CN103963998A - Main force-bearing satellite structure with hexagonal framework - Google Patents
Main force-bearing satellite structure with hexagonal framework Download PDFInfo
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- CN103963998A CN103963998A CN201410188593.9A CN201410188593A CN103963998A CN 103963998 A CN103963998 A CN 103963998A CN 201410188593 A CN201410188593 A CN 201410188593A CN 103963998 A CN103963998 A CN 103963998A
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Abstract
The invention discloses a main force-bearing satellite structure with a hexagonal framework. The main force-bearing satellite structure comprises two hexagonal frames, a plurality of adjustable transverse rods and six longitudinal specially-shaped rods. The corners of the two hexagonal frames are connected to form the hexagonal framework through the six longitudinal specially-shaped rods, each longitudinal specially-shaped rod is provided with a plurality of installation holes which are of symmetrical structures, and every two specially-shaped rods are respectively in adjustable connection with one end of the corresponding adjustable transverse rod through two corresponding installation holes. The main force-bearing satellite structure with the hexagonal framework is simple, reasonable in technology, and high in adjustability, has the advantages of being low in overall weight, convenient to install, good in expansibility, high in adaptability and the like, and has a wide application prospect.
Description
Technical field
The present invention relates to satellite technology field, be 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.
Summary of the invention
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 object of the present invention is to provide a kind of hexagonal-shaped frame primary load bearing satellite structure.The hexagonal carbon fiber framework that the invention provides 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 present invention realizes 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.
Hexagonal-shaped frame primary load bearing satellite structure of the present invention, 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 present invention in detail below in conjunction with the drawings and specific embodiments;
Fig. 1 is the structural representation of hexagonal-shaped frame primary load bearing satellite structure embodiment of the present invention;
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 present invention is realized, reach object and effect is easy to understand, below in conjunction with detailed description of the invention, further set forth the present invention.
The present invention 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 the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, do not departing under the prerequisite of principle of the present invention; can also make some improvements and modifications, these improvements and modifications also should be considered as protection scope of the present invention.
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 1 and 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.
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| CN201410188593.9A CN103963998B (en) | 2014-05-06 | 2014-05-06 | A kind of hexagonal-shaped frame primary load bearing satellite structure |
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|---|---|---|---|
| CN201410188593.9A CN103963998B (en) | 2014-05-06 | 2014-05-06 | A kind of hexagonal-shaped frame primary load bearing satellite structure |
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| CN103963998B CN103963998B (en) | 2017-03-01 |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105083590A (en) * | 2015-09-02 | 2015-11-25 | 南京理工大学 | Multiunit cubesat main load-bearing structure |
| CN105269492A (en) * | 2015-11-23 | 2016-01-27 | 上海卫星装备研究所 | Glue joint positioning device and method for high-accuracy hexagonal-prism satellite main force bearing frame |
| CN105667836A (en) * | 2016-03-03 | 2016-06-15 | 航天东方红卫星有限公司 | Satellite strut structure |
| CN105883003A (en) * | 2016-04-28 | 2016-08-24 | 南京理工大学 | Multi-unit cubic star main load-bearing structure based on carbon fiber composite |
| RU2621221C1 (en) * | 2015-12-22 | 2017-06-01 | Российская Федерация, от имени которой выступает Федеральное космическое агентство | Service system module |
| CN107010194A (en) * | 2017-01-17 | 2017-08-04 | 深圳市哈威飞行科技有限公司 | The carbon fiber three-way connection structure and its manufacture method of duct aircraft |
| CN104441690B (en) * | 2014-11-06 | 2018-09-11 | 上海复合材料科技有限公司 | A kind of forming method of tank mounting plate preburied frame |
| IT201700091364A1 (en) * | 2017-08-07 | 2019-02-07 | Lettich Silvio | STRUCTURED SET TO CREATE SATELLITE STRUCTURES |
| CN110683077A (en) * | 2019-09-19 | 2020-01-14 | 上海卫星工程研究所 | Trapezoidal satellite structure suitable for radar antenna and manufacturing method |
| CN111230474A (en) * | 2020-01-10 | 2020-06-05 | 哈尔滨工业大学 | Assembling device, parallel assembling equipment and assembling method for microsatellite |
| CN116176867A (en) * | 2023-05-04 | 2023-05-30 | 北京凌空天行科技有限责任公司 | Modularized cabin section |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104441690B (en) * | 2014-11-06 | 2018-09-11 | 上海复合材料科技有限公司 | A kind of forming method of tank mounting plate preburied frame |
| CN105083590B (en) * | 2015-09-02 | 2017-03-22 | 南京理工大学 | Multiunit cubesat main load-bearing structure |
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| RU2621221C1 (en) * | 2015-12-22 | 2017-06-01 | Российская Федерация, от имени которой выступает Федеральное космическое агентство | Service system module |
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| CN105883003A (en) * | 2016-04-28 | 2016-08-24 | 南京理工大学 | Multi-unit cubic star main load-bearing structure based on carbon fiber composite |
| CN107010194A (en) * | 2017-01-17 | 2017-08-04 | 深圳市哈威飞行科技有限公司 | The carbon fiber three-way connection structure and its manufacture method of duct aircraft |
| IT201700091364A1 (en) * | 2017-08-07 | 2019-02-07 | Lettich Silvio | STRUCTURED SET TO CREATE SATELLITE STRUCTURES |
| WO2019030787A1 (en) * | 2017-08-07 | 2019-02-14 | LETTICH, Silvio | Structured set to make satellite structures |
| CN110683077A (en) * | 2019-09-19 | 2020-01-14 | 上海卫星工程研究所 | Trapezoidal satellite structure suitable for radar antenna and manufacturing method |
| CN111230474A (en) * | 2020-01-10 | 2020-06-05 | 哈尔滨工业大学 | Assembling device, parallel assembling equipment and assembling method for microsatellite |
| CN116176867A (en) * | 2023-05-04 | 2023-05-30 | 北京凌空天行科技有限责任公司 | Modularized cabin section |
| CN116176867B (en) * | 2023-05-04 | 2023-10-20 | 北京凌空天行科技有限责任公司 | Modularized cabin section |
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| CN103963998B (en) | 2017-03-01 |
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