CN117963172A - Micro-nano satellite unfolding mechanism - Google Patents
Micro-nano satellite unfolding mechanism Download PDFInfo
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- CN117963172A CN117963172A CN202410319995.1A CN202410319995A CN117963172A CN 117963172 A CN117963172 A CN 117963172A CN 202410319995 A CN202410319995 A CN 202410319995A CN 117963172 A CN117963172 A CN 117963172A
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Abstract
The invention discloses a micro-nano satellite unfolding mechanism which comprises a satellite main body, a solar wing assembly, a data transmission antenna assembly, an electric detection antenna assembly, a first rope limiting piece, a first binding rope and a first cutting mechanism, wherein the first binding rope is connected with the satellite main body; the solar wing component comprises a sailboard swinging mechanism, a solar sailboard and a sailboard 180-degree unfolding mechanism; the solar sailboard, the data transmission base support and the electric detection connecting rod are provided with first rope limiting parts; the first rope is wound on the outer side of the satellite main body through a first rope limiting piece, and the solar wing assembly, the data transmission antenna assembly and the electric detection antenna assembly are kept in a folded state; the first cutting mechanism is arranged on the satellite main body and corresponds to the first binding rope. The invention can realize the rapid folding and unfolding of the solar wing, the data transmission antenna and the electric detection antenna, and has the advantages of large whole related range, simple structure, low cost, convenient mass production, convenient disassembly and assembly, stable and reliable structure, adaptability to complex environments such as high and low temperature and space saving.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a micro-nano satellite unfolding mechanism.
Background
With the development of microsatellite and aerospace technology, the microsatellite is widely applied to various directions such as communication, remote sensing, scientific research and the like due to the advantages of low cost, multiple satellites per arrow, rapid launching and the like. In order to facilitate the realization of rapid concentrated emission, a constellation network is formed in the space networking, and microsatellites have strict requirements on the size and weight of the satellites.
The satellite envelope is increased by directly expanding the solar wings and the antenna out of the satellite, so that the launching cost is increased, the structure needing to be expanded out of the satellite is folded and fixed before the satellite enters the orbit, and the satellite-entering satellite arrow is unlocked and expanded after the satellite-entering satellite arrow is separated. The existing satellite unfolding mechanism is complex in structure, high in manufacturing cost and complex in operation. Therefore, how to provide a micro-nano satellite unfolding mechanism and a unfolding method related to a micro-satellite solar wing, a data transmission antenna and an electric detection antenna, which have the advantages of simple structure, low cost, convenient mass production and convenient operation, are one of the technical problems to be solved in the field.
Disclosure of Invention
In view of the above, the present invention provides a micro-nano satellite unfolding mechanism, which aims to solve the problems in the prior art.
In order to solve the technical problems, the invention adopts the following technical scheme:
A micro-nano satellite deployment mechanism comprising:
A satellite body;
A solar wing assembly; the solar wing component comprises a sailboard swinging mechanism, a solar sailboard and a sailboard 180-degree unfolding mechanism; the sailboard swinging mechanism is arranged on the satellite main body; the solar sailboard swinging mechanism is sequentially connected with a plurality of solar sailboards; the adjacent solar sailboards are connected through a 180-degree unfolding mechanism of the sailboards;
A data transmission antenna assembly; the data transmission antenna assembly comprises a data transmission 90-degree unfolding mechanism, a first data transmission connecting rod, a second data transmission connecting rod, a data transmission 180-degree unfolding mechanism, a data transmission base bracket and a data transmission driving mechanism; the data transmission 90-degree unfolding mechanism is arranged on the satellite main body; one end of the first data transmission connecting rod is connected with the data transmission 90-degree unfolding mechanism, and the other end of the first data transmission connecting rod is connected with the second data transmission connecting rod through the data transmission 180-degree unfolding mechanism; the data transmission base support is arranged at the other end of the second data transmission connecting rod; the data transmission driving mechanism is arranged on the data transmission base bracket;
An electrical detection antenna assembly; the electric detection antenna assembly comprises an electric detection antenna support, an electric detection 90-degree unfolding mechanism, an electric detection connecting rod, an electric detection antenna base and an electric detection antenna; the electric detection antenna support is arranged on the satellite main body; one end of the electric detection connecting rod is connected with the electric detection antenna support through the electric detection 90-degree unfolding mechanism, and the other end of the electric detection connecting rod is connected with the electric detection antenna base; the electric detection antenna is arranged on the electric detection antenna base;
A first rope stopper; the solar sailboard, the data transmission base support and the electric detection connecting rod are provided with the first rope limiting part;
a first binding rope; the first binding rope is wound on the outer side of the satellite main body through the first rope limiting piece, and the solar wing assembly, the data transmission antenna assembly and the electric detection antenna assembly are kept in a folded state;
A first cut-off mechanism; the first cutting mechanism is arranged on the satellite main body, and the first cutting mechanism is arranged corresponding to the first binding rope.
Preferably, the solar wing assembly further comprises a windsurfing board limiting assembly for supporting and limiting the solar windsurfing board.
Preferably, the sailboard limiting assembly comprises a sailboard supporting seat and a sailboard limiting piece; the sailboard supporting seat is arranged on the satellite main body; the sailboard limiting piece is arranged on the innermost solar sailboard; the sailboard limiting piece is provided with a sailboard slot; and the sailboard supporting seat is provided with a sailboard inserting block matched with the sailboard inserting groove.
Preferably, a second rope limiting part is arranged on the outermost solar sailboard; the innermost solar sailboard is provided with a second cutting mechanism; and a second binding rope is wound between the second rope limiting piece and the second cutting mechanism, so that the solar wing component is kept in a folded state.
Preferably, the data transmission antenna assembly further comprises a data transmission limiting assembly for supporting and limiting the data transmission antenna assembly.
Preferably, the data transmission limiting assembly comprises a data transmission supporting seat and a data transmission limiting piece; the data transmission supporting seat is arranged on the satellite main body; the data transmission limiting piece is arranged on the first data transmission connecting rod; the data transmission limiting piece is provided with a data transmission slot; and the data transmission supporting seat is provided with a data transmission plug block matched with the data transmission slot.
Preferably, the electric detection antenna assembly further comprises an electric detection limit assembly for supporting and limiting the electric detection antenna assembly.
Preferably, the electric detection limiting assembly comprises an electric detection supporting seat and an electric detection limiting piece; the electric detection supporting seat is arranged on the satellite main body and/or the solar wing component; the electric detection limiting piece is arranged on the electric detection connecting rod; the electric detection limiting piece is provided with an electric detection slot; the electric detection supporting seat is provided with an electric detection plug block matched with the electric detection slot.
Preferably, the number of the electric detection antenna components is seven; the solar wing assembly, the data transmission antenna assembly and the rest of the electric detection antenna assemblies are limited by a fourth binding rope; the satellite main body is provided with a third cutting mechanism corresponding to the third binding rope and a fourth cutting mechanism corresponding to the fourth binding rope.
Preferably, the 180-degree unfolding mechanism of the sailboard, the 90-degree unfolding mechanism of the data transmission and the 180-degree unfolding mechanism of the data transmission are all provided with locking mechanisms.
Compared with the prior art, the invention has the following technical effects: the invention can realize the rapid folding and unfolding of the solar wing, the data transmission antenna and the electric detection antenna, and has the advantages of large whole related range, simple structure, low cost, convenient mass production, convenient disassembly and assembly, stable and reliable structure, adaptability to complex environments such as high and low temperature and space saving.
Drawings
FIG. 1 is a schematic view of a micro-nano satellite deployment mechanism according to the present invention at a viewing angle prior to deployment;
FIG. 2 is a schematic view of a micro-nano satellite deployment mechanism according to the present invention at another viewing angle prior to deployment;
FIGS. 3a, 3b, 3c, and 3d are schematic views illustrating the unfolding process according to the present invention;
FIG. 4 is a schematic view of a solar wing assembly prior to deployment;
FIG. 5 is a schematic illustration of a solar module during deployment;
FIG. 6 is a schematic view of the solar wing assembly after deployment;
FIG. 7 is a schematic diagram of a data transmission antenna assembly before deployment;
FIG. 8 is a schematic diagram of a data transmission antenna assembly during deployment;
FIG. 9 is a schematic diagram of the data transmission antenna assembly after being unfolded;
FIG. 10 is a schematic diagram of an electrical detection antenna assembly disposed corresponding to a solar wing assembly prior to deployment;
FIG. 11 is a schematic view of an electrical detection antenna assembly disposed corresponding to a solar wing assembly during deployment;
FIG. 12 is a schematic view of an electrical detection antenna assembly disposed corresponding to a solar wing assembly after deployment;
FIG. 13 is a schematic diagram of one of the electrical detecting antenna elements on the same side as the data transmission antenna element before deployment;
FIG. 14 is a schematic diagram of one of the electrical detecting antenna elements on the same side as the data transmission antenna element during deployment;
FIG. 15 is a schematic diagram of an unfolded one of the electrical detection antenna assemblies located on the same side as the data transmission antenna assembly;
FIG. 16 is a schematic view of the positions of the first, third and fourth cutoff mechanisms;
FIG. 17 is a schematic view of the position of the second severing mechanism;
FIG. 18 is a schematic diagram of the electrical detection 90 degree deployment mechanism before and after deployment;
FIG. 19 is a schematic view of the data transmission 90 degree deployment mechanism before and after deployment;
FIG. 20 is a schematic view of a windsurfing board 180 degree deployment mechanism before and after deployment;
FIG. 21 is a schematic view of an electrical detection support and an electrical detection limiter according to one specification;
In the figure: 1. a satellite body; 2. a solar wing assembly; 201. a sailboard swinging mechanism; 202. a solar sailboard; 203. a sailboard 180-degree unfolding mechanism; 204. a sailboard supporting seat; 205. a second rope stopper; 206. a second cutting mechanism; 3. a data transmission antenna assembly; 301. a data transmission 90-degree unfolding mechanism; 302. a first data transmission link; 303. a second data transmission link; 304. a data transmission 180-degree unfolding mechanism; 305. a data transmission base bracket; 306. a data transmission driving mechanism; 307. a data transmission supporting seat; 308. a data transmission limiting piece; 309. a heat insulating mat; 4. an electrical detection antenna assembly; 401. an electric detection antenna support; 402. electrically detecting a 90-degree unfolding mechanism; 4021. a first fixed joint; 4022. a second fixed joint; 4023. a first movable joint; 4024. a second movable joint; 403. an electrical detection link; 404. an electric detecting antenna base; 405. an electric detection supporting seat; 406. an electrical detection limit piece; 407. an electrical detection antenna; 5. a first rope stopper; 6. a first binding rope; 7. a first cut-off mechanism; 8. a second binding rope; 9. a third binding rope; 10. a fourth binding rope; 11. a third cutting mechanism; 12. a fourth cutting mechanism; 13. a fourth rope stopper; 14. a stop block; 15. a locking shaft; 16. a locking groove; 17. and a wire clamping seat.
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.
Referring to fig. 1-21, the present invention provides a micro-nano satellite deployment mechanism, comprising:
a satellite main body 1;
A solar wing assembly 2; the solar wing assembly 2 comprises a windsurfing board swinging mechanism 201, a solar windsurfing board 202 and a windsurfing board 180 degree unfolding mechanism 203; the sailboard swinging mechanism 201 is arranged on the cabin board at the left side of the satellite main body 1 and is used for controlling the solar sailboard 202 connected with the sailboard swinging mechanism 201 to rotate; three solar sailboards 202 are sequentially connected to the sailboard swinging mechanism 201 from inside to outside and are used for providing energy for satellites; the innermost solar sailboard 202 is connected with the sailboard swinging mechanism 201 through a sailboard connecting rod; the adjacent solar sailboards 202 are connected through two sailboard 180-degree unfolding mechanisms 203, so that the solar sailboards 202 can be folded together and can be unfolded in a 180-degree rotation mode;
A data transmission antenna assembly 3; the data transmission antenna assembly 3 comprises a data transmission 90-degree unfolding mechanism 301, a first data transmission connecting rod 302, a second data transmission connecting rod 303, a data transmission 180-degree unfolding mechanism 304, a data transmission base support 305 and a data transmission driving mechanism 306; the data transmission 90-degree unfolding mechanism 301 is arranged on a cabin board on the right side of the satellite main body 1 and is used for controlling the data transmission connecting rod to rotate 90 degrees; one end of a first data transmission connecting rod 302 is connected with a data transmission 90-degree unfolding mechanism 301 through a first data transmission connecting rod fixing piece, the other end of the first data transmission connecting rod 302 is connected with a second data transmission connecting rod 303 through a data transmission 180-degree unfolding mechanism 304, and the second data transmission connecting rod 303 can be unfolded in a 90-degree rotation mode relative to the first data transmission connecting rod 302 through the arrangement of the data transmission 180-degree unfolding mechanism 304; the data transmission base support 305 is arranged at the other end of the second data transmission connecting rod 303; the data transmission driving mechanism 306 is arranged on the data transmission base support 305, and can realize further expansion of the data transmission antenna after the data transmission antenna assembly 3 is expanded; the extra-satellite distance of the data transmission antenna can be prolonged by arranging the first data transmission connecting rod 302 and the second data transmission connecting rod 303;
an electrical detection antenna assembly 4; the electric detection antenna assembly 4 comprises an electric detection antenna support 401, an electric detection 90-degree unfolding mechanism 402, an electric detection connecting rod 403, an electric detection antenna base 404 and an electric detection antenna 407; the electric detection antenna support 401 is arranged on a cabin board at the top of the satellite main body 1, and the whole electric detection antenna assembly 4 is fixed on the satellite main body 1; one end of the electric detection connecting rod 403 is connected with the electric detection antenna support 401 through the electric detection 90-degree unfolding mechanism 402, and the other end of the electric detection connecting rod 403 is connected with the electric detection antenna base 404; the electric detection antenna 407 is disposed on the electric detection antenna base 404; the electrical detection antenna assembly 4 can be deployed 90 degrees out of the satellite by the electrical detection 90 degree deployment mechanism 402.
A first rope stopper 5; the outermost solar sailboard 202, the data transmission base support 305 and the electric detection connecting rod 403 are all provided with a first rope limiting piece 5; each first rope limiting piece 5 is provided with a first rope limiting groove;
A first binding rope 6; the first binding rope 6 is wound on the outer side of the satellite main body 1 through a first rope limiting groove on the first rope limiting piece 5 to fixedly limit the solar wing assembly 2, the data transmission antenna assembly 3 and the electric detection antenna assembly 4, so that the solar wing assembly 2, the data transmission antenna assembly 3 and the electric detection antenna assembly 4 are kept in a folded state;
A first cutting mechanism 7; the first cutting mechanism 7 is arranged on the cabin board of the satellite main body 1, and the first cutting mechanism 7 is arranged corresponding to the first binding rope 6 and is used for cutting the first binding rope 6; the solar wing component 2, the data transmission antenna component 3 and the electric detection antenna component 4 in the unfolding mechanism are folded and unfolded through the matching of the first cutting mechanism 7 and the first binding rope 6.
In this embodiment, the solar wing assembly 2 further includes a sailboard limiting assembly for supporting and limiting the solar sailboard 202, which not only can support the solar wing assembly 2 to keep the solar wing assembly 2 at a certain distance from the satellite main body 1, so as to avoid collision, but also can limit the degrees of freedom of the solar wing assembly 2 in the directions other than the direction of deployment outside the satellite, so as to resist the load in the direction of mechanical vibration.
In this embodiment, the windsurfing board limiting component includes a windsurfing board supporting seat 204 and a windsurfing board limiting piece; the sailboard support seat 204 is arranged on the satellite main body 1; the sailboard limiting piece is arranged on the innermost solar sailboard 202; the sailboard limiting piece is provided with a sailboard slot; the sailboard support seat 204 is provided with a sailboard plug matched with the sailboard slot; when the solar wing assembly 2 is in a folded state, the sailboard plug is inserted into the sailboard slot, so that the purposes of supporting and limiting the solar wing assembly 2 are achieved, and when the solar wing assembly 2 is to be unfolded, the sailboard plug is separated from the sailboard slot, so that the unfolding operation is not influenced.
In this embodiment, a solar panel support base 204 and a solar panel limiting member, which are mutually matched, are also disposed between adjacent solar panels 202, so as to support and limit the solar panels 202.
In this embodiment, the outermost solar sailboard 202 is provided with a second rope limiter 205; the second rope limiting piece 205 is in a hook-shaped structure and is used for hooking the second binding rope 8 to play a limiting role; the innermost solar sailboard 202 is provided with a second cutting mechanism 206; the second rope limiting piece 205 and the second cutting mechanism 206 are wound with the second binding rope 8, and the three solar sailboards 202 in the solar wing assembly 2 are kept in a folded state, wherein the second rope limiting piece 205 limits the second binding rope 8 through the second rope limiting piece 205, and the second rope limiting piece 205 and the second cutting mechanism 206 are matched, so that the solar sailboards 202 are folded and unfolded.
In this embodiment, the data antenna assembly 3 further includes a data limiting assembly for supporting and limiting the data antenna assembly 3, which not only can support the data antenna assembly 3 to keep a certain distance between the data antenna assembly 3 and the satellite main body 1 to avoid collision, but also limits the degrees of freedom of the data antenna assembly 3 in all directions except the direction of spreading out of the satellite, i.e. the data antenna assembly 3 cannot translate or rotate on a plane consistent with the distance between the upper cabin plates of the satellite main body 1 to resist loads in the direction of mechanical vibration.
In this embodiment, the data transmission limiting assembly includes a data transmission supporting seat 307 and a data transmission limiting member 308; the data transmission support 307 is disposed on the satellite main body 1; the data transmission limiting piece 308 is disposed on the first data transmission connecting rod 302; the data transmission limiting piece 308 is provided with a data transmission slot; the data transmission support seat 307 is provided with a data transmission plug matched with the data transmission slot; when the data transmission antenna assembly 3 is in a folded state, the data transmission plug is inserted into the data transmission slot, the purpose of supporting and limiting the data transmission antenna assembly 3 is achieved, and when the data transmission antenna assembly 3 is to be unfolded, the data transmission plug is separated from the data transmission slot, so that the unfolding operation is not affected.
In this embodiment, one end of the data transmission 180-degree expansion mechanism 304 is connected to the first data transmission link 302 through a first data transmission link fixing member, and the other end of the data transmission 180-degree expansion mechanism 304 is connected to the second data transmission link 303 through a second data transmission link fixing member.
In this embodiment, a heat insulation pad 309 is disposed between the first rope limiting member 5 and the data base support 305 on the data antenna assembly 3 for heat insulation.
In this embodiment, the electric detection antenna assembly 4 further includes an electric detection limit assembly for supporting and limiting the electric detection antenna assembly 4, which not only can support the electric detection antenna assembly 4 to keep a certain distance between the electric detection antenna assembly 4 and the satellite main body 1, so as to avoid collision, but also limit the degrees of freedom of the electric detection antenna assembly 4 in all directions except the direction of spreading out the satellite, i.e. the electric detection antenna assembly 4 cannot translate or rotate on a plane consistent with the distance between the cabin plates on the satellite main body 1, so as to resist the load in the direction of mechanical vibration.
In this embodiment, the electrical detection link 403 is connected to the electrical detection 90 degree deployment mechanism 402 by an electrical detection link connector.
In this embodiment, the electrical detection limiting component includes an electrical detection supporting seat 405 and an electrical detection limiting member 406; the electric detection support seat 405 is disposed on the satellite body 1 and/or the solar wing assembly 2; the electrical detection limiting piece 406 is arranged on the electrical detection connecting rod 403; the electric detection limiting piece 406 is provided with an electric detection slot; the electric detection supporting seat 405 is provided with an electric detection plug matched with the electric detection slot; when the electric detection antenna assembly 4 is in a folded state, the electric detection plug is inserted into the electric detection slot, the purpose of supporting and limiting the electric detection antenna assembly 4 is achieved, and when the electric detection antenna assembly 4 needs to be unfolded, the electric detection plug is separated from the electric detection slot, so that the unfolding operation is not influenced.
In the present embodiment, the number of the electrical detecting antenna assemblies 4 is seven; one electric detection antenna assembly 4 of the seven electric detection antenna assemblies 4 is arranged on the left side of the satellite main body 1 in a folding way, the electric detection antenna assembly 4 is arranged corresponding to the middle position of the solar wing assembly 2, the remaining six electric detection antenna assemblies 4 are divided into three groups, each group comprises two electric detection antenna assemblies 4, and the three groups of electric detection antenna assemblies 4 are respectively arranged on the front side, the rear side and the right side of the satellite main body 1 in a folding way; wherein, two electric detection antenna assemblies 4 which are positioned on the same side with the data transmission antenna assembly 3 are limited by a third binding rope 9, and the solar wing assembly 2, the data transmission antenna assembly 3 and the rest electric detection antenna assemblies 4 are limited by a fourth binding rope 10; the satellite body 1 is provided with a third cutting mechanism 11 corresponding to the third binding string 9 and a fourth cutting mechanism 12 corresponding to the fourth binding string 10.
In the present embodiment, the electric detection support seat 405 corresponding to the electric detection antenna assembly 4 corresponding to the solar wing assembly 2 is disposed on the outermost solar sailboard 202; the rest of the electric detection supporting bases 405 of the electric detection antenna assembly 4 are all disposed on the satellite body 1.
In this embodiment, the outermost solar sailboard 202 and the data transmission driving mechanism 306 are provided with a fourth rope limiting member 13; the fourth rope limiting piece 13 and the electric detection limiting piece 406 in the electric detection antenna assembly 4 which is not positioned on the same side with the data transmission antenna assembly 3 are respectively provided with a fourth rope limiting groove for limiting the fourth binding rope 10; the fourth binding rope 10 is wound around the satellite main body 1 for one circle to fold the solar wing component 2, the data transmission antenna component 3 and the five electric detection antenna components which are not positioned on the same side with the data transmission antenna component 3, and the fourth binding rope 10 is limited by a fourth rope limiting groove on the fourth rope limiting piece 13.
In this embodiment, the fourth rope limiting members 13 with multiple specifications are configured, and according to different installation positions of the fourth rope limiting members 13, the fourth rope limiting members 13 with proper specifications are selected, and meanwhile, the fourth rope limiting grooves on the fourth rope limiting members 13 with different specifications are matched with the corresponding fourth rope limiting members 13.
In the present embodiment, the number of the fourth rope stoppers 13 on the data transmission driving mechanism 306 is two.
In this embodiment, the electrical detection limiting members 406 with multiple specifications are configured, and the electrical detection limiting members 406 with proper specifications are selected according to different installation positions of the electrical detection limiting members 406.
In this embodiment, the electrical detection support bases 405 with various specifications are configured, and the electrical detection support bases 405 with appropriate specifications are selected according to different installation positions of the electrical detection support bases 405.
In the present embodiment, the number of the third binding-cord 9 and the third cutoff mechanism 11 is two; the two third binding ropes 9 and the two third cutting mechanisms 11 are arranged in a one-to-one correspondence; the two third binding ropes 9 and the two cutting structures are matched to limit the two electric detection antenna assemblies 4 which are positioned on the same side with the data transmission antenna assembly 3, so that the folding and unfolding functions are realized.
In this embodiment, the electrical detection limiting members 406 on the two electrical detection antenna assemblies 4 located on the same side as the data transmission antenna assembly 3 are respectively provided with a third rope limiting groove for limiting the third binding rope 9.
In this embodiment, each electrical detection limiting member 406 corresponding to the third rope limiting groove is provided with a wire clamping seat 17; each wire clamping seat 17 is positioned above the corresponding third rope limiting groove and plays a further limiting role on the third binding rope 9.
In this embodiment, the first rope limiting members 5 with multiple specifications are configured, and according to different installation positions of the first rope limiting members 5, the first rope limiting members 5 with appropriate specifications are selected, and meanwhile, the first rope limiting grooves on the first rope limiting members 5 with different specifications are matched with the corresponding first rope limiting members 5.
In this embodiment, the electrical detection 90 degree deployment mechanism 402 includes a first fixed joint 4021, a second fixed joint 4022, a first movable joint 4023 and a second movable joint 4024; the first fixed joint 4021 is fixedly connected to the electric detection antenna support 401; the second stationary joint 4022 is rotatably coupled to the first stationary joint 4021; one end of the first movable joint 4023 is rotatably connected to the first fixed joint 4021; the other end of the first movable joint 4023 is rotatably connected to one end of a second movable joint 4024; the other end of the second movable joint 4024 is rotatably connected to a second fixed joint 4022.
In this embodiment, the sailboard 180-degree deployment mechanism 203, the data transmission 90-degree deployment mechanism 301 and the data transmission 180-degree deployment mechanism 304 all include a driving seat and a driven seat; the driven seat is rotatably connected with the driving seat.
In this embodiment, the driven seat and the driving seat with different specifications are configured, and the driven seat and the driving seat with appropriate specifications are selected to be mounted at corresponding positions according to different mounting positions of the driven seat and the driving seat.
In this embodiment, the windsurfing 180 degree unfolding mechanism 203, the data transmission 90 degree unfolding mechanism 301 and the data transmission 180 degree unfolding mechanism 304 are all provided with locking mechanisms.
In the present embodiment, the locking mechanism includes a stopper 14 and a locking shaft 15; the stop block 14 is rotatably connected to the driven seat; a torsion spring is arranged between the stop block 14 and the driven seat; the locking shaft 15 is arranged on one side of the stop block 14 far away from the driven seat; the driving seat is provided with a locking groove 16 which is matched with the locking shaft 15.
In this embodiment, the electrical detection antenna holders 401 with different specifications are configured, and the electrical detection antenna holders 401 with suitable specifications can be selected according to the installation positions of the electrical detection antenna assembly 4, so as to meet the use requirements.
In the present embodiment, the electric detection 90 degree deployment mechanism 402 provides the deployment driving force through a torsion spring; the data transmission 90-degree deployment mechanism 301, the data transmission 180-degree deployment mechanism 304, and the windsurfing 180-degree deployment mechanism 203 provide deployment driving force through the spiral springs.
In the present embodiment, the first cutting mechanism 7, the second cutting mechanism 206, the third cutting mechanism 11, and the fourth cutting mechanism 12 are all electric knives; the electric heating knife is of a double-head structure, and is convenient for limiting the corresponding binding rope.
In this embodiment, in order to ensure satellite functions and facilitate installation and manufacture, the numbers of the electric detection supporting seat 405, the electric detection antenna support 401, the electric detection connecting rod 403, the electric detection limiting piece 406 and the electric detection antenna base 404 in each electric detection antenna assembly 4 are all in one-to-one correspondence with the installation positions.
The folding and unfolding method of the micro-nano satellite unfolding mechanism comprises the following steps:
The folding method comprises the following steps: 1) Assembling the solar wing assembly 2, the electric detection antenna assembly 4 and the data transmission antenna assembly 3, and completing the installation of the electric detection support seat 405, the data transmission support seat 307, the sailboard support seat 204 and all the cut-off structures; 2) Mounting the solar wing assembly 2, the electric detecting antenna assembly 4 and the data transmission antenna assembly 3 at a design position on the satellite main body 1; 3) The solar sailboard 202 is folded, and the solar wing assembly 2 is fixed through the second binding rope 8, so that the solar wing assembly 2 is in a folded state; 4) The electric detection antenna assembly 4 positioned on the same side as the data transmission antenna assembly 3 is folded and fixed through a third binding rope 9, so that the electric detection antenna assembly 4 positioned on the same side as the data transmission antenna assembly 3 is in a folded state; 5) The rest electric detection antenna components and the data transmission antenna components 3 are folded and fixed through the first binding rope 6 and the fourth binding rope 10, so that all the solar wing components 2, the electric detection antenna components 4 and the data transmission antenna components 3 are in a folding state.
The unfolding method comprises the following steps: 1) The first cutting mechanism 7 and the fourth cutting mechanism 12 start to work, the first binding rope 6 and the second binding rope 8 are cut off, the data transmission antenna assembly 3 and the electric detection antenna assembly 4 which is not positioned on the same side with the data transmission antenna assembly 3 start to be unfolded, wherein the second fixed joint 4022 in the electric detection 90-degree unfolding mechanism 402 which is not positioned on the same side with the data transmission antenna assembly 3 rotates outside the star and drives the first movable joint 4023 and the second movable joint 4024 to move at the same time, when the first movable joint 4023 and the second movable joint 4024 rotate outwards to 90 degrees, the driven seat in the data transmission 90-degree unfolding mechanism 301 can not rotate further relatively to the front of the driving seat, and simultaneously, the locking shaft 15 just rotates into the locking groove 16 on the driving seat and is locked, so that the driven seat in the data transmission 90-degree unfolding mechanism 301 just rotates outwards by 90 degrees relative to the driving seat and drives the first movable joint 4023 and the second movable joint 4024 to move outwards, and the driven seat in the same direction rotates by 180 degrees relative to the driving seat, and the driven seat in the same direction is locked, and the driven seat in the end is just rotated by 180 degrees relative to the driving seat, and the driven seat in the driving seat is just rotates by 180 degrees, and the driven seat in the same direction is extended, and the driven seat in the end is locked by 180 degrees, the driven seat is just rotates outwards by 180 degrees, and the driven seat is rotated by the locking seat in the driving seat, and is rotated by 90 degrees;
2) The third cutting mechanism 11 starts to work, cuts off the third binding rope 9, starts to spread the electric detection antenna assembly 4 positioned on the same side with the data transmission antenna assembly 3, and the specific spreading process is consistent with the spreading process of the electric detection antenna assembly 4 which is not positioned on the same side with the data transmission antenna assembly 3 in the step 1), and the electric detection antenna assembly 4 positioned on the same side with the data transmission antenna assembly 3 rotates outwards for 90 to be parallel to the installation cabin board and locks, so that all the electric detection antenna assemblies 4 are completely spread;
3) The sailboard swinging mechanism 201 controls the sailboard connecting rod to rotate 90 degrees, then the second cutting mechanism 206 starts to work, the second binding rope 8 for fixing the solar sailboard 202 is cut off, under the action of the sailboard swinging mechanism 201 and the sailboard 180-degree unfolding mechanism 203, the solar wing assembly 2 is unfolded, in the process, the sailboard swinging mechanism 201 rotates 90 degrees, the solar sailboard 202 on the outer side in the two adjacent solar sailboards 202 rotates 180 degrees relative to the solar sailboard 202 on the inner side, and finally the data transmission driving mechanism 306 controls the data transmission antenna to be unfolded finally after the data transmission antenna assembly 3 is unfolded, so that the step-by-step unfolding of the satellite unfolding mechanism is completed.
The foregoing description is only of the preferred embodiments of the present invention and is not intended to limit the technical scope of the present invention, so that any minor modifications, equivalent changes and modifications made to the above embodiments according to the technical principles of the present invention still fall within the scope of the technical solutions of the present invention.
Claims (10)
1. A micro-nano satellite deployment mechanism, comprising:
a satellite main body (1);
A solar wing assembly (2); the solar wing assembly (2) comprises a sailboard swinging mechanism (201), a solar sailboard (202) and a sailboard 180-degree unfolding mechanism (203); the sailboard swinging mechanism (201) is arranged on the satellite main body (1); the solar sailboard swinging mechanism (201) is sequentially connected with a plurality of solar sailboards (202); adjacent solar sailboards (202) are connected through a 180-degree unfolding mechanism (203) of the sailboards;
A data transmission antenna assembly (3); the data transmission antenna assembly (3) comprises a data transmission 90-degree unfolding mechanism (301), a first data transmission connecting rod (302), a second data transmission connecting rod (303), a data transmission 180-degree unfolding mechanism (304), a data transmission base support (305) and a data transmission driving mechanism (306); the data transmission 90-degree unfolding mechanism (301) is arranged on the satellite main body (1); one end of the first data transmission connecting rod (302) is connected with a data transmission 90-degree unfolding mechanism (301), and the other end of the first data transmission connecting rod (302) is connected with the second data transmission connecting rod (303) through the data transmission 180-degree unfolding mechanism (304); the data transmission base support (305) is arranged at the other end of the second data transmission connecting rod (303); the data transmission driving mechanism (306) is arranged on the data transmission base bracket (305);
An electrical detection antenna (407) assembly (4); the electric detection antenna (407) component (4) comprises an electric detection antenna (407) support (401), an electric detection 90-degree unfolding mechanism (402), an electric detection connecting rod (403), an electric detection antenna (407) base (404) and an electric detection antenna (407); the electric detection antenna (407) support (401) is arranged on the satellite main body (1); one end of the electric detection connecting rod (403) is connected with the electric detection antenna (407) support (401) through the electric detection 90-degree unfolding mechanism (402), and the other end of the electric detection connecting rod (403) is connected with the electric detection antenna (407) base (404); the electric detection antenna (407) is arranged on the base (404) of the electric detection antenna (407);
A first rope stopper (5); the solar sailboard (202), the data transmission base support (305) and the electric detection connecting rod (403) are provided with the first rope limiting piece (5);
A first binding rope (6); the first rope binding piece (6) is wound on the outer side of the satellite main body (1) through the first rope limiting piece (5) and enables the solar wing assembly (2), the data transmission antenna assembly (3) and the electric detection antenna (407) assembly (4) to be kept in a folded state;
A first cutting mechanism (7); the first cutting mechanism (7) is arranged on the satellite main body (1), and the first cutting mechanism (7) is arranged corresponding to the first binding rope (6).
2. A micro-nano satellite deployment mechanism according to claim 1, wherein the solar wing assembly (2) further comprises a windsurfing board limiting assembly for supporting and limiting the solar windsurfing board (202).
3. A micro-nano satellite deployment mechanism according to claim 2, wherein the sailboard limiting assembly comprises a sailboard support (204) and a sailboard limiting member; the sailboard supporting seat (204) is arranged on the satellite main body (1); the sailboard limiting piece is arranged on the innermost solar sailboard (202); the sailboard limiting piece is provided with a sailboard slot; and a sailboard insert block matched with the sailboard slot is arranged on the sailboard supporting seat (204).
4. A micro-nano satellite deployment mechanism according to claim 3, wherein the outermost solar sailboard (202) is provided with a second rope limiting element (205); a second cutting mechanism (206) is arranged on the innermost solar sailboard (202); a second binding rope (8) is wound between the second rope limiting piece (205) and the second cutting mechanism (206) and enables the solar wing assembly (2) to keep a folded state.
5. A micro-nano satellite deployment mechanism according to claim 1, wherein the data transmission antenna assembly (3) further comprises a data transmission limiting assembly for supporting and limiting the data transmission antenna assembly (3).
6. The micro-nano satellite deployment mechanism according to claim 5, wherein the data transmission limiting assembly comprises a data transmission supporting seat (307) and a data transmission limiting piece (308); the data transmission supporting seat (307) is arranged on the satellite main body (1); the data transmission limiting piece (308) is arranged on the first data transmission connecting rod (302); the data transmission limiting piece (308) is provided with a data transmission slot; the data transmission supporting seat (307) is provided with a data transmission plug block matched with the data transmission slot.
7. The micro-nano satellite deployment mechanism according to claim 1, wherein the electrical detection antenna (407) assembly (4) further comprises an electrical detection limit assembly for supporting and limiting the electrical detection antenna (407) assembly (4).
8. The micro-nano satellite deployment mechanism according to claim 7, wherein the electrical detection limit assembly comprises an electrical detection support (405) and an electrical detection limit (406); the electric detection supporting seat (405) is arranged on the satellite main body (1) and/or the solar wing component (2); the electric detection limiting piece (406) is arranged on the electric detection connecting rod (403); the electric detection limiting piece (406) is provided with an electric detection slot; the electric detection supporting seat (405) is provided with an electric detection plug block matched with the electric detection slot.
9. The micro-nano satellite deployment mechanism according to claim 1, wherein the number of the electric detection antenna (407) components (4) is seven; the electric detection antenna (407) component (4) positioned on the same side with the data transmission antenna component (3) is limited through a third binding rope (9), and the solar wing component (2), the data transmission antenna component (3) and the rest electric detection antenna (407) components (4) are limited through a fourth binding rope (10); the satellite main body (1) is provided with a third cutting mechanism (11) corresponding to the third binding rope (9) and a fourth cutting mechanism (12) corresponding to the fourth binding rope (10).
10. The micro-nano satellite unfolding mechanism according to claim 1, wherein a locking mechanism is arranged on each of the sailboard 180-degree unfolding mechanism (203), the data transmission 90-degree unfolding mechanism (301) and the data transmission 180-degree unfolding mechanism (304).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410319995.1A CN117963172A (en) | 2024-03-20 | 2024-03-20 | Micro-nano satellite unfolding mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410319995.1A CN117963172A (en) | 2024-03-20 | 2024-03-20 | Micro-nano satellite unfolding mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117963172A true CN117963172A (en) | 2024-05-03 |
Family
ID=90856599
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410319995.1A Pending CN117963172A (en) | 2024-03-20 | 2024-03-20 | Micro-nano satellite unfolding mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117963172A (en) |
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2024
- 2024-03-20 CN CN202410319995.1A patent/CN117963172A/en active Pending
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