CN113247312A - Unlocking and unfolding structure of cubic star solar sailboard - Google Patents
Unlocking and unfolding structure of cubic star solar sailboard Download PDFInfo
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- CN113247312A CN113247312A CN202110794503.0A CN202110794503A CN113247312A CN 113247312 A CN113247312 A CN 113247312A CN 202110794503 A CN202110794503 A CN 202110794503A CN 113247312 A CN113247312 A CN 113247312A
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- solar
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- unlocking
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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
Abstract
The invention provides a cubic star solar array panel unlocking and unfolding structure which can save space and reduce mechanism complexity and achieve the purpose of independent unfolding of a cubic star solar array panel, and the cubic star solar array panel unlocking and unfolding structure comprises a main support and two solar array panel assemblies symmetrically arranged at the end parts of two sides of the main support, wherein the two solar array panel assemblies are respectively connected with the main support in a rotating manner through unfolding hinges with elasticity, and after the solar array panel assemblies are folded, an unlocking mechanism is arranged on the main support; the unlocking mechanism comprises a hot knife mounting support fixedly mounted on the main support, a hot blade mounted on the hot knife mounting support, and pre-tightening ropes, the end portions of the pre-tightening ropes are respectively connected with the movable ends of the two solar wing sail panel assemblies, the other ends of the two pre-tightening ropes are respectively connected to the hot knife mounting support, the two pre-tightening ropes are located on the hot blade and can be burnt out after being heated by the hot blade, and after the pre-tightening ropes are burnt out, the two solar wing sail panel assemblies are unfolded through elastic potential energy of unfolding hinges.
Description
Technical Field
The invention relates to the technical field of solar sailboards, in particular to a cubic star solar sailboard unlocking and unfolding structure.
Background
The solar wing is the energy source of the satellite. Namely, a solar panel is a device for collecting solar energy, and is generally applied to energy supply of satellites and spacecrafts. The existing solar wings are almost completely arranged on the symmetrical plane of the satellite, and in the launching stage, the solar wings at two sides are folded on the star body and are supported by multiple points between the star body, so that the solar wings can bear the vibration environment of carrying; after the star and the arrow are separated, the unlocking function is completed according to the program control or remote control instruction, the constraint on the solar cell array is removed, and the solar wings on the two sides are symmetrically unfolded.
The traditional unlocking device for the solar wing adopts an explosion bolt or a memory alloy mode, the explosion bolt is heavy in weight and can generate impact, and the traditional unlocking device is not suitable for micro-nano satellites. Although the memory alloy has no impact influence and can be repeatedly used, one solar wing sailboard needs an unlocking mechanism, and the existing memory alloy unlocking device is large in size and weight and occupies too much space in the star.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, adapt to the practical requirements, provide an unlocking and unfolding structure of a cubic star solar array, save space, reduce the complexity of a mechanism, achieve the purpose of automatic unfolding of cubic star solar wings, and simultaneously realize the purpose of simultaneously unlocking double wings by using a single mechanism and returning an unlocking success signal.
In order to realize the purpose of the invention, the technical scheme adopted by the invention is as follows:
designing a cubic star solar array panel unlocking and unfolding structure, which comprises a main support and two solar array panel assemblies symmetrically arranged at the end parts of two sides of the main support, wherein the two solar array panel assemblies are respectively and rotatably connected with the main support through unfolding hinges with elastic force, and the two solar array panel assemblies can be turned towards two sides of the main support and are attached to two side walls of the main support; after the solar wing sail panel assembly is folded, an unlocking mechanism is arranged on the main support positioned at the movable end of the solar wing sail panel assembly; the unlocking mechanism comprises a hot knife mounting support fixedly mounted on the main support, a hot blade mounted on the hot knife mounting support, and pre-tightening ropes, the end portions of the pre-tightening ropes are respectively connected with the movable ends of the two solar wing sail panel assemblies, the other ends of the two pre-tightening ropes are respectively connected to the hot knife mounting support, the two pre-tightening ropes are located on the hot blade and can be burnt out after being heated by the hot blade, and after the pre-tightening ropes are burnt out, the two solar wing sail panel assemblies are unfolded through elastic potential energy of unfolding hinges.
The hot knife mounting bracket is provided with a wire pressing block, the hot knife blade is positioned on the wire pressing block, and the pre-tightening rope is positioned on the end part of the hot knife blade and supported by the wire pressing block.
The hot knife blade is characterized by further comprising a pre-tightening rope tightening mechanism, wherein the pre-tightening rope tightening mechanism comprises an adjusting piece, the adjusting piece is fixed on the hot knife mounting bracket, an extending part is arranged at the end part of the adjusting piece, and the extending part is located above a pre-tightening rope on the side part of the hot knife blade; the extension part is provided with a threaded hole, an adjusting bolt is connected with the threaded hole in an internal thread mode, the front end of the adjusting bolt abuts against the pre-tightening rope, and pressure is applied to the pre-tightening rope through the adjusting bolt to adjust tension of the pre-tightening rope.
And the two pressing rods on the two microswitches are arranged on the two sides of the hot knife mounting bracket and can be pressed by the end parts of the solar wing sail panel assemblies after the two solar wing sail panel assemblies are retracted.
The hot blades 48 are two main hot blades and backup hot blades, and the main hot blades and the backup hot blades are arranged in a close fit manner.
The hot blade is fixedly connected with the hot blade mounting bracket through the insulating sleeve.
The end connection of pretension rope has the bail, pretension rope pass through the bail with solar wing sail board component's end connection.
The bail is T shape, the round hole has been seted up on the tip of sun wing sail board subassembly, the opening of round hole is linear, the bail enters into through linear opening extremely it is fixed after 90 degrees rotations in the round hole.
The unfolding hinge comprises an upper hinge component A, an upper hinge component B, a torsion spring and a lower hinge, wherein the upper hinge component A and the upper hinge component B are arranged at intervals and are fixedly connected with an aluminum substrate on the solar wing sail panel assembly, the lower hinge is connected between the upper hinge component A and the upper hinge component B in a rotating mode through a rotating shaft, the torsion spring is sleeved on the rotating shaft, one end of the torsion spring is connected with the lower hinge, the other end of the torsion spring is connected with the aluminum substrate, and the torsion spring is right applied to the solar wing sail panel assembly, applies elasticity and enables the solar wing sail panel assembly to unfold.
Two copper sheets arranged at intervals are arranged on one unfolding hinge in the same solar wing sail panel assembly, the two copper sheets are fixed on the lower hinge, a groove is formed in the end portion of the aluminum substrate at the position corresponding to the torsion spring, a pressing rod extending towards the copper sheets is arranged in the groove, one end of each of the two copper sheets is fixed, the other end of each of the two copper sheets is suspended in the air and is a flexible movable end, and after the solar wing sail panel assembly is unfolded, the end portion of the pressing rod is located above the copper sheets and is arranged at intervals with the copper sheets above the pressing rod; when the solar wing sail panel assembly is retracted, the pressing rod presses the upper copper sheets and enables the two copper sheets to be in contact to achieve circuit communication.
The invention has the beneficial effects that:
according to the design, the solar wing sail panel assembly can be automatically detected after being unfolded in place, the solar wing sail panel assemblies of the double wings can be unlocked simultaneously through a single mechanism during unfolding, automatic unfolding can be achieved, the structural design is simple, the occupied space in a star is small, the unfolding is free of impact, the recovery cost is low, and only the pre-tightening rope needs to be replaced.
Drawings
FIG. 1 is a schematic diagram of the main structure of the solar sail panel assembly of the present design in the deployed state;
FIG. 2 is a schematic diagram of the main structure of the solar sail panel assembly of the present design in the stowed state;
FIG. 3 is a schematic diagram of the main structure of the solar sail panel assembly of the present design;
FIG. 4 is a schematic view of a rear view of the solar sail panel assembly of the configuration shown in FIG. 3;
FIG. 5 is a schematic view of the main structure of the auxiliary support assembly of the present design;
FIG. 6 is a schematic view of the main structure of the unlocking mechanism in the present design;
FIG. 7 is another schematic view of the release mechanism of FIG. 6;
FIG. 8 is a schematic view of the main structure of the unfolding hinge of the present design;
FIG. 9 is a schematic view of the main structure of the unfolding hinge with a switch at the root in the present design;
FIG. 10 is a schematic diagram of the circuit formed by the micro-switch and the hot blade in the present design.
Detailed Description
The invention is further illustrated with reference to the following figures and examples:
example 1: a cube star solar panel unlocking deployment structure, see fig. 1-10.
It includes main support 5, symmetry and installs in two solar wing array panels 1 of main support 5 both sides tip, two solar wing array panels 1 rotate through expansion hinge 2 that has elasticity respectively and connect with main support 5 on, and two solar wing array panels can overturn and laminate on the both sides wall of main support 5 to main support 5 both sides.
In the design, the solar wing sail panel assembly 1 comprises an aluminum substrate 11, the back of the aluminum substrate 11 is of a multi-rib characteristic, and has high rigidity under the condition of ensuring light weight, meanwhile, 4 solar cells 14 are pasted on the back of the aluminum substrate 11 and distributed with a plurality of holes 112, a plurality of solar cells 14 are pasted on the other side of the aluminum substrate 11, the whole star is charged by using a limited area as far as possible, through holes 113 are reserved on two corners of the aluminum substrate 11, and connecting wires of the solar cells 14 penetrate through the through holes 113 to be connected with a power supply controller inside the star body conveniently.
In this design, it unfold hinge 2 include hinge part A21, last hinge part B24, torsion spring 22, lower hinge 23, go up hinge part A21, go up hinge part B24 interval set up and all with aluminium base board 11 fixed connection on the sun wing sail board subassembly 1, lower hinge 23 rotates through the pivot to be connected between last hinge part A21, last hinge part B24, and the cover has in the pivot torsion spring 22, torsion spring 22's one end is connected with lower hinge 23, and the other end is connected with aluminium base board 11, just torsion spring 22 is right sun wing sail board subassembly is applyed elasticity and is impeld sun wing sail board subassembly 1 to unfold.
Furthermore, in the design, two copper sheets 25 arranged at intervals are arranged on one unfolding hinge in the same solar wing sail panel assembly to form an unfolding hinge 3 with a switch at the root, the two copper sheets 25 are fixed on the lower hinge 23, a groove is arranged at the end part of the aluminum substrate 11 corresponding to the torsion spring 22, a pressing rod 26 extending towards the copper sheets is arranged in the groove, one end of each of the two copper sheets 25 is fixed, the other end of each of the two copper sheets 25 is suspended in the air and is a flexible movable end, and after the solar wing sail panel assembly 1 is unfolded, the end part of each pressing rod 26 is arranged above the corresponding copper sheet and is arranged at an interval with the copper sheet above the corresponding pressing rod; after the solar wing sail panel assembly 1 is retracted, the pressing rod 26 presses the upper copper sheets and enables the two copper sheets to be in contact to achieve circuit communication, circuit conduction can be achieved through the contact of the two copper sheets, and therefore the controller can detect whether the two solar wing sail panel assemblies are unfolded or not through the two copper sheets.
Further, after the solar wing sail panel assembly 1 is retracted, an unlocking mechanism 4 is installed on the main support 5 located at the movable end of the solar wing sail panel assembly 1; the unlocking mechanism 4 comprises a hot knife mounting support 42 fixedly mounted on the main support, a hot blade 48 mounted on the hot knife mounting support 42, and pre-tightening ropes 43 with end portions respectively connected with the movable ends of the two solar wing sail panel assemblies 1, the other ends of the two pre-tightening ropes 43 are respectively connected to the hot knife mounting support 42, the two pre-tightening ropes 43 are located on the hot blade and can be burnt out after being heated by the hot blade, and after the pre-tightening ropes are burnt out, the two solar wing sail panel assemblies are unfolded through elastic potential energy of the unfolding hinge.
In this design, it has wired briquetting 44 to install on the hot sword installing support 42, hot blade 48 is located on the line briquetting 44, the rope 43 that tightens in advance is located on the 48 tip of hot blade and through line briquetting 44 supports, simultaneously, hot blade 48 is two and is main hot blade, the hot blade of backup respectively, and main hot blade, the hot blade of backup are hugged closely the setting, its the hot blade passes through insulating cover 47 and hot sword installing support 42 fixed connection.
The hot knife blade is characterized by further comprising a pre-tightening rope tightening mechanism, wherein the pre-tightening rope tightening mechanism comprises an adjusting piece 45, the adjusting piece 45 is fixed on the hot knife mounting bracket 42, an extending part is arranged at the end part of the adjusting piece 45, and the extending part is located above the pre-tightening rope on the side part of the hot knife blade; a threaded hole is formed in the extending part, an adjusting bolt 464 is connected to the threaded hole in an internal thread mode, the front end of the adjusting bolt 6 abuts against the pre-tightening rope 43, and pressure is applied to the pre-tightening rope 43 through the adjusting bolt 46 to adjust tension of the pre-tightening rope.
In the design, one pre-tightening rope can be used, the middle part of the pre-tightening rope is positioned on the hot blade, the two ends of the pre-tightening rope are respectively connected with the clamp 41, and the pre-tightening rope 43 is connected with the end part of the solar wing sail panel assembly 11 through the clamp 41. In this embodiment, the staple bolt 41 is T-shaped, a round hole has been seted up on the tip of solar wing sail panel assembly 1, the opening of round hole is linear, the staple bolt enters into through linear opening and fixes after rotating 90 degrees in the round hole.
Furthermore, in the present design, two sides of the hot knife mounting bracket 42 are further respectively provided with a micro switch 49 having a hold-down bar, the hold-down bars 13 on the two micro switches are arranged on two sides of the hot knife mounting bracket, and after the two solar wing panel assemblies 11 are retracted, the hold-down bars 13 on the two micro switches can be held down by the end portions of the solar wing panel assemblies to form a circuit conduction, the circuit is shown in fig. 10, the state of the solar wing panel assemblies 11 after being retracted can be detected by the micro switch 49 and the hold-down bars 13 thereon in combination with fig. 10, and whether the solar wing panel assemblies 11 are opened or not can also be detected.
Furthermore, in the design, the auxiliary support assemblies 12 are respectively arranged in the middle of the inner sides of the two solar wing sail panel assemblies 11, each auxiliary support assembly 12 comprises an auxiliary support core rod 121, 9 disc springs 122 and a screw 123, the auxiliary support core rod 121 is connected to the aluminum substrate, the 9 disc springs 122 are sleeved on the auxiliary support core rod 121 and are limited by the screws, and when the solar wing sail panel assemblies 11 are in a furled state, a single auxiliary support assembly 12 can provide about 100N of support force through the disc springs. The supporting force will be supported by the frame on the star when the auxiliary supporting mechanism is pressed. After the hot blade blows the pre-tightening rope and unlocks the solar wing sail panel assembly 11, the auxiliary support mechanism can assist in providing instantaneous unfolding drive to drive the solar wing sail panel assembly 11 to unfold.
When the device is used, firstly, the two solar wing sail assemblies 11 need to be reversely rotated towards two sides to enable the two solar wing sail assemblies 11 to be retracted, at the moment, a pre-tightening rope with a certain length is cut in advance, clamp nails are tied at two ends of the pre-tightening rope, then, the solar wings on the two sides are in a retracted state, the pre-tightening rope penetrates through a gap of a hot knife mounting support and is carried on the two hot knife blades, then, the clamp nails enter the round holes through linear openings and rotate for 90 degrees to realize the connection of the clamp nails with the round holes and an aluminum substrate, then, the pressing rods on the micro switches on the two sides are fluctuated to enable the micro switch pressing rods to press elastic pieces on the micro switches, the internal circuits of the micro switches are confirmed to be in a connected state, then, line pressing blocks and adjusting pieces are sequentially installed, and the tightening force of the pre-tightening rope on the aluminum substrates on the two sides is adjusted through the depth of the screwed adjusting bolts; at this time, the pressing rod presses on the copper sheets and enables the two copper sheets to be connected to realize internal circuit communication, and the end parts of the aluminum substrates at the movable ends of the two solar wing sail panel assemblies 11 press on the pressing rod.
When two solar wing sailboard assemblies 11 need to be unfolded, the spaceborne computer sends a heating instruction, the power supply sequence is that the main knife supplies power and the standby knife supplies power, the main knife supplies power for 120s, the standby knife supplies power for 120s, the total time is 240s, the power supply frequency is 5 times, after the hot blade is electrified and heated, the pre-tightening rope 41 is cut off, the solar wing sailboards on two sides are unfolded under the action of the unfolding hinges at the root parts, so that the purpose of releasing two solar wings is achieved, when the solar wing sailboards on two sides are unfolded, the two micro-switch pressing rods 13 can release the restraint of the elastic sheets on the micro-switches 49 on two sides, at the moment, the two paths of power supplies are in an open circuit, and the system stops electrifying the hot blade 48. If only one side is unfolded, the elastic sheet on the microswitch 49 on the unfolded side is bounced off, the power supply loop is in an open circuit, the program can continue to heat the hot blade under the condition that the pressing rods of the microswitches on the two sides are in an open state after the solar wing sailboards on the two sides are unfolded, the microswitches are in an open circuit, the main hot blade and the standby hot blade stop supplying power, when the solar wings on the two sides are unfolded, the two copper sheets of the unfolding hinge with the switch at the root are released from contact, the power supply state is changed, the state signal returns to the satellite-borne computer, and the situation that the solar wings are unfolded in place can be judged.
The embodiments of the present invention are disclosed as the preferred embodiments, but not limited thereto, and those skilled in the art can easily understand the spirit of the present invention and make various extensions and changes without departing from the spirit of the present invention.
Claims (10)
1. The utility model provides a cube star solar array panel unblock expandes structure, includes that main support, symmetry install in two solar array panel components of main support both sides tip, its characterized in that: the two solar wing sail panel assemblies are respectively rotatably connected with the main support through elastic unfolding hinges, and can be turned towards two sides of the main support and attached to two side walls of the main support; after the solar wing sail panel assembly is folded, an unlocking mechanism is arranged on the main support positioned at the movable end of the solar wing sail panel assembly; the unlocking mechanism comprises a hot knife mounting support fixedly mounted on the main support, a hot blade mounted on the hot knife mounting support, and pre-tightening ropes, the end portions of the pre-tightening ropes are respectively connected with the movable ends of the two solar wing sail panel assemblies, the other ends of the two pre-tightening ropes are respectively connected to the hot knife mounting support, the two pre-tightening ropes are located on the hot blade and can be burnt out after being heated by the hot blade, and after the pre-tightening ropes are burnt out, the two solar wing sail panel assemblies are unfolded through elastic potential energy of unfolding hinges.
2. The cube-star solar sail panel unlocking deployment structure of claim 1, wherein: the hot knife mounting bracket is provided with a wire pressing block, the hot knife blade is positioned on the wire pressing block, and the pre-tightening rope is positioned on the end part of the hot knife blade and supported by the wire pressing block.
3. A cube-star solar sail panel unlocking deployment structure as defined in claim 2, wherein: the hot knife blade is characterized by further comprising a pre-tightening rope tightening mechanism, wherein the pre-tightening rope tightening mechanism comprises an adjusting piece, the adjusting piece is fixed on the hot knife mounting bracket, an extending part is arranged at the end part of the adjusting piece, and the extending part is located above a pre-tightening rope on the side part of the hot knife blade; the extension part is provided with a threaded hole, an adjusting bolt is connected with the threaded hole in an internal thread mode, the front end of the adjusting bolt abuts against the pre-tightening rope, and pressure is applied to the pre-tightening rope through the adjusting bolt to adjust tension of the pre-tightening rope.
4. The cube-star solar sail panel unlocking deployment structure of claim 1, wherein: and the two pressing rods on the two microswitches are arranged on the two sides of the hot knife mounting bracket and can be pressed by the end parts of the solar wing sail panel assemblies after the two solar wing sail panel assemblies are retracted.
5. The cube-star solar sail panel unlocking deployment structure of claim 1, wherein: the hot blade is two and is main hot blade, the hot blade of backup respectively, and main hot blade, the hot blade of backup are hugged closely and are set up.
6. The cube-star solar sail panel unlocking deployment structure of claim 1, wherein: the hot blade is fixedly connected with the hot blade mounting bracket through the insulating sleeve.
7. The cube-star solar sail panel unlocking deployment structure of claim 1, wherein: the end connection of pretension rope has the bail, pretension rope pass through the bail with solar wing sail board component's end connection.
8. A cube-star solar sail panel unlocked deployment structure as defined in claim 7, wherein: the bail is T shape, the round hole has been seted up on the tip of sun wing sail board subassembly, the opening of round hole is linear, the bail enters into through linear opening extremely it is fixed after 90 degrees rotations in the round hole.
9. The cube-star solar sail panel unlocking deployment structure of claim 1, wherein: the unfolding hinge comprises an upper hinge component A, an upper hinge component B, a torsion spring and a lower hinge, wherein the upper hinge component A and the upper hinge component B are arranged at intervals and are fixedly connected with an aluminum substrate on the solar wing sail panel assembly, the lower hinge is connected between the upper hinge component A and the upper hinge component B in a rotating mode through a rotating shaft, the torsion spring is sleeved on the rotating shaft, one end of the torsion spring is connected with the lower hinge, the other end of the torsion spring is connected with the aluminum substrate, and the torsion spring is right applied to the solar wing sail panel assembly, applies elasticity and enables the solar wing sail panel assembly to unfold.
10. The cube-star solar sail unlocking deployment structure of claim 9, wherein: two copper sheets arranged at intervals are arranged on one unfolding hinge in the same solar wing sail panel assembly, the two copper sheets are fixed on the lower hinge, a groove is formed in the end portion of the aluminum substrate at the position corresponding to the torsion spring, a pressing rod extending towards the copper sheets is arranged in the groove, one end of each of the two copper sheets is fixed, the other end of each of the two copper sheets is suspended in the air and is a flexible movable end, and after the solar wing sail panel assembly is unfolded, the end portion of the pressing rod is located above the copper sheets and is arranged at intervals with the copper sheets above the pressing rod; when the solar wing sail panel assembly is retracted, the pressing rod presses the upper copper sheets and enables the two copper sheets to be in contact to achieve circuit communication.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110794503.0A CN113247312B (en) | 2021-07-14 | 2021-07-14 | Unlocking and unfolding structure of cubic star solar sailboard |
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| CN202110794503.0A CN113247312B (en) | 2021-07-14 | 2021-07-14 | Unlocking and unfolding structure of cubic star solar sailboard |
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| CN113247312B CN113247312B (en) | 2021-10-15 |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103662101A (en) * | 2013-11-20 | 2014-03-26 | 上海宇航系统工程研究所 | Repeatedly-unfolded-folded solar wing device suitable for lunar surface environment |
| CN106564626A (en) * | 2016-10-14 | 2017-04-19 | 上海微小卫星工程中心 | Compacting and releasing mechanism for wing cell |
| CN106628267A (en) * | 2016-10-28 | 2017-05-10 | 浙江大学 | Pico-nano-satellite solar turning plate unfolding and locking device |
| EP3339188A1 (en) * | 2016-12-23 | 2018-06-27 | Universite De Montpellier | Cubesat bus architecture |
| CN108674692A (en) * | 2018-04-04 | 2018-10-19 | 南京理工大学 | A kind of remote sensing microsatellite |
| CN109760856A (en) * | 2019-03-13 | 2019-05-17 | 北京微分航宇科技有限公司 | A kind of solar wing unlock unfolding mechanism using miniatured hinge |
| CN112340068A (en) * | 2020-11-06 | 2021-02-09 | 长光卫星技术有限公司 | Solar sailboard unfolding system based on hot knife |
-
2021
- 2021-07-14 CN CN202110794503.0A patent/CN113247312B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103662101A (en) * | 2013-11-20 | 2014-03-26 | 上海宇航系统工程研究所 | Repeatedly-unfolded-folded solar wing device suitable for lunar surface environment |
| CN106564626A (en) * | 2016-10-14 | 2017-04-19 | 上海微小卫星工程中心 | Compacting and releasing mechanism for wing cell |
| CN106628267A (en) * | 2016-10-28 | 2017-05-10 | 浙江大学 | Pico-nano-satellite solar turning plate unfolding and locking device |
| EP3339188A1 (en) * | 2016-12-23 | 2018-06-27 | Universite De Montpellier | Cubesat bus architecture |
| CN108674692A (en) * | 2018-04-04 | 2018-10-19 | 南京理工大学 | A kind of remote sensing microsatellite |
| CN109760856A (en) * | 2019-03-13 | 2019-05-17 | 北京微分航宇科技有限公司 | A kind of solar wing unlock unfolding mechanism using miniatured hinge |
| CN112340068A (en) * | 2020-11-06 | 2021-02-09 | 长光卫星技术有限公司 | Solar sailboard unfolding system based on hot knife |
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