CN213292738U - On-orbit flexible solar cell array unfolding device for spacecraft - Google Patents
On-orbit flexible solar cell array unfolding device for spacecraft Download PDFInfo
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- CN213292738U CN213292738U CN202022502073.4U CN202022502073U CN213292738U CN 213292738 U CN213292738 U CN 213292738U CN 202022502073 U CN202022502073 U CN 202022502073U CN 213292738 U CN213292738 U CN 213292738U
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- solar cell
- cell panel
- pressing device
- screw rod
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Abstract
The invention relates to the technical field of spacecrafts, in particular to an on-orbit flexible solar cell array unfolding device for a spacecraft, which comprises: the solar cell panel comprises an upper cover plate, a structural plate, a base, a satellite, a solar cell panel and a pressing device, wherein the upper cover plate is hinged with the structural plate, the satellite is connected with the solar cell panel, the pressing device comprises a Kevlar rope, a screw rod, a nut, a tension breaker and a heating cable, the Kevlar rope of the pressing device winds around the periphery of the structural plate for one circle, and two ends of the Kevlar rope are connected with two ends of the screw rod of the pressing device; the screw rod penetrates through the expanding breaker and is fastened in the expanding breaker by a nut; the ware that rises is made by memory alloy, under heating cable's effect, carries out the electric current heating, and the ware that rises takes place deformation expansion, makes the screw rod fracture, the utility model discloses a closing device extrudees the certain radian of formation to flexible solar cell panel with the structural slab, and solar panel can produce an elasticity this moment, utilizes this elasticity as the power supply, makes solar cell panel expand.
Description
Technical Field
The utility model relates to a spacecraft technical field, concretely relates to flexible solar cell array in orbit expandes device that spacecraft was used.
Background
The solar cell array is used as a main source of a satellite power supply, converts sunlight into electric energy on orbit and supplies power to equipment on the satellite. Except that a part of the microsatellites adopt the body-mounted solar cell array, most satellites adopt the expansion solar cell array, and the more energy required by the satellites, the larger area of the solar cell array is required.
The traditional satellite solar cell array structure is heavy and high in cost, and the microsatellite cannot carry a large-area traditional rigid solar cell array due to the limitation of volume and weight.
In order to make up for the defects, the invention provides an on-orbit flexible solar cell array unfolding device for a spacecraft, which is a patent No. CN106809407B granted to China "
The device is characterized in that gunpowder is arranged in a structural cabin, gas is generated by igniting and exploding the gunpowder, and the gas generated by explosion is used as a power source to expand the solar cell array.
The technical effect achieved by the device is that the solar array is unfolded.
The power device comprises a gas generator, a buffer gas tank, a gas path pipe and a remote control igniter, and the components are matched with each other to finish gas generation to form a power source so as to expand a solar cell array.
Disclosure of Invention
An object of the utility model is to provide an on-orbit flexible solar array expandes device has solved the problem that solar array expandes device power component quality heavy construction is complicated.
An on-orbit flexible solar cell array unfolding device for a spacecraft comprises an upper cover plate, a structural plate, a base, a satellite, a solar cell panel and a pressing device;
the upper cover plate is hinged with the structural plate, and the satellite is connected with the solar cell panel;
the pressing device comprises a Kevlar rope, a screw rod, a nut, a tension breaker and a heating cable;
the Kevlar of the pressing device winds around the periphery of the structural plate for one circle, and two ends of the Kevlar are connected with two ends of a screw rod of the pressing device; the screw rod penetrates through the expanding breaker and is fastened in the expanding breaker by a nut; the expanding breaker is made of memory alloy, and is heated by current under the action of a heating cable, so that the expanding breaker deforms and expands to break the screw rod, and the structural plate is unlocked and unfolded;
the solar panel is made of flexible materials, the solar panel has elasticity in the arrow direction after being compressed by the structural plate, and if the pressing force of the structural plate disappears, the elasticity in the arrow direction can enable the solar panel to be unfolded.
The utility model discloses beneficial effect:
the utility model discloses a closing device extrudees the certain radian of formation to flexible solar cell panel with the structural slab, and solar cell panel can produce an elasticity this moment, utilizes this elasticity as the power supply, makes solar cell panel expand.
The utility model discloses compare with prior art's power device structure simpler, the quality is lighter, can effectual reduction satellite quality to reduce the emission cost.
Drawings
Fig. 1 is a first cross-sectional view of an in-orbit flexible solar cell array deployment device for a spacecraft of the present invention.
Fig. 2 is a second cross-sectional view of the on-orbit flexible solar cell array deployment device for spacecraft of the present invention.
Fig. 3 is the solar cell panel of the on-orbit flexible solar cell array unfolding apparatus for spacecraft of the present invention.
Fig. 4 is the schematic structural diagram of the pressing device of the on-orbit flexible solar cell array unfolding apparatus for the spacecraft of the present invention.
Fig. 5 is a schematic structural view of the expanding breaker of the on-orbit flexible solar cell array unfolding apparatus for the spacecraft of the present invention.
11. An upper cover plate; 12. a structural panel; 13. a base; 14. a satellite; 15. a solar panel; 16. a pressing device; 161. a Kevlar cord; 162. a screw; 163. a nut; 164. a swelling breaker; 165. the cable is heated.
Detailed Description
The preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings, which are easily implemented by those having ordinary skill in the art to which the present invention pertains.
As shown in fig. 3 and 4, an in-orbit flexible solar cell array unfolding device for a spacecraft comprises an upper cover plate 11, a structural plate 12, a base 13, a satellite 14, a solar cell panel 15 and a pressing device 16;
as shown in fig. 3, the upper cover plate 11 is hinged with the structural plate 12, and the satellite 14 is connected with the solar cell panel 15;
as shown in fig. 4 and 5, the pressing device 16 includes a kevlar pull rope 161, a screw 162, a nut 163, a tension breaker 164, and a heating cable 165;
as shown in fig. 4 and 5, the kevlar pull line 161 of the pressing device 16 is wound around the structure plate 12 in one turn, and two ends of the kevlar pull line 161 are connected with two ends of the screw 162 of the pressing device 16; the screw 162 passes through the expanding breaker 164 and is fastened in the expanding breaker 164 by a nut 163; the expanding-breaking device 164 is made of memory alloy, and under the action of the heating cable 165, current heating is carried out, the expanding-breaking device 164 deforms and expands, the screw 162 is broken, and the structural plate 12 is unlocked and unfolded;
as shown in fig. 1 and fig. 2, the structural plate 12 is pressed against the solar cell panel 15 by the pressing device 16, the solar cell panel 15 is made of a flexible material, the solar cell panel 15 has an elastic force in the direction of arrow 1 after being pressed by the structural plate 12, and the elastic force in the direction of arrow 1 can expand the solar cell panel 15 if the pressing force of the structural plate 12 is removed.
The utility model discloses the theory of operation:
as shown in fig. 1 and 3, when the satellite 14 enters the orbit, the pressing device 16 deforms and expands the expanding device 164 under the action of the heating cable 165, the screw 162 is broken, the structural plate 12 is unlocked and unfolded, and the solar cell panel 15 is not pressed by the structural plate 12 because the structural plate 12 is unlocked, so that the solar cell panel 15 is unfolded in the direction of arrow 1 under the influence of the elastic force.
Claims (3)
1. An in-orbit flexible solar cell array deployment device for a spacecraft, comprising: the device comprises an upper cover plate (11), a structural plate (12), a base (13), a satellite (14), a solar cell panel (15) and a pressing device (16); the method is characterized in that: the upper cover plate (11) is hinged with the structural plate (12), the satellite (14) is connected with the solar cell panel (15), the satellite (14) is positioned at the lower end of the upper cover plate (11), the solar cell panel (15) is positioned inside the structural plate (12), the pressing device (16) comprises a Kevlar rope (161), a screw rod (162), a nut (163), an expanding breaker (164) and a heating cable (165), the Kevlar rope (161) of the pressing device (16) winds around the periphery of the structural plate (12) for one circle, two ends of the Kevlar rope (161) are connected with two ends of the screw rod (162) of the pressing device (16), the screw rod (162) penetrates through the expanding breaker (164), the screw rod (162) is fixed in the expanding breaker (164) through a nut (163), and under the action of a heating cable (165) arranged at one end of the expanding breaker (164), the structural plate (12) is tightly pressed on the solar cell panel (15) through the pressing device (16).
2. The on-orbit flexible solar cell array deployment device for the spacecraft of claim 1, wherein: the expanding-cutter (164) is made of memory alloy.
3. The on-orbit flexible solar cell array deployment device for the spacecraft of claim 1, wherein: the solar panel (15) is made of a flexible material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022502073.4U CN213292738U (en) | 2020-11-04 | 2020-11-04 | On-orbit flexible solar cell array unfolding device for spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022502073.4U CN213292738U (en) | 2020-11-04 | 2020-11-04 | On-orbit flexible solar cell array unfolding device for spacecraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213292738U true CN213292738U (en) | 2021-05-28 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022502073.4U Active CN213292738U (en) | 2020-11-04 | 2020-11-04 | On-orbit flexible solar cell array unfolding device for spacecraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213292738U (en) |
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2020
- 2020-11-04 CN CN202022502073.4U patent/CN213292738U/en active Active
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