disclosure of Invention
The present invention is directed to a typical microsatellite solar wing to solve the above-mentioned problems.
In order to achieve the above purpose, the present invention provides the following technical solutions: a typical microsatellite solar wing disposed on a star, comprising:
the connecting mechanism is arranged on the star.
And the substrate structure is arranged on the connecting structure and is used for providing an installation environment for the solar cell.
Preferably, the connecting mechanism comprises a hinge arranged on the star body and used for connecting the substrate structure, and an unlocking device arranged on the star body and used for locking the substrate structure, and the connecting mechanism is used for connecting the star body and the substrate structure.
Preferably, the hinge is connected with a traction spring, the traction spring is used for traction of the substrate structure, and the traction spring can drive the substrate structure to open automatically.
Preferably, the substrate structure comprises a body-mounted wing substrate arranged on the star body and a deployment wing substrate arranged on the connecting mechanism, and the number of the deployment wing substrates is two.
Preferably, the inner side of the unfolding wing base plate is provided with a mounting hole, the locking hole is matched with the unlocking device in size, and the unlocking device can lock the unfolding wing base plate through the mounting hole.
Preferably, solar cell circuits are connected to the body-mounted wing substrate and the unfolding wing substrate, and can provide power for stars.
Preferably, the solar cell circuits are arranged on the body-mounted wing substrate and the unfolding wing substrate in an array manner, so that a current output function is realized.
Compared with the prior art, the invention has the beneficial effects that: according to the typical microsatellite solar wing, as the solar wing interface is simple, the selected hinges are all goods shelf products, and then the hinges are assembled with the base plate hinge mounting positions through screws or pins, so that the microsatellite solar wing has the advantages of good operability, modularization, easiness in maintenance and replacement, time and cost saving, basically negligible unlocking impact due to the adoption of the memory alloy type unlocking mechanism, contribution to the maintenance of the attitude of the microsatellite and the like.
Drawings
FIG. 1 is an overall exploded view of an embodiment of the present invention;
FIG. 2 is a schematic drawing showing the overall folding of an embodiment of the present invention;
FIG. 3 is a schematic diagram of a star according to an embodiment of the present invention;
fig. 4 is a schematic diagram of a solar cell circuit according to an embodiment of the invention.
In the figure:
1. solar cell circuit 2, unfolding wing substrate 3, and body-mounted wing substrate
4. Hinge 5, unlocking device 6 and star
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
As shown in fig. 1 and 2, the present invention provides a technical solution: a typical microsatellite solar wing, which is disposed on a star 6, the star 6 being a microsatellite, comprising: the solar cell module comprises a connecting mechanism and a substrate structure, wherein the connecting mechanism is arranged on a star 6 and is used for connecting the star 6 with the substrate structure, the substrate structure is arranged on the connecting mechanism and is used for providing energy for the star 6, and the substrate structure is used for bearing the solar cell circuit 1.
As shown in fig. 4, the connection mechanism comprises four hinge hinges 4 arranged on the star 6 and used for connecting the substrate structure, each hinge 4 is composed of a group of two hinges, two hinges arranged on two sides of the star 6, a spring, a fastener and the like, the hinge hinges 4 are connected with a traction spring, the traction spring is used for traction of the substrate structure, the hinge hinges 4 are in a natural state and are in an unfolding and locking state, after unlocking, the hinge hinges are in a gathering state through compression of the traction spring, after unlocking, the unlocking device 5 is unlocked, the male hinge and the female hinge are opened under the action of the traction spring and are locked in place, the driving sailboard is opened and output in-place signals, the hinge is connected with the substrate and the star 6 through screws or pins, the hinge main body material is aluminum alloy, the installation surface is subjected to natural-color conductive oxidation and is in direct contact with the metal shell of the star 6, the grounding effect is achieved, the traction spring is made of stainless steel, the surface is plated with cold welding prevention plating layers and memory alloy 5 which is arranged on the star 6 and is used for locking a substrate structure, the number of the memory alloy 5 is consistent with that of hinge hinges 4, the number of the memory alloy 5 is four, each two are in a group, the memory alloy 5 is arranged on two sides of the star 6, when the unfolding wing substrate 2 is in a folded state, the unlocking device plays a fixing and supporting role, when the unlocking current is controlled, the memory alloy in the unlocking device 5 is heated to deform to release the unfolding wing substrate 2, the unfolding state is reached, after the unlocking is carried out, the memory alloy in the unlocking device 5 is restored to an initial state, the unfolding wing substrate 2 can continue to carry out pressing operation to realize the purpose of repeatable unlocking, the unlocking device is connected with the substrate and the star 6 through screws, the main body material of the unlocking device is aluminum alloy, the mounting surface is subjected to natural-color conductive oxidation and is in direct contact with the metal shell of the star 6, acting as a ground.
As shown in fig. 3, the substrate structure includes a body-mounted wing substrate 3 disposed on a star 6, the body-mounted wing substrate 3 and an unfolding wing substrate 2 are connected with a solar cell circuit 1, the solar cell circuit 1 adopts a serial-parallel mode, voltage requirements can be met, the front-end circuit is connected in parallel, circuit reliability is improved, a three-junction gallium arsenide solar cell is selected as a cell, the cell has higher photoelectric conversion efficiency than a silicon solar cell, a glass cover plate is attached to the surface of the cell for space protection, an antireflection film is plated on the surface of the cover plate, the solar cell circuit 1 is attached to a polyimide film surface of the substrate through silicon rubber, interconnection between the solar cell circuits 1 and the front-end circuit are realized through silver strips, electric energy loss is reduced, finally, wires are welded to the connector input star 6 on the silver strips, electric energy output function is realized, the solar cell circuit 1 is disposed on the body-mounted wing substrate 3 and the unfolding wing substrate 2 in an array, the body-mounted wing substrate 3 and the unfolding wing substrate 2 are disposed on a connecting mechanism, the two-layer carbon fiber composite material panel, aluminum honeycomb adhesive, a (four sides) and polyimide film are formed by laminating adhesive, the metal alloy film and a metal film is arranged at the mounting hole is matched with a mounting hole of a metal alloy mounting hole, and a memory hole is formed in the mounting hole and the metal film.
According to the above-mentioned illustration, when the satellite is in a state before launching, the unfolding wing base plate 2 is folded and compressed, the hinge 4 and the unlocking device 5 play a role in fixing and supporting the unfolding wing base plate 2, after the star 6 is unfolded or enters a track, when the ground passes through an instruction, the storage battery in the star 6 is discharged, current enters the unlocking device, the memory alloy in the unlocking device 5 is electrified and generates heat to deform, and the unfolding wing base plate 2 is unlocked, at this time, the solar wing is unfolded under the effect of the hinge, the hinge is locked after reaching a set position, the unfolding wing base plate 2 completes the unfolding action, and when the solar battery circuit 1 is used for the day, the solar battery generates electric energy to be input into the star 6 to play a role in supplying power.
Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (7)
1. A typical microsatellite solar wing, which is mounted on a star, comprising:
the connecting mechanism is arranged on the star;
and the substrate structure is arranged on the connecting structure and is used for providing an installation environment for the solar cell.
2. A typical microsatellite solar wing according to claim 1 wherein: the connecting structure comprises a hinge arranged on the star body and used for connecting the substrate structure, and an unlocking device arranged on the star body and used for locking the substrate structure.
3. A typical microsatellite solar wing according to claim 2 wherein: and the hinge is connected with a traction spring, and the traction spring is used for traction of the substrate structure.
4. A typical microsatellite solar wing according to claim 1 or 2, characterized in that: the substrate structure comprises a body-mounted wing substrate arranged on the star body and a unfolding wing substrate arranged on the connecting structure.
5. An exemplary microsatellite solar wing according to claim 4 wherein: and the inner side of the unfolding wing base plate is provided with a mounting hole, and the locking hole is matched with the unlocking device in size.
6. An exemplary microsatellite solar wing according to claim 4 wherein: solar cell circuits are connected to the body-mounted wing substrate and the unfolding wing substrate.
7. A typical microsatellite solar wing according to claim 6 wherein: the solar cell circuits are arranged on the body-mounted wing substrate and the unfolding wing substrate in an array mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311850306.1A CN117699060A (en) | 2023-12-29 | 2023-12-29 | Typical microsatellite solar wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311850306.1A CN117699060A (en) | 2023-12-29 | 2023-12-29 | Typical microsatellite solar wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117699060A true CN117699060A (en) | 2024-03-15 |
Family
ID=90148037
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311850306.1A Pending CN117699060A (en) | 2023-12-29 | 2023-12-29 | Typical microsatellite solar wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117699060A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN120096837A (en) * | 2025-04-27 | 2025-06-06 | 深圳市魔方卫星科技有限公司 | A multi-layer solar wing adjustment device suitable for micro-satellites |
-
2023
- 2023-12-29 CN CN202311850306.1A patent/CN117699060A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN120096837A (en) * | 2025-04-27 | 2025-06-06 | 深圳市魔方卫星科技有限公司 | A multi-layer solar wing adjustment device suitable for micro-satellites |
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