CN203806149U - Hexagonal frame main bearing satellite structure - Google Patents
Hexagonal frame main bearing satellite structure Download PDFInfo
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- CN203806149U CN203806149U CN201420228874.8U CN201420228874U CN203806149U CN 203806149 U CN203806149 U CN 203806149U CN 201420228874 U CN201420228874 U CN 201420228874U CN 203806149 U CN203806149 U CN 203806149U
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- bar
- hexagonal
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- connector
- roots
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Abstract
The utility model discloses a hexagonal frame main bearing satellite structure which comprises two hexagonal frame components, a plurality of adjustable transverse rods and six longitudinal special-shaped rods. The corner ends of the two hexagonal frame components are respectively connected by the six longitudinal special-shaped rods to form a hexagonal frame. Each longitudinal special-shaped rod is provided with a plurality of mounting holes which are symmetrical. Two special-shaped rods are respectively adjustably connected to one end of the adjustable transverse rod through two corresponding mounting holes. The hexagonal frame main bearing satellite structure is simple, reasonable in technology, high in adjustability, lightweight, convenient to mount, good in expandability, high in adaptability, promising in application prospect, and the like.
Description
Technical field
The utility model relates to satellite technology field, is specifically related to a kind of hexagonal-shaped frame primary load bearing satellite structure.
Background technology
Framed structure and other framing member form satellite structure main body jointly, are provided installing space and position by loading instrument and equipment, bear quiet, the dynamic load that act on satellite, and after supporting it to enter the orbit, on planned orbit, complete set task.Therefore, framework is the crucial main force support structure that affects the performances such as satellite platform structural strength, coupling stiffness and whole star dynamic response characteristic.
At present, the applied framed structure complex forms of satellite platform, quality is large, installing space is limited, poor to the comformability of load.
Utility model content
In order to solve prior art middle frame version complexity, quality is large, installing space is limited, waits not enoughly to the comformability of load is poor, the purpose of this utility model is to provide a kind of hexagonal-shaped frame primary load bearing satellite structure.The utility model provides the hexagonal carbon fiber framework of spatial altitude in a kind of lightweight, simple in structure, adjustable cabin, is used for solving the problems of the technologies described above.
To achieve these goals, the utility model is to realize by the following technical solutions: a kind of hexagonal-shaped frame primary load bearing satellite structure, comprise two hexagon frames, some adjustable cross bars and the longitudinal special-shaped bar of the six roots of sensation, the angle end of described two hexagon frames connects into hexagonal-shaped frame by the longitudinal different in nature bar of the six roots of sensation respectively, described longitudinal special-shaped bar is provided with some mounting holes that are symmetrical structure, passes through two corresponding mounting holes one end of the adjustable cross bars of adjustable connection respectively between described two special-shaped bars.The angle end of two hexagon frames connects into hexagonal-shaped frame by the longitudinal different in nature bar of the six roots of sensation respectively provides six side is installed.
Described hexagon frame comprises the horizontal square bar of the six roots of sensation and six T-pipe joints, and the horizontal square bar of the described six roots of sensation forms hexagon frame by six T-pipe joints.Wherein laterally square bar is to be made up of carbon/epoxy composite material; T-pipe joint is to be made up of carbon fibre material.
The horizontal square bar length of the described six roots of sensation is identical, and described T-pipe joint is provided with the first connector and the second connector for connecting horizontal square bar end, and the horizontal square bar of the described six roots of sensation forms regular hexagon framework by the first connector and the second connector connector.Regular hexagon framework provides larger installing space for satellite platform, and stress balance, uses more firm.
In described T-pipe joint, joint among three members is used for connecting longitudinal special-shaped boom end, and joint among three members vertical the first connector and the second connector respectively.
Described horizontal square bar is provided with embedded part in some bars.
The material of described horizontal square bar, longitudinal special-shaped bar, adjustable cross bar is high modulus carbon fiber material M55J-6K, and layering type is [± 45 °/0 °
4/ 90 °/0 °
3] s.
The utility model hexagonal-shaped frame primary load bearing satellite structure, the laying of configuration to framework, material, composite material etc. is optimized design and simulation analysis, intermediate lateral square bar is connected and carries out customized design with longitudinal special-shaped bar, realize the adjustable in space in cabin, therefore, obtained simple in structure, the beneficial effect such as quality is light, easy for installation, favorable expandability, strong adaptability, application prospect is extensive.
Brief description of the drawings
Describe the utility model in detail below in conjunction with the drawings and specific embodiments;
Fig. 1 is the structural representation of the utility model hexagonal-shaped frame primary load bearing satellite structure embodiment;
Fig. 2 is adjustable cross bar and longitudinal special-shaped bar connection diagram in Fig. 1;
Fig. 3 is T-pipe joint structural representation in Fig. 1;
Fig. 4 is horizontal square bar structural representation in Fig. 1;
Fig. 5 is longitudinal special-shaped bar structural representation in Fig. 1;
Fig. 6 is adjustable bar structure schematic diagram in Fig. 1.
In figure, be labeled as: 1. laterally square bar, 2. T-pipe joint, 3. longitudinal special-shaped bar, 4. adjustable cross bar, 5. embedded part in bar.
Detailed description of the invention
For technological means, creation characteristic that the utility model is realized, reach object and effect is easy to understand, below in conjunction with detailed description of the invention, further set forth the utility model.
The utility model provides a kind of hexagonal-shaped frame primary load bearing satellite structure according to the deficiencies in the prior art, as depicted in figs. 1 and 2, comprise the longitudinal special-shaped bar 3 of two hexagon frames, adjustable cross bar 4 and the six roots of sensation, the angle end of described two hexagon frames connects into hexagonal-shaped frame by the longitudinal different in nature bar 3 of the six roots of sensation respectively, described longitudinal special-shaped bar 3 is provided with some mounting holes that are symmetrical structure, passes through two corresponding mounting holes one end of the adjustable cross bars 4 of adjustable connection respectively between described two special-shaped bars 3.Described horizontal square bar 1 is provided with embedded part 5 in some bars.
As shown in figures 1 and 3, described hexagon frame comprises the horizontal square bar 1 of the six roots of sensation and six T-pipe joints 2, the horizontal square bar 1 of the described six roots of sensation forms hexagon frame by six T-pipe joints 2, horizontal square bar 1 length of the described six roots of sensation is identical, described T-pipe joint 2 is provided with the first connector and the second connector for connecting horizontal square bar 1 end, and the horizontal square bar 1 of the described six roots of sensation forms regular hexagon by the first connector and the second connector connector.In described T-pipe joint 2, joint among three members is used for connecting longitudinal special-shaped bar 3 ends, and joint among three members vertical the first connector and the second connector respectively.
T-pipe joint 2 reinforcing materials are as shown in Figure 3 selected high strength T800S-12K carbon fibre material, and basis material is epoxy AG-80 resin matrix, forms through mold pressing.
Horizontal square bar material is as shown in Figure 4 carbon/epoxy composite material, and reinforcing material is selected high-modulus M55J-6K carbon fibre material, and basis material is epoxy AG-80 resin matrix, and layering type is [± 45 °/0 °
4/ 90 °/0 °
3]
s
Longitudinal special-shaped bar structure is as shown in Figure 5 polygon, for two side plates and upper lower clapboard provide attachment face, material is carbon/epoxy composite material, and reinforcing material is selected high-modulus M55J-6K carbon fibre material, basis material is epoxy AG-80 resin matrix, layering type [± 45 °/0
4°/90 °/0
3°]
s.
Adjusting beam material is as shown in Figure 6 carbon/epoxy composite material, and reinforcing material is selected high-modulus M55J-6K carbon fibre material, and basis material is epoxy AG-80 resin matrix, and layering type is [± 45 °/0 °
4/ 90 °/0 °
3]
s.Be connected with splicing by riveted joint with carbon fiber gusset plate.
The above is preferred implementation of the present utility model; should be understood that; for those skilled in the art; do not departing under the prerequisite of principle described in the utility model; can also make some improvements and modifications, these improvements and modifications also should be considered as protection domain of the present utility model.
Claims (6)
1. a hexagonal-shaped frame primary load bearing satellite structure, it is characterized in that, comprise two hexagon frames, adjustable cross bar (4) and the longitudinal special-shaped bar of the six roots of sensation (3), the angle end of described two hexagon frames connects into hexagonal-shaped frame by the longitudinal different in nature bar of the six roots of sensation (3) respectively, described longitudinal special-shaped bar (3) is provided with some mounting holes that are symmetrical structure, passes through two corresponding mounting holes one end of the adjustable cross bars of adjustable connection (4) respectively between described two special-shaped bars (3).
2. hexagonal-shaped frame primary load bearing satellite structure according to claim 1, it is characterized in that, described hexagon frame comprises the horizontal square bar of the six roots of sensation (1) and six T-pipe joints (2), and the horizontal square bar of the described six roots of sensation (1) forms hexagon frame by six T-pipe joints (2).
3. hexagonal-shaped frame primary load bearing satellite structure according to claim 2, it is characterized in that, the horizontal square bar of the described six roots of sensation (1) length is identical, described T-pipe joint (2) is provided with the first connector and the second connector for connecting horizontal square bar (1) end, and the horizontal square bar of the described six roots of sensation (1) forms regular hexagon frame by the first connector and the second connector connector.
4. hexagonal-shaped frame primary load bearing satellite structure according to claim 2, it is characterized in that, in described T-pipe joint (2), joint among three members is used for connecting longitudinal special-shaped bar (3) end, and joint among three members vertical the first connector and the second connector respectively.
5. according to the hexagonal-shaped frame primary load bearing satellite structure described in claim 2 to 4 any one, it is characterized in that, described horizontal square bar (1) is provided with embedded part (5) in some bars.
6. hexagonal-shaped frame primary load bearing satellite structure according to claim 2, it is characterized in that, the material of described horizontal square bar (1), longitudinal special-shaped bar (3), adjustable cross bar (4) is high modulus carbon fiber material M55J-6K, and layering type is [± 45 °/0 °
4/ 90 °/0 °
3] s.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420228874.8U CN203806149U (en) | 2014-05-06 | 2014-05-06 | Hexagonal frame main bearing satellite structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420228874.8U CN203806149U (en) | 2014-05-06 | 2014-05-06 | Hexagonal frame main bearing satellite structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203806149U true CN203806149U (en) | 2014-09-03 |
Family
ID=51444942
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420228874.8U Expired - Fee Related CN203806149U (en) | 2014-05-06 | 2014-05-06 | Hexagonal frame main bearing satellite structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203806149U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103963998A (en) * | 2014-05-06 | 2014-08-06 | 上海卫星工程研究所 | Main force-bearing satellite structure with hexagonal framework |
| CN104309824A (en) * | 2014-09-12 | 2015-01-28 | 上海卫星工程研究所 | Satellite configuration of embedded compound eye camera load |
| CN104787359A (en) * | 2014-12-30 | 2015-07-22 | 上海新跃仪表厂 | Small monitoring satellite structure |
| CN106742084A (en) * | 2016-11-23 | 2017-05-31 | 上海卫星工程研究所 | It is a kind of to be applied to the eight prism support meanss that 15 antennas are uniformly installed |
-
2014
- 2014-05-06 CN CN201420228874.8U patent/CN203806149U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103963998A (en) * | 2014-05-06 | 2014-08-06 | 上海卫星工程研究所 | Main force-bearing satellite structure with hexagonal framework |
| CN104309824A (en) * | 2014-09-12 | 2015-01-28 | 上海卫星工程研究所 | Satellite configuration of embedded compound eye camera load |
| CN104787359A (en) * | 2014-12-30 | 2015-07-22 | 上海新跃仪表厂 | Small monitoring satellite structure |
| CN106742084A (en) * | 2016-11-23 | 2017-05-31 | 上海卫星工程研究所 | It is a kind of to be applied to the eight prism support meanss that 15 antennas are uniformly installed |
| CN106742084B (en) * | 2016-11-23 | 2019-08-02 | 上海卫星工程研究所 | A kind of eight prism support devices uniformly installed suitable for 15 antennas |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140903 Termination date: 20210506 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |