CN113619812A - Standard modular microsatellite system - Google Patents
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- CN113619812A CN113619812A CN202111063283.0A CN202111063283A CN113619812A CN 113619812 A CN113619812 A CN 113619812A CN 202111063283 A CN202111063283 A CN 202111063283A CN 113619812 A CN113619812 A CN 113619812A
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- 108091092878 Microsatellite Proteins 0.000 title claims abstract description 27
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 34
- 238000005259 measurement Methods 0.000 claims description 21
- 238000000926 separation method Methods 0.000 claims description 8
- 230000002787 reinforcement Effects 0.000 claims description 6
- 238000013461 design Methods 0.000 description 11
- 238000011161 development Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 238000004519 manufacturing process Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000009434 installation Methods 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000009776 industrial production Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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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
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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
- B64G1/223—Modular spacecraft systems
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Abstract
The invention discloses a standard modular microsatellite system, relates to a modular satellite architecture, aims to overcome the problems of insufficient expansibility and insufficient universality of the conventional satellite architecture, and comprises the following steps: the connector is fixed on the outer side wall of the drawer type structure unit; the mechanical interfaces are distributed and fixed on the outer side wall of the drawer type structure unit; a plurality of drawer type structure units in each group of splicing units are longitudinally stacked; the adjacent two layers of drawer type structure units are connected through corresponding mechanical interfaces; the adjacent two layers of drawer type structure units are electrically connected through corresponding connectors; the boss step seam allowance of the upper drawer type structure unit is embedded into the concave step seam allowance of the lower drawer type structure unit; the switching unit comprises a plurality of reinforcing laminates, and the tops and the bottoms of all the splicing units are respectively covered and fixed with one reinforcing laminate; the plug-in unit comprises at least one load; the load is fixed above the splicing unit through a reinforcing laminate positioned at the top of the splicing unit.
Description
Technical Field
The invention relates to a modular satellite architecture.
Background
In recent years, due to the advantages of light weight, small volume, short emission period, high performance, low cost and the like, microsatellites have attracted attention in various fields such as communication, remote sensing, scientific research, military and the like. The microsatellite has short production period and lower cost, can meet the special requirements of rapid development and emergency launching, and is paid attention by a plurality of aerospace major countries such as the United states, Russia and the like.
The traditional design method of the satellite architecture is to carry out customized design on a branch system according to specific tasks, so that the designed satellite systems are different, the interfaces are various in form, the quality is high, and the cost is high. The design method of the public platform has certain universality, however, as the application market of the satellite is increasingly prosperous, the types and the number of the satellites are continuously increased, and the requirements of users on the research and development period and the cost of the satellite are increasingly strict. It can be seen that the two design methods at present are difficult to achieve the development goals of high performance, short cycle and low cost of the microsatellite.
The design of the existing modularized satellite architecture, for example, patent No. 201810130591.2, discloses a modularized satellite architecture, which does not propose specific function application, and has insufficient expansibility and insufficient universality.
Patent No. 201580068138.8 discloses a modular architecture optimized to make microsatellites, the modules being square, stacked one above the other, and having insufficient expandability and versatility.
Disclosure of Invention
The invention aims to overcome the problems of insufficient expansibility and insufficient universality of the conventional satellite architecture and provides a standard modular microsatellite system.
The invention discloses a standard modular microsatellite system, which comprises a plurality of drawer type structure units, a standard connecting structure, a switching unit and an external hanging unit;
the specifications of the drawer-type structure units are the same, and each drawer-type structure unit is provided with a corresponding functional unit;
the standard connecting structure comprises a connector, a mechanical interface and a step type spigot;
the socket connector is fixed on the outer side wall of the drawer type structure unit and is electrically connected with the corresponding functional unit inside the drawer type structure unit;
the number of the mechanical interfaces is multiple, and the mechanical interfaces are distributed and fixed on the outer side wall of the drawer type structure unit;
the stepped spigot comprises a concave stepped spigot and a convex stepped spigot which are matched with each other;
the concave step seam allowance is arranged on the upper surface of the drawer type structure unit side plate, and the convex step seam allowance is arranged on the lower surface of the drawer type structure unit bottom plate;
the plurality of drawer-type structure units are combined into at least one group of splicing units, the plurality of drawer-type structure units in each group of splicing units are longitudinally stacked, and the plurality of drawer-type structure units are stacked in the height direction of the drawer-type structure units;
in each group of splicing units, two adjacent layers of drawer type structure units are connected through corresponding mechanical interfaces; the adjacent two layers of drawer type structure units are electrically connected through corresponding connectors, so that the corresponding splicing units are electrically connected; the boss step seam allowance of the upper drawer type structure unit is embedded into the concave step seam allowance of the lower drawer type structure unit;
the switching unit comprises a plurality of reinforcing laminates, and the tops and the bottoms of all the splicing units are respectively covered and fixed with one reinforcing laminate;
the plug-in unit comprises at least one load;
the load is fixed above the splicing unit through a reinforcing laminate positioned at the top of the splicing unit.
The invention has the beneficial effects that:
the space requirement of the satellite on different carrying can be met by the assembling mode, the drawer type structure unit is used as a main body mounting structure of each module of the satellite and is assembled in the satellite body structure in a stacking mode, the integrity and the rigidity of the satellite can be guaranteed, and the requirement of the satellite on the mechanical performance is met. The drawer type structural units are provided with uniform installation interfaces, all modules and units can be spliced quickly, a three-dimensional stacking and splicing mode is supported, and multi-dimensional platform integration and structural reconstruction can be completed quickly.
Meanwhile, all drawer type structure units are provided with uniform installation interfaces, the drawer type structure units can be flexibly expanded according to different loads and task requirements, the types and the number of the expansion modules can be flexibly configured according to the task requirements, the influence of great increase of the development period caused by the expansion of the modules on the design, the manufacture and the like of the satellite can be effectively avoided, the engineering realization is strong, and the industrial production and the commercial application of the satellite are facilitated.
Drawings
FIG. 1 is a schematic view of a drawer-type structure unit and a standard connection structure according to an embodiment of the present invention;
FIG. 2 is a schematic top view of a posture measurement and position control assembly configured with drawer-type structural units and standard connection structures in accordance with one embodiment of the present invention;
FIG. 3 is a schematic top view of a posture measurement and posture control assembly configured with drawer-type structural units and standard connection structures in accordance with an embodiment of the present invention;
FIG. 4 is a top view of a power module configured with drawer-type structural units and standard connection structures in accordance with an embodiment of the present invention;
FIG. 5 is a schematic diagram of a standard modular microsatellite system according to an embodiment of the present invention;
FIG. 6 is a schematic diagram of a standard modular microsatellite system according to an embodiment of the present invention;
FIG. 7 is a block diagram of a standard modular microsatellite system according to an embodiment of the invention.
Detailed Description
In the embodiment, the standard modular microsatellite system comprises a plurality of drawer type structure units 1, a standard connecting structure, a switching unit and an external hanging unit;
the specifications of the drawer-type structure units 1 are the same, and each drawer-type structure unit 1 is provided with a corresponding functional unit;
the standard connecting structure comprises a connector assembly 2-1, a mechanical interface 2-2 and a step type spigot 2-3;
the connector 2-1 is fixed on the outer side wall of the drawer type structure unit 1, and the connector 2-1 is electrically connected with the corresponding functional unit in the drawer type structure unit 1;
the mechanical interfaces 2-2 are distributed and fixed on the outer side wall of the drawer type structural unit 1;
the stepped spigot 2-3 comprises a concave stepped spigot and a convex stepped spigot which are matched with each other;
the concave step seam allowance is arranged on the upper surface of the side plate of the drawer type structure unit 1, and the convex step seam allowance is arranged on the lower surface of the bottom plate of the drawer type structure unit 1;
the drawer-type structure units 1 are combined into at least one group of splicing units, the drawer-type structure units 1 in each group of splicing units are longitudinally stacked, and the drawer-type structure units 1 are longitudinally stacked in the height direction of the drawer-type structure units 1;
in each group of splicing units, two adjacent layers of drawer type structure units 1 are connected through corresponding mechanical interfaces 2-2; the adjacent two layers of drawer type structure units 1 are electrically connected through corresponding connectors 2-1, so that the corresponding splicing units are electrically connected; and the boss step seam allowance of the upper drawer type structure unit 1 is embedded into the concave step seam allowance of the lower drawer type structure unit 1;
the switching unit comprises a plurality of reinforcing laminate plates 3, and the tops and the bottoms of all the splicing units are respectively covered and fixed with one reinforcing laminate plate 3;
the plug-in unit comprises at least one load 4-1;
the load 4-1 is fixed above the splice unit by means of a reinforcement ply 3 located on top of the splice unit.
Specifically, aiming at the development characteristics of the microsatellite and the existing technical problems, the invention provides a design method and a system architecture of a standardized modular microsatellite, as shown in fig. 5 to 7, the design method and the system architecture comprise the following steps: the system comprises a drawer type structure unit 1, a standard connecting structure, a switching unit and an external hanging unit.
The drawer-type structure units 1 have fixed sizes and standardized structures, the drawer-type structure units 1 and the reinforcing laminate 3 are connected with each other by defining standardized standard connecting structures, can be spliced quickly, support a three-dimensional stacking and splicing mode, and can quickly complete multi-dimensional platform integration and structure reconstruction.
As shown in FIG. 1, the standard connection structure comprises a connector 2-1, a mechanical interface 2-2 with a suitable shape and size and a stepped spigot 2-3 respectively arranged on the upper and lower parts of the frame of the drawer type structure unit 1.
As shown in fig. 5 to 7, the transit unit includes a plurality of reinforcing laminates 3 and a bottom bracket 6.
The plug-in unit comprises a load 4-1 and a solar panel 4-2.
Each drawer-type structure unit 1 can be flexibly expanded according to different loads 4-1 and task requirements, and the drawer-type structure units 1 can be assembled into different satellite function modules according to different quantities (or heights). The type and number of the extended satellite function modules can be flexibly configured according to task requirements.
The satellite functional module and the switching unit which are composed of the drawer type structural unit 1 are assembled into a satellite main body structure together in a stacking mode, and the stacking mode can be longitudinal stacking. The size of the satellite functional module and the mechanical interface 2-2 are standardized and universal designs.
When the drawer type structure units are longitudinally stacked, the upper layer drawer type structure unit 1 and the lower layer drawer type structure unit 1 which are longitudinally adjacent are spliced through the stepped seam allowances 2-3. The upper and lower layers of drawer-type structure units 1 can be electrically connected through the connectors 2-1 at the side walls, or when a circuit board with an electrical connection structure and functional units installed inside the drawer-type structure units 1 is required according to the satellite function, the bottom of the drawer-type structure units 1 can be arranged in a hollow manner according to the actual situation, the circuit board is provided with connectors, and the upper and lower layers of drawer-type structure units 1 are electrically connected or data transmission is carried out through the connectors on the circuit board.
The external hanging unit is connected with the reserved interface of the bottom support 6 through the side part of the reinforced laminate 3, and the interface adopts a standardized mechanical interface.
As described above, the standard connection structure and the reinforcing laminate 3 ensure the integrity and rigidity of the satellite and meet the requirements of the satellite on mechanical performance.
In some embodiments, a plurality of groups of splicing units are longitudinally stacked, and two groups of splicing units which are longitudinally adjacent are connected and fixed through one reinforcing laminate 3.
Specifically, the number of groups of splicing units is determined according to the specific functional requirements of the satellite, and the maximum number of layers of the drawer-type structure unit 1 in each group of splicing units is N, where N is an integer greater than 2;
the multiple groups of splicing units are longitudinally stacked, and the two adjacent groups of splicing units are fixedly connected through a reinforcing laminate 3.
As shown in fig. 7, the satellite function module and the transit unit are stacked at intervals. N is then 5, i.e. a splice unit is made up of a stack of at most 5 drawer units 1. And two vertically-stacked splicing units are fixedly connected through the middle reinforcing laminate 3, so that the integrity and rigidity of the satellite are further ensured, and the requirement of the satellite on the mechanical performance is met.
In some embodiments, adjacent drawer-type structural units 1 in the same layer are spliced by corresponding short edges.
Specifically, splicing units are arranged between two adjacent reinforcing laminates 3, and the number of the splicing units is determined according to the specific functional requirements of the satellite; a plurality of drawer type structure units 1 can be arranged on the same layer, and the drawer type structure units 1 are correspondingly spliced through short edges.
In some embodiments, adjacent drawer-type structural units 1 in the same layer are spliced by corresponding long edges.
Specifically, splicing units are arranged between two adjacent reinforcing laminates 3, and the number of the splicing units is determined according to the specific functional requirements of the satellite; a plurality of drawer type structure units 1 can be arranged on the same layer, and the drawer type structure units 1 are correspondingly spliced through long edges.
The satellite functional module and the switching unit which are composed of the drawer type structural units 1 are assembled into the satellite main body structure together in a stacking mode, assembly in various modes can be carried out according to requirements of different tasks and requirements of carrying space, and the stacking mode includes transverse short edge splicing and transverse long edge splicing besides longitudinal stacking. The transverse long edge splicing is that two drawer type structure units 1 on each layer are directly spliced or separately spliced by connecting long edges, and the up-and-down splicing is realized through the reinforcing laminate 3.
As shown in fig. 6, the splicing manner of the splicing unit may also be transverse long-edge splicing, that is, assembling and splicing are performed by connecting long-edge side plates of the drawer-type structural unit 1.
And the quantity of the load 4-1 is determined according to the functional requirements of the satellite, if the load area is too large and exceeds the area of the splicing units in the transverse direction, the load can be fixed by adding a group of drawer type structural units in a mode of splicing the short edges (connecting the long edges) of the satellite in the transverse direction or in a mode of manufacturing a support frame on the existing structure. As shown in fig. 6, the number of the splice units in the transverse direction is 2, and the number of the loads 4-1 is 2, and if one splice unit corresponds to one satellite function module at this time, the loads 4-1 corresponding to different satellite function modules may be different loads.
In a similar way, the splicing mode of the splicing units is transverse short edge splicing, namely the short edge side plates of the drawer type structure unit 1 are connected for assembling and splicing.
In some embodiments, the reinforcement laminate 3 comprises a mechanical interface 2-2 adapted to the drawer-type structural unit 1;
the lower surface of the reinforcing laminate 3 positioned at the top of the splicing unit is provided with a boss step spigot;
the upper surface of the reinforcing laminate 3 positioned at the bottom of the splicing unit is provided with a concave step spigot;
the upper surface and the lower surface of the reinforcing laminated plate 3 positioned between the splicing units are respectively provided with a concave step seam allowance and a convex step seam allowance.
Specifically, the mechanical interface 2-2 and the stepped spigot 2-3 are both standardized and universal designs. So that the reinforcement plate 3 and the drawer-type structural unit 1 can also be spliced by means of a standard connection of this general design.
In some embodiments, one or more of the splice units between two adjacent reinforcement plies 3 is configured as a satellite function module, which is a GPS receiver, measurement and control transponder, or power controller.
Specifically, the drawer-type structure unit 1 may be assembled into different modules according to different numbers (or heights), including a GPS receiver, a measurement and control transponder, and/or a power controller.
As shown in fig. 2, the drawer-type structure unit 1 is configured as an attitude measurement and attitude control assembly, and includes the drawer-type structure unit 1 and the mechanical interface 2-2, as well as a magnetometer 8, a front-mounted flywheel 9 and a fiber-optic gyroscope 10, which are located in the drawer-type structure unit 1.
As shown in fig. 3, the drawer-type structure unit 1 is configured as another attitude measurement and attitude control assembly, except that the drawer-type structure unit 1 and the mechanical interface 2-2 are the same as the above-described actuator, and the front-mounted flywheel 9, the fiber-optic gyroscope 10, and the tilt-mounted flywheel 11 are located in the drawer-type structure unit 1.
As shown in fig. 4, the drawer type structure unit 1 is configured as a power module, and includes the drawer type structure unit 1, a mechanical interface 2-2 and a connector 2-1, and a battery 12 in the drawer type structure unit 1.
The three components can be assembled with other components, so that when the storage battery 9 or the flywheel, the fiber-optic gyroscope 10 and the like are in failure, the drawer-type structure unit 1 is replaced and maintained, the maintenance, replacement or manufacturing time is shortened, the service life of the satellite is prolonged, and the development period is shortened.
In some embodiments, the system further comprises a posture and orbit measurement and posture control module 13 and a satellite and arrow separation device 5;
the attitude and orbit measurement and attitude control module 13 is positioned below the splicing unit and is connected and fixed with the splicing unit;
the satellite and arrow separation device 5 is positioned below the attitude and orbit measurement and attitude control module 13 and is fixedly connected with the attitude and orbit measurement and attitude control module 13.
In some embodiments, the pod further comprises a base bracket 6;
the bottom bracket 6 is positioned below the attitude and orbit measurement and attitude control module 13, and the satellite and arrow separation device 5 is fixedly connected with the attitude and orbit measurement and attitude control module 13 through the bottom bracket 6.
Further, a GPS antenna 7 is also included;
the GPS antenna 7 is fixed in the bottom bracket 6.
In some embodiments, the plug-in unit further comprises at least one solar windsurfing board 4-2;
the solar sailboard 4-2 is fixedly connected with the reinforcing laminate 3.
Specifically, different splicing schemes are proposed according to different splicing modes.
As shown in fig. 5, a standard modular microsatellite system-based assembly scheme is provided, which includes: the solar energy power generation system comprises reinforcing laminated plates 3, a load 4-1, a solar sailboard 4-2, a magnetic torquer 4-3, a posture measurement and posture control module 13, a satellite-rocket separation device 5 and a plurality of drawer type structure units 1 located between the reinforcing laminated plates 3, wherein the drawer type structure units 1 are assembled in a longitudinal stacking mode.
As shown in fig. 6, another modular microsatellite system based assembly is provided, which has the same structure as fig. 5 and comprises: the solar energy collecting device comprises reinforcing laminates 3, solar sailboards 4-2, a plurality of drawer type structure units 1 positioned between the reinforcing laminates 3 and a satellite-rocket separation device 5; in addition, two loads 4-1, a bottom bracket 6 and a GPS antenna 7 are included, as well as a attitude and orbit measurement and attitude control module 13. The drawer-type structural units 1 are further spliced by transverse short edges on the basis of longitudinal splicing, two drawer-type structural units 1 on each layer are spliced in a mode that the short edges are connected (the long edges are connected), and the drawer-type structural units are spliced up and down through the reinforcing laminated plates 3.
Claims (10)
1. A standard modular microsatellite system is characterized by comprising a plurality of drawer type structure units (1), a standard connecting structure, a switching unit and an external hanging unit;
the specifications of the drawer-type structure units (1) are the same, and each drawer-type structure unit (1) is provided with a corresponding functional unit;
the standard connecting structure comprises a connector (2-1), a mechanical interface (2-2) and a step type spigot (2-3);
the connector (2-1) is fixed on the outer side wall of the drawer type structure unit (1), and the connector (2-1) is electrically connected with a corresponding functional unit in the drawer type structure unit (1);
the number of the mechanical interfaces (2-2) is multiple, and the mechanical interfaces are distributed and fixed on the outer side wall of the drawer type structural unit (1);
the stepped spigot (2-3) comprises a concave stepped spigot and a convex stepped spigot which are matched with each other;
the concave step seam allowance is arranged on the upper surface of the side plate of the drawer type structure unit (1), and the convex step seam allowance is arranged on the lower surface of the bottom plate of the drawer type structure unit (1);
the drawer-type structure units (1) are combined into at least one group of splicing units, the drawer-type structure units (1) in each group of splicing units are longitudinally stacked, and the drawer-type structure units (1) are stacked in the longitudinal stacking direction along the height direction of the drawer-type structure units (1);
in each group of splicing units, two adjacent layers of drawer type structure units (1) are connected through corresponding mechanical interfaces (2-2); the adjacent two layers of drawer type structure units (1) are electrically connected through corresponding connectors (2-1), so that the corresponding splicing units are electrically connected; the boss step seam allowance of the upper drawer type structure unit (1) is embedded into the concave step seam allowance of the lower drawer type structure unit (1);
the switching unit comprises a plurality of reinforcing laminate plates (3), and the top and the bottom of all the splicing units are respectively covered and fixed with one reinforcing laminate plate (3);
the plug-in unit comprises at least one load (4-1);
the load (4-1) is fixed above the splicing unit through a reinforcing laminate (3) positioned at the top of the splicing unit.
2. A standard modular microsatellite system as recited in claim 1,
the multiple groups of splicing units are longitudinally stacked, and the two groups of splicing units which are longitudinally adjacent are fixedly connected through a reinforcing laminate (3).
3. A standard modular microsatellite system as in claim 1 or 2,
adjacent drawer type structural units (1) on the same layer are correspondingly spliced through short edges.
4. A standard modular microsatellite system as in claim 1 or 2,
the adjacent drawer type structure units (1) on the same layer are correspondingly spliced through long edges.
5. A standard modular microsatellite system as claimed in claim 2 wherein the reinforcement laminate (3) includes a mechanical interface (2-2) adapted to the drawer-type structural unit (1);
the lower surface of the reinforcing laminate (3) positioned at the top of the splicing unit is provided with a convex step seam allowance;
the upper surface of the reinforcing laminate (3) positioned at the bottom of the splicing unit is provided with a concave step spigot;
the upper surface and the lower surface of the reinforcing laminated plate (3) positioned between the splicing units are respectively provided with a concave step seam allowance and a convex step seam allowance.
6. A standard modular microsatellite system as in claim 2 wherein one or more of the splice units between adjacent two reinforcement slabs (3) are configured as a satellite function module being a GPS receiver, a measurement and control transponder or a power controller.
7. A standard modular microsatellite system according to claim 1, 2, 5 or 6 further including attitude and orbit measurement and attitude control modules (13) and satellite and arrow separation means (5);
the attitude and orbit measurement and control module (13) is positioned below the splicing unit and is fixedly connected with the splicing unit;
the satellite and arrow separation device (5) is positioned below the attitude and orbit measurement and attitude control module (13) and is fixedly connected with the attitude and orbit measurement and attitude control module (13).
8. A standard modular microsatellite system as claimed in claim 7 wherein the pod further includes a base support (6);
the bottom support (6) is positioned below the attitude and orbit measurement and posture control module (13), and the satellite and arrow separation device (5) is fixedly connected with the attitude and orbit measurement and posture control module (13) through the bottom support (6).
9. A standard modular microsatellite system as claimed in claim 8 further including a GPS antenna (7);
the GPS antenna (7) is fixed in the bottom bracket (6).
10. A standard modular microsatellite system as claimed in claim 1 wherein said plug-in unit further comprises at least one solar windsurfing board (4-2);
the solar sailboard (4-2) is fixedly connected with the reinforcing laminate (3).
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| CN202111063283.0A CN113619812A (en) | 2021-09-10 | 2021-09-10 | Standard modular microsatellite system |
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| CN111086658A (en) * | 2019-12-31 | 2020-05-01 | 东方红卫星移动通信有限公司 | Connection and separation device for satellite group transmission |
| CN112340065A (en) * | 2020-10-10 | 2021-02-09 | 苏州泰富晶宇科技有限公司 | Flat satellite platform with high load bearing capacity |
| CN213769017U (en) * | 2020-11-24 | 2021-07-23 | 东方红卫星移动通信有限公司 | Satellite stacking structure for low-earth-orbit satellite group transmission |
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Application publication date: 20211109 |