CN112340068B - Solar sailboard unfolding system based on hot knife - Google Patents
Solar sailboard unfolding system based on hot knife Download PDFInfo
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- CN112340068B CN112340068B CN202011229723.0A CN202011229723A CN112340068B CN 112340068 B CN112340068 B CN 112340068B CN 202011229723 A CN202011229723 A CN 202011229723A CN 112340068 B CN112340068 B CN 112340068B
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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
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Abstract
A solar sailboard unfolding system based on a hot knife belongs to the technical field of spacecraft solar sailboard unfolding and locking. The invention solves the problems of larger separation impact and large forbidden distribution area required by a solar wing in the conventional compression release and expansion locking mode of the micro-nano satellite solar sailboard. Every sailboard and satellite body all through miniature hinged joint between, all pre-buried compress tightly on the sailboard and bury the piece, hot sword structrual installation is on satellite body, compresses tightly between the piece through the strong guy line connection, realizes the expansion of sailboard through the cutting of hot sword structure strong guy line, sets up a supporting seat at least between every sailboard and the satellite body, and every supporting seat all with satellite body rigid coupling. The method is used for compressing, releasing, unfolding and locking the micro-nano satellite solar sailboard. The device has the characteristics of low cost, simple structure, easiness in assembly, light weight, small impact, high sheet distribution rate, easiness in standardized modularization and the like.
Description
Technical Field
The invention relates to a solar sailboard unfolding system based on a hot knife, and belongs to the technical field of spacecraft solar sailboard unfolding and locking.
Background
In recent years, with the rise of commercial aerospace, the development of micro devices and components, integrated multifunctional structures, space plug and play, integrated comprehensive electronics and other technologies are widely applied to micro-nano satellites, new opportunities and challenges are brought to the design of the micro-nano satellites, the micro-nano satellites are developing towards high integration and high functions, the supply of energy sources cannot be separated from the realization of various complex functions on the satellites, the solar sailboards serve as important components of a power supply subsystem and play a vital role in the whole service life cycle of the satellites, the micro-nano satellites are small in size, and the energy sources provided by the body-mounted battery pieces cannot meet the energy source requirements of the high-function and high-density micro-nano satellites easily, so that the expandable solar sailboards are necessary for solving the problem of energy shortage of the high-function micro-nano satellites.
The compression release and the expansion locking of the micro-nano satellite solar array are key technologies of satellite in-orbit flight, and the stable compression state of the solar array can ensure that a solar cell has a good mechanical environment in an emission section, so that the performance cannot be influenced due to the damage caused by the severe environment of the emission section; the successful unlocking and locking of the solar sailboard can ensure the effective supply of energy when the satellite is in an in-orbit flight state, and the locking rigidity of the solar sailboard can ensure the reduction of disturbance of an attitude and orbit control system in the imaging and attitude adjusting process.
The traditional satellite deployable solar sailboard is usually compressed by initiating explosive devices such as cutters, and the solar sailboard is unlocked by the initiation of the initiating explosive devices after the solar sailboard enters the orbit.
Disclosure of Invention
The invention aims to solve the problems of large separation impact and large solar wing required cloth forbidden area in the existing compression release and expansion locking mode of the micro-nano satellite solar sailboard, and further provides a solar sailboard expansion system based on a hot knife.
The technical scheme adopted by the invention for solving the technical problems is as follows:
a solar sailboard unfolding system based on a hot knife comprises a satellite body and sailboards positioned on two sides of the satellite body,
the novel satellite navigation satellite.
Further, the miniature hinge comprises a male hinge, a female hinge, a rotating shaft and a locking pin, the male hinge is fixedly arranged on the satellite body, the female hinge is fixedly arranged on the sailboard, the male hinge is rotatably connected with the female hinge through the rotating shaft, a torsion spring is sleeved on the rotating shaft, a locking plate is integrally and fixedly arranged on one side of the female hinge, a positioning hole is formed in the locking plate, the locking pin is axially and slidably arranged on the male hinge along the rotating shaft, a compression spring is sleeved on the locking pin, and one end of the locking pin penetrates into the positioning hole when the sailboard is in an unfolded state.
Furthermore, an arc-shaped locking slide way is processed on one side of the locking plate, and one end of the locking slide way is communicated with the positioning hole.
Further, a male hinge switch sheet is installed on the male hinge, a female hinge switch sheet is installed on the female hinge, the male hinge switch sheet and the female hinge switch sheet are respectively connected to the whole satellite control system through cables to form a loop, when the sailboard is folded, the male hinge switch sheet is separated from the female hinge switch sheet, the loop is disconnected, and when the sailboard is unfolded to a limit position, the male hinge switch sheet is in contact with the female hinge switch sheet, and the loop is closed.
Furthermore, the hot knife structure comprises a packaging shell, a wire arrangement board penetrating through the packaging shell, a mounting seat axially slidably sleeved on the packaging shell, and a limit nut screwed on the packaging shell, wherein resistance wires are arranged on the wire arrangement board, insulating pressing plates are clamped between two sides of the wire arrangement board and the inner wall of the packaging shell, two end parts of the wire arrangement board are respectively connected with the two insulating pressing plates through screws, the mounting seat is fixedly installed on the surface of the satellite body, a pre-tightening spring is sleeved on the packaging shell between the limit nut and the mounting seat, and a fusing part is fixedly installed at one end of the wire arrangement board.
Furthermore, a convex edge is processed at one end of the packaging shell, a sliding channel is axially formed in the mounting seat, and the packaging shell is slidably mounted on the mounting seat through the convex edge and the sliding channel.
Furthermore, the pressing embedded parts penetrate through the arrangement of the sailboards, through holes are formed in the pressing embedded parts and the supporting seat, each pressing embedded part is provided with a locking nut and a rope tying device, the strong horse wire penetrates through the supporting seat and the through holes in the pressing embedded parts, two ends of the strong horse wire are tied to the two rope tying devices respectively, the pressing force of the strong horse wire is adjusted through the locking nuts, the pressing embedded parts are connected with escape-proof nuts, the strong horse wire is fused through heating of a hot knife when the sailboards are pre-unfolded, and the broken strong horse wire is prevented from being separated from the rope tying devices and the satellite body through the escape-proof nuts.
Further, the miniature hinges are arranged on two sides of one end of the satellite body, and the supporting seats are arranged on two sides of the other end of the satellite body.
Further, flexible rubber pad is installed to the one end that the satellite body was kept away from to the supporting seat.
Further, two miniature hinges are arranged between each sailboard and the satellite body.
Compared with the prior art, the invention has the following effects:
the method is used for compressing, releasing, unfolding and locking the micro-nano satellite solar sailboard.
The two sailboards are furled by a big force horse wire, the force which needs to be born by the big force horse wire in the launching section is calculated according to the weight of the sailboards and the overload of the selected rocket, and the number of the big force horse wire is selected according to the force;
the satellite main body energizes the hot knife for 5 seconds according to the program control instruction, and after the strong force guy wire is fused, the sailboards on the two sides are synchronously unfolded.
Through setting up the supporting seat, prevent that the windsurfing board from touching the satellite body when drawing in.
The cloth piece distributing device has the characteristics of low cost, simple structure, easiness in assembly, light weight, small impact, high cloth piece rate, easiness in standardized modularization and the like.
Drawings
FIG. 1 is a schematic front view of the present application;
FIG. 2 is a schematic top view of the present application;
FIG. 3 is an enlarged view at P of FIG. 2;
FIG. 4 is a schematic view of a first perspective structure of the micro hinge;
FIG. 5 is a second perspective view of the micro hinge;
FIG. 6 is a schematic perspective view of the supporting base;
FIG. 7 is a perspective view of a hot knife structure;
FIG. 8 is a main cross-sectional view of a hot knife configuration;
FIG. 9 is a cross-sectional schematic view of a windsurfing board;
FIG. 10 is an enlarged view at I of FIG. 9;
FIG. 11 is a schematic view of the tether;
figure 12 is a schematic view of the connection between the tether and the compression insert.
Detailed Description
The first embodiment is as follows: the embodiment is described with reference to fig. 1 to 12, and a solar sailboard unfolding system based on a hot knife comprises a satellite body 1 and sailboards 2 positioned at two sides of the satellite body 1,
it still includes miniature hinge 3, hot sword structure 4, supporting seat 5 and energetically strong guy 6, all is connected through miniature hinge 3 between every windsurfing board 2 and the satellite body 1, all pre-buried compress tightly on the windsurfing board 2 and bury piece 7, hot sword structure 4 is installed on satellite body 1, compresses tightly through energetically strong guy 6 between the piece 7 and connect, and the expansion of windsurfing board 2 is realized to energetically strong guy 6 through the cutting of hot sword structure 4, sets up a supporting seat 5 between every windsurfing board 2 and the satellite body 1 at least, and every supporting seat 5 all with satellite body 1 rigid coupling.
The method is used for compressing, releasing, unfolding and locking the micro-nano satellite solar sailboard 2.
The hot knife structure 4 is at least one and plays a role of cutting the big force horse wire 6 to realize the unfolding of the windsurfing board 2. When the double-hot-cutter structures 4 symmetrically arranged on the two sides of the satellite body 1 are adopted, the two hot-cutter structures 4 are mutually backup, and the solar wing sailboards 2 on the two sides can be synchronously unfolded as long as one side cuts off the strong force motor line 6. The system reliability is high.
The number of the micro hinges 3 is at least two, and the micro hinges are preferably symmetrically arranged on two sides of the satellite body 1.
Each sailboard 2 is correspondingly arranged on two sides of the satellite body 1 through the miniature hinges 3 and is folded through one high-force horse wire 6, the force which needs to be born by the high-force horse wire 6 in the launching section can be calculated according to the weight of the sailboards 2 and the overload of the selected rocket, and the number of the high-force horse wire 6 is selected according to the force;
when the satellite main body enters a preset orbit, the satellite main body energizes the hot knife for 5 seconds according to the program control instruction, and after the large force motor wire 6 is fused, the sailboards 2 on the two sides are unfolded synchronously.
By arranging the supporting seat 5, the sailboard 2 is prevented from touching the satellite body 1 when being folded.
The sailboard 2 is a honeycomb sandwich board.
The cloth piece distributing device has the characteristics of low cost, simple structure, easiness in assembly, light weight, small impact, high cloth piece rate, easiness in standardized modularization and the like.
The miniature hinge 3 comprises a male hinge 31, a female hinge 32, a rotating shaft 33 and a locking pin 34, wherein the male hinge 31 is fixedly arranged on the satellite body 1, the female hinge 32 is fixedly arranged on the sailboard 2, the male hinge 31 is rotatably connected with the female hinge 32 through the rotating shaft 33, a torsion spring 35 is sleeved on the rotating shaft 33, a locking plate 36 is integrally and fixedly arranged on one side of the female hinge 32, a positioning hole is formed in the locking plate 36, the locking pin 34 is axially and slidably arranged on the male hinge 31 along the rotating shaft 33, a compression spring 37 is sleeved on the locking pin 34, and one end of the locking pin 34 penetrates into the positioning hole when the sailboard 2 is in an unfolded state. Under the unfolded state of the sailboard 2, the locking pin 34 penetrates through the positioning hole, the miniature hinge 3 is in a locking state, the locking position of the miniature hinge 3 can be adjusted by changing the opening position of the positioning hole on the locking plate 36, and therefore the sailboard 2 is controlled to be unfolded in place and form an angle with the satellite main body. In the state where the windsurfing board 2 is folded, the locking pin 34 is pulled out, and the windsurfing board 2 rotates around the rotating shaft 33 to be folded.
An arc-shaped locking slideway 36-1 is processed on one side of the locking plate 36, and one end of the locking slideway 36-1 is arranged to be communicated with the positioning hole. During the unfolding of the windsurfing board 2, the locking pin 34 slides along the locking slideway 36-1 until penetrating into the positioning hole to be locked.
The male hinge 31 is provided with a male hinge switch sheet 38, the female hinge 32 is provided with a female hinge switch sheet 39, the male hinge switch sheet 38 and the female hinge switch sheet 39 are respectively connected to the whole star control system through cables and form a loop, when the windsurfing board 2 is folded, the male hinge switch sheet 38 is separated from the female hinge switch sheet 39, the loop is disconnected, and when the windsurfing board 2 is unfolded to a limit position, the male hinge switch sheet 38 is contacted with the female hinge switch sheet 39, and the loop is closed. The male hinge switch sheet 38 and the female hinge switch sheet 39 form a simple unfolding-to-position switch of the windsurfing board 2. When the circuit is closed, the whole star control system detects that the windsurfing board 2 is unfolded to the extreme position. The female hinge switch piece 38 is made of aluminum alloy, and the male hinge switch piece 39 is made of a steel sheet with high elasticity, so that the structure is simple, and the reliability is high.
The hot knife structure 4 comprises a packaging shell 41, a wire arrangement board 42 penetrating the packaging shell 41, a mounting seat 43 axially slidably sleeved on the packaging shell 41, and a limit nut 44 screwed on the packaging shell 41, wherein resistance wires 45 are distributed on the wire arrangement board 42, insulating pressing plates 46 are clamped between two sides of the wire arrangement board 42 and the inner wall of the packaging shell 41, two end parts of the wire arrangement board 42 are respectively connected with the two insulating pressing plates 46 through screws 47, the mounting seat 43 is fixedly mounted on the surface of the satellite body 1, a pre-tightening spring 48 is sleeved on the packaging shell 41 between the limit nut 44 and the mounting seat 43, and a fusing part 49 is fixedly mounted at one end of the wire arrangement board 42. The through-hole that the inner wall of encapsulation casing 41 formed is the rectangle structure, guarantees the stable connection between wire arranging board 42, the insulation board and the encapsulation casing 41.
The resistance wires 45 can be arranged on one side of the wire arranging plate 42, and can also be arranged on two sides of the wire arranging plate 42 oppositely. The resistance wire 45 is arranged in a serpentine shape. So design, firstly can increase resistance wire 45's length in limited space, the convenient regulation to resistance wire 45 resistance, simultaneously, snakelike arranging can make resistance wire 45's distribution more even, and resistance wire 45 can generate heat in the use, and the heat can not excessively concentrate, convenient heat dissipation simultaneously.
The side surface of the wire arranging plate 42 is provided with a groove, and the resistance wires 45 arranged on the wire arranging plate 42 are embedded in the groove. The heat distribution can be uniform, the heat concentration is prevented, and the heat dissipation is convenient.
The insulating pressing plate 46 is made of polyimide.
The resistance wire 45 is a nickel-chromium alloy resistance wire. Both ends of the resistance wire 45 are connected to the power supply controller.
The working principle is as follows:
according to the overall requirement, the resistance value required by the resistance wire 45 is calculated by combining the distribution of the power subsystem to the energy source, the maximum allowable power current and the power time of the satellite power supply and other factors, so as to adjust the length of the resistance wire 45 and the routing circuit of the resistance wire in the wiring board 42 and arrange the wiring, the two ends of the wired wiring board 42 are clamped by the polyimide insulating pressing plate 46, then the combined body is put into the packaging shell 41 of the hot knife, the wiring board 42 and the polyimide insulating pressing plate 46 are fixed with the packaging shell 41 into a whole by the fastening screw 47, the hot knife structure 4 is packaged by the sealant after the lead wire is welded at the lead-out end, only the fusing part 49 is exposed, the whole hot knife is installed on the surface of the satellite body 1 by the installation seat 43, the fusing part 49 is contacted with the strong force horse wire 6 to be cut by the pre-tightening spring 48, the tightness of the pre-tightening spring 48 can be adjusted by adjusting the limit nut 44, thereby adjusting the degree of contact between the hot knife and the high force horse wire 6 to be cut.
According to the overall requirements of a certain type of noctilucent remote sensing navigation enhanced small satellite, the voltage of a storage battery on the satellite is 12V in a full state, the allowed maximum current is 6.5A, factors such as single machine starting of a launching section part, damping power consumption of attitude control components after separation of satellites and arrows and the like are considered, and the allowed current-on time of a hot knife is less than or equal to 5 s.
According to the analysis of the thermal control subsystem, the hot knife structure 4 needs to meet the use requirement of-60 ℃ to 120 ℃, an evaluation level high-low temperature cycle test is carried out on the hot knife structure 4 in a vacuum tank, and the test structure meets the task index requirement.
The hot knife structure 4 parameters of the present application are as follows:
weight: 35g of
Room temperature cutting time: less than or equal to 2s (adjustable)
Cutting current: less than or equal to 6.5A
Working temperature: -60 ℃ to 120 DEG C
The times of repeated use are as follows: not less than 30 times
Ground storage life: more than or equal to 5 years
The hot knife structure 4 is simple in structure, easy to assemble, light in weight, small in impact, low in production cost, short in manufacturing period, small and small, does not occupy space, and can meet the requirements of low research and development cost and high reliability of the micro-nano satellite.
A rib 50 is formed at one end of the package housing 41, a sliding channel 51 is formed on the mounting seat 43 along the axial direction, and the package housing 41 is slidably mounted on the mounting seat 43 through the rib 50 and the sliding channel 51. Through the rib 50 and the sliding channel 51, the packaging shell 41 is circumferentially limited, so that the packaging shell can only axially move along the mounting seat 43. Two through holes are processed on the packaging shell 41, each through hole is arranged along the radial direction of the packaging shell 41 in a penetrating manner, and one ends of two screws 47 are arranged in the two through holes in a penetrating manner corresponding to threads. By the design, the fixed connection between the wire arranging plate 42 and the packaging shell 41 is facilitated.
The pressing embedded part 7 penetrates through the arrangement of the sailboard 2, through holes are formed in the pressing embedded part 7 and the supporting seat 5, each pressing embedded part 7 is provided with a locking nut 8 and a rope tying device 9, the large force horse wire 6 penetrates through the supporting seat 5 and the through holes in the pressing embedded part 7, two ends of the large force horse wire 6 are tied to the two rope tying devices 9 respectively, the pressing force of the large force horse wire 6 is adjusted through the locking nuts 8, the pressing embedded part 7 is connected with an escape-proof nut 10, when the sailboard 2 is pre-unfolded, the large force horse wire 6 is fused through heating of a hot knife, and the large force horse wire 6 which is disconnected is prevented from being separated from the rope tying devices 9 and the satellite body through the escape-proof nut 10. The furled sailboards 2 are compacted by a big force guy 6. Two ends of the strong horse wire 6 are connected to the compressing embedded part 7 through the rope tying device 9, the locking nut 8 rotates outwards until a preset numerical value of the micro-torque measuring device is met, then the escape-proof nut 10 is screwed on the outer side of the compressing embedded part 7, the rope tying device 9 is of an I-shaped structure and penetrates through the compressing embedded part 7 in the radial direction, the locking nut and the escape-proof nut are arranged on two sides of the rope tying device respectively, the escape-proof nut 10 is used for preventing the rope tying device 9 from unrestrained flying out from two ends to form space garbage after the strong horse wire 6 is disconnected, and meanwhile, the rope tying device is prevented from damaging solar cell pieces on a sailboard in the flying out process.
The miniature hinge 3 is installed in one end both sides of satellite body 1, supporting seat 5 is installed in another tip both sides of satellite body 1. Preventing the sailboard 2 from touching the satellite body 1 when folded.
One end of the supporting seat 5 far away from the satellite body 1 is provided with a flexible rubber pad 11. By the design, the mechanical response of the sailboard 2 in the whole satellite launching section can be reduced.
Two miniature hinges 3 are arranged between each sailboard 2 and the satellite body 1. The stable unfolding and folding actions of the sailboard 2 are ensured.
Claims (9)
1. The utility model provides a solar sailboard system of expandes based on hot sword, it includes satellite body (1) and is located sailboard (2) of satellite body (1) both sides, its characterized in that: the satellite navigation; compress tightly and bury piece (7) and run through sailboard (2) setting, compress tightly and bury on piece (7) and all seted up the through-hole on supporting seat (5), every compresses tightly and buries and all installs lock nut (8) and tether device (9) on piece (7), powerful horse wire (6) pass supporting seat (5) and compress tightly the through-hole on burying piece (7), and the both ends of powerful horse wire (6) are tied to two tether devices (9) respectively, adjust the packing force of powerful horse wire (6) through lock nut (8), compress tightly and bury and be connected with on piece (7) and prevent escaping nut (10), when sailboard (2) are pre-opened, through heating fusing powerful horse wire (6) to the hot knife, prevent horse wire (6) of disconnection from breaking away from tether device (9) and satellite body through preventing escaping nut (10).
2. The hot knife-based solar windsurfing board deployment system of claim 1, wherein: the miniature hinge (3) comprises a male hinge (31), a female hinge (32), a rotating shaft (33) and a locking pin (34), the male hinge (31) is fixedly arranged on the satellite body (1), the female hinge (32) is fixedly arranged on the sailboard (2), the male hinge (31) is rotatably connected with the female hinge (32) through the rotating shaft (33), a torsion spring (35) is sleeved on the rotating shaft (33), a locking plate (36) is integrally and fixedly arranged on one side of the female hinge (32), a positioning hole is formed in the locking plate (36), the locking pin (34) is axially and slidably arranged on the male hinge (31) along the rotating shaft (33), a compression spring (37) is sleeved on the locking pin (34), and one end of the locking pin (34) penetrates through the positioning hole in the unfolded state of the sailboard (2).
3. The hot knife-based solar windsurfing board deployment system of claim 2, wherein: an arc-shaped locking slideway (36-1) is processed on one side of the locking plate (36), and one end of the locking slideway (36-1) is communicated with the positioning hole.
4. The hot-knife-based solar windsurfing board deployment system of claim 2 or 3, wherein: the sail board control system is characterized in that a male hinge switch sheet (38) is installed on the male hinge (31), a female hinge switch sheet (39) is installed on the female hinge (32), the male hinge switch sheet (38) and the female hinge switch sheet (39) are connected to the whole star control system through cables respectively to form a loop, when the sail board (2) is folded, the male hinge switch sheet (38) is separated from the female hinge switch sheet (39), the loop is disconnected, and when the sail board (2) is unfolded to a limit position, the male hinge switch sheet (38) is in contact with the female hinge switch sheet (39), and the loop is closed.
5. The hot knife-based solar windsurfing board deployment system of claim 1, wherein: the hot knife structure (4) comprises a packaging shell (41), a wiring board (42) penetrating into the packaging shell (41), a mounting seat (43) axially slidably sleeved on the packaging shell (41) and a limiting nut (44) screwed on the packaging shell (41), wherein resistance wires (45) are distributed on the wiring board (42), insulating pressing plates (46) are clamped between the two sides of the wiring board (42) and the inner wall of the packaging shell (41), the two end parts of the wiring board (42) and the two insulating pressing plates (46) are connected through screws (47) respectively, the mounting seat (43) is fixedly mounted on the surface of the satellite body (1), a pre-tightening spring (48) is sleeved on the packaging shell (41) between the limiting nut (44) and the mounting seat (43), and a fusing part (49) is fixedly mounted at one end of the wiring board (42).
6. The hot knife-based solar windsurfing board deployment system of claim 5, wherein: a rib (50) is processed at one end of the packaging shell (41), a sliding channel (51) is axially formed in the mounting seat (43), and the packaging shell (41) is slidably mounted on the mounting seat (43) through the rib (50) and the sliding channel (51).
7. The hot knife-based solar windsurfing board deployment system of claim 1, wherein: the miniature hinge (3) is arranged on two sides of one end of the satellite body (1), and the supporting seat (5) is arranged on two sides of the other end of the satellite body (1).
8. The hot knife-based solar windsurfing board deployment system of claim 1, wherein: one end of the supporting seat (5) far away from the satellite body (1) is provided with a flexible rubber pad (11).
9. The hot knife-based solar windsurfing board deployment system of claim 1, wherein: two miniature hinges (3) are arranged between each sailboard (2) and the satellite body (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011229723.0A CN112340068B (en) | 2020-11-06 | 2020-11-06 | Solar sailboard unfolding system based on hot knife |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011229723.0A CN112340068B (en) | 2020-11-06 | 2020-11-06 | Solar sailboard unfolding system based on hot knife |
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| CN112340068A CN112340068A (en) | 2021-02-09 |
| CN112340068B true CN112340068B (en) | 2022-04-15 |
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| CN113148229B (en) * | 2021-03-24 | 2022-08-12 | 上海埃依斯航天科技有限公司 | Two-dimensional three-folding solar cell array for satellite |
| CN113071719B (en) * | 2021-04-30 | 2023-02-03 | 北京吾天科技有限公司 | Double-hot-cutter type compression and release mechanism |
| CN113104238B (en) * | 2021-05-20 | 2022-08-02 | 中国电子科技集团公司第十八研究所 | Circuit for preventing fault of solar wing spreading indicating switch |
| CN113401369A (en) * | 2021-06-07 | 2021-09-17 | 长光卫星技术有限公司 | High-efficient expansion heat pipe radiation radiator |
| CN113247312B (en) * | 2021-07-14 | 2021-10-15 | 北京智星空间技术研究院有限公司 | Unlocking and unfolding structure of cubic star solar sailboard |
| CN113753266A (en) * | 2021-09-23 | 2021-12-07 | 北京国电高科科技有限公司 | Fuse type pressing and releasing device |
| CN115848646B (en) * | 2022-12-16 | 2023-10-27 | 苏州馥昶空间技术有限公司 | Supporting mechanism of space camera |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106275515A (en) * | 2015-06-05 | 2017-01-04 | 北京信威通信技术股份有限公司 | A kind of development mechanism of satellite sun windsurfing |
| CN204726686U (en) * | 2015-06-05 | 2015-10-28 | 北京信威通信技术股份有限公司 | A kind of development mechanism of satellite sun windsurfing |
| CN205396581U (en) * | 2016-03-11 | 2016-07-27 | 北京空间飞行器总体设计部 | Microminiature fuse ware |
| CN106564626B (en) * | 2016-10-14 | 2019-09-17 | 上海微小卫星工程中心 | The compression relieving mechanism of wing group |
| CN106628267B (en) * | 2016-10-28 | 2019-04-09 | 浙江大学 | A kind of expansion of skin Nano satellite solar energy turnover panel and locking device |
| CN106584599B (en) * | 2016-12-06 | 2018-09-28 | 山东航天电子技术研究所 | A kind of thermal cutting formula cable separation arrangement |
| CN207346124U (en) * | 2017-10-09 | 2018-05-11 | 长光卫星技术有限公司 | Microsatellite solar wing spreading locking device |
| CN109229431B (en) * | 2018-09-11 | 2021-06-11 | 北京空间机电研究所 | Non-explosive unlocking device and locking and unlocking method |
| CN209939004U (en) * | 2019-02-27 | 2020-01-14 | 上海宇航系统工程研究所 | Inward-folding micro-nano satellite solar wing |
| CN111806723B (en) * | 2019-04-11 | 2021-11-12 | 武汉珈鹰智能科技有限公司 | Compression release mechanism for satellite solar sailboard |
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2020
- 2020-11-06 CN CN202011229723.0A patent/CN112340068B/en active Active
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Denomination of invention: A solar panel deployment system based on thermal knife Granted publication date: 20220415 Pledgee: Jilin Shuangyang Rural Commercial Bank Co.,Ltd. Ecological Square sub branch Pledgor: Changguang Satellite Technology Co.,Ltd. Registration number: Y2024220000052 |
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