CN103448917A - Quick assembly service capsule of high-orbit satellite platform and application of quick assembly service capsule - Google Patents
Quick assembly service capsule of high-orbit satellite platform and application of quick assembly service capsule Download PDFInfo
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- CN103448917A CN103448917A CN2013103453371A CN201310345337A CN103448917A CN 103448917 A CN103448917 A CN 103448917A CN 2013103453371 A CN2013103453371 A CN 2013103453371A CN 201310345337 A CN201310345337 A CN 201310345337A CN 103448917 A CN103448917 A CN 103448917A
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- 239000002775 capsule Substances 0.000 title abstract 9
- 238000003032 molecular docking Methods 0.000 claims abstract description 31
- 238000009434 installation Methods 0.000 claims description 47
- 238000012360 testing method Methods 0.000 abstract description 4
- 238000011161 development Methods 0.000 abstract description 2
- 238000012986 modification Methods 0.000 abstract description 2
- 230000004048 modification Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000010606 normalization Methods 0.000 description 1
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Abstract
The invention discloses a quick assembly service module of a high-orbit satellite platform and application of the quick assembly service capsule. The quick assembly service capsule is of a cylinder structure with a section in the shape of an isosceles trapezoid and is mainly composed of a capsule plate and a capsule plate docking mechanism connected with the capsule plate, and one or multiple the quick assembly service capsules are arranged on the satellite public platform and used for meeting requirements of single-machine matching of different satellites, and can perform parallel quick assembly. Each capsule plate can be used as a mounting face of a single machine, the problem of generality and expansibility of the public platform in different tasks of high-orbit to-ground remote sensing satellites is solved, modification projects, aiming at different task platforms, of the public platform are reduced, whole-satellite single-machine assembly and test time is reduced, and satellite development period is shortened.
Description
Technical field
The present invention relates to the aerospace vehicle field, in particular, relate to a kind of high orbit satellite platform and assemble fast the service module configuration.
Background technology
Early stage satellite platform provides the unit attachment face to be the auxiliary load-carrying construction of satellite or itself to be exactly the satellite main force support structure, exists the problem of dismounting at any time and change.But, in order to meet the installation requirement of the supporting unit of platform, and the change of unit is on the minimum that affects of platform, need a kind of public satellite platform service module of development, can meet the variety classes unit is installed, and the platform component part is concurrent assembly to greatest extent, can the walk abreast requirement of electrical measurement etc. of each system of platform, to meet different mission requirements.
Summary of the invention
For the technical matters existed in above-mentioned prior art, the invention provides a kind of high orbit satellite platform and assemble fast service module and application thereof, can realize that the satellite platform service module assembles fast, unit is by system layout, the assembling of service module independent, the test of whole star module body nearby.Solved under high orbit remote sensing of the earth satellite different task, the commonality of common platform and extendability, the amended subject of platform while having reduced common platform for different task, reduced whole star unit assembling, test duration, shortened the satellite lead time.
To achieve the above object of the invention, the technical solution adopted in the present invention is as follows:
A kind of high orbit satellite platform assembles service module fast, and the cross section that described service module mainly is comprised of the cabin plate docking mechanism of cabin plate and connecting cabin plate is the column structure of isosceles trapezoid.
Described cabin plate comprises: front side plate, rear quarter panel, upper mounting plate, lower installation board, left side board, right side board, described cabin plate docking mechanism comprises for front side plate, quick installation mechanism on the front left of left side board and upper mounting plate docking, for front side plate, quick installation mechanism under the front left of left side board and lower installation board docking, for front side plate, quick installation mechanism on the front right of right side board and upper mounting plate docking, for front side plate, quick installation mechanism under the front right of right side board and lower installation board docking, for rear quarter panel, quick installation mechanism on the rear left of left side board and upper mounting plate docking, for rear quarter panel, quick installation mechanism under the rear left of left side board and lower installation board docking, for rear quarter panel, quick installation mechanism on the rear right of right side board and upper mounting plate docking, for rear quarter panel, quick installation mechanism under the rear right of right side board and lower installation board docking.
Between described each cabin plate and between quick installation mechanism and cabin plate, by screw, install.
Described front side plate can be used as main heat delivery surface, and described left side board and right side board can be used as the auxiliary heat dissipation face.
Above-mentioned high orbit satellite platform assembles the application of service module on satellite platform fast, and the quantity of described quick assembling service module on satellite platform is one or more, in order to meet the unit installation requirement of different satellites.
High orbit satellite platform provided by the present invention assembles the configuration of service module fast, normalisation, integrated design philosophy have been adopted, satellite platform assembles fast service module and adopts the cylinder configuration that cross section is isosceles trapezoid, can utilize to greatest extent the enveloping space of high orbit satellite common platform, and for common platform different task demand, can further increase the quantity that satellite platform assembles service module fast, while for common platform, meeting the different task demand, the different installation requirements of unit product provide possibility.Assembling service module height is that 0.27m(can further expand fast), effectively the attachment face area is 0.7m
2, load-carrying capacity is 100kg, can meet the installation requirement of most of unit.The assembling service module adopts quick installation mechanism to be installed to easily on common platform for satellite fast, can meet whole star concurrent assembly and testing requirement, has shortened the satellite lead time.
The accompanying drawing explanation
Fig. 1 is the structural representation of quick assembling service module provided by the present invention;
Fig. 2 is the exploded drawings of Fig. 1;
Fig. 3 is that quick assembling service module provided by the present invention is assemblied in the schematic diagram on certain high rail common platform for satellite.
The specific embodiment
Below in conjunction with the drawings and specific embodiments, technical solution of the present invention is described in further detail.
Fig. 1, Fig. 2 are the configurations of quick assembling service module provided by the present invention, and the cross section mainly be comprised of the cabin plate docking mechanism of cabin plate and connecting cabin plate is the column structure of isosceles trapezoid.The upper base length in the isosceles trapezoid cross section of the quick assembling service module of the present embodiment is 500mm, the length of going to the bottom is 1330mm, highly for 270mm.
The cabin plate comprises: front side plate 6, rear quarter panel 12, upper mounting plate 2, lower installation board 3, left side board 1, right side board 9, cabin plate docking mechanism comprises for front side plate 6, quick installation mechanism 4 on the front left of left side board 1 and upper mounting plate 2 docking, for front side plate 6, quick installation mechanism 5 under the front left of left side board 1 and lower installation board 3 docking, for front side plate 6, quick installation mechanism 8 on the front right of right side board 9 and upper mounting plate 2 docking, for front side plate 6, quick installation mechanism 7 under the front right of right side board 9 and lower installation board 3 docking, for rear quarter panel 12, quick installation mechanism 14 on the rear left of left side board 1 and upper mounting plate 2 docking, for rear quarter panel 12, quick installation mechanism 13 under the rear left of left side board 1 and lower installation board 3 docking, for rear quarter panel 12, quick installation mechanism 11 on the rear right of right side board 9 and upper mounting plate 2 docking, for rear quarter panel 12, quick installation mechanism 10 under the rear right of right side board 9 and lower installation board 3 docking.Between each cabin plate and between quick installation mechanism and cabin plate, all by screw, install.
Quick assembling service module provided by the present invention, for the different task demand of common platform, can further increase the quantity that satellite platform assembles service module fast, and supporting the providing of unit that meets different capacity weights for common platform may.Shown in Fig. 3, be to assemble fast service module to be assemblied in the schematic diagram on certain high rail common platform for satellite, the embodiment shown in Fig. 3, installed two assembling service modules 100 fast.
High orbit satellite platform provided by the present invention assembles service module fast, and its front side plate can be used as the main heat delivery surface of instrument, and left side board and right side board can be used as the auxiliary heat dissipation face.
The foregoing is only embodiments of the invention, not in order to limit the present invention, all any modifications of doing within the spirit and principles in the present invention, be equal to and replace and improvement etc., within all should being included in protection scope of the present invention.
Claims (4)
1. a high orbit satellite platform assembles service module fast, it is characterized in that, the cross section that described service module mainly is comprised of the cabin plate docking mechanism of cabin plate and connecting cabin plate is the column structure of isosceles trapezoid.
2. high orbit satellite platform according to claim 1 assembles service module fast, it is characterized in that, described cabin plate comprises: front side plate, rear quarter panel, upper mounting plate, lower installation board, left side board, right side board, described cabin plate docking mechanism comprises for front side plate, quick installation mechanism on the front left of left side board and upper mounting plate docking, for front side plate, quick installation mechanism under the front left of left side board and lower installation board docking, for front side plate, quick installation mechanism on the front right of right side board and upper mounting plate docking, for front side plate, quick installation mechanism under the front right of right side board and lower installation board docking, for rear quarter panel, quick installation mechanism on the rear left of left side board and upper mounting plate docking, for rear quarter panel, quick installation mechanism under the rear left of left side board and lower installation board docking, for rear quarter panel, quick installation mechanism on the rear right of right side board and upper mounting plate docking, for rear quarter panel, quick installation mechanism under the rear right of right side board and lower installation board docking.
3. high orbit satellite platform according to claim 2 assembles service module fast, it is characterized in that, between described each cabin plate and between quick installation mechanism and cabin plate, by screw, installs.
4. high orbit satellite platform according to claim 1 assembles the application of service module on satellite platform fast, it is characterized in that, the quantity of described quick assembling service module on common platform for satellite is one or more, supporting in order to the unit that meets the different task satellite.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310345337.1A CN103448917B (en) | 2013-08-08 | 2013-08-08 | A kind of high orbit satellite platform quick assembling service module and application thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310345337.1A CN103448917B (en) | 2013-08-08 | 2013-08-08 | A kind of high orbit satellite platform quick assembling service module and application thereof |
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| Publication Number | Publication Date |
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| CN103448917A true CN103448917A (en) | 2013-12-18 |
| CN103448917B CN103448917B (en) | 2016-12-28 |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104176272A (en) * | 2014-08-06 | 2014-12-03 | 上海卫星工程研究所 | Eight-bar connection non-contact satellite platform configuration |
| CN104787359A (en) * | 2014-12-30 | 2015-07-22 | 上海新跃仪表厂 | Small monitoring satellite structure |
| CN104842219A (en) * | 2015-02-12 | 2015-08-19 | 上海卫星装备研究所 | Satellite structure platform multi-procedure intensive type repairing system and method |
| CN106043741A (en) * | 2016-08-05 | 2016-10-26 | 深圳航天东方红海特卫星有限公司 | Satellite configuration design method adapting to one-rocket multi-satellite launching |
| CN109850186A (en) * | 2019-02-28 | 2019-06-07 | 中国空间技术研究院 | A kind of flat-rack satellite structure and assembly method for several satellite in a rocket parallel connection transmitting |
| CN109878761A (en) * | 2019-02-14 | 2019-06-14 | 上海卫星工程研究所 | Wedge shape space physics field measurement satellite configuration and its assembly method |
| CN109969429A (en) * | 2019-02-13 | 2019-07-05 | 上海卫星工程研究所 | Changeover mechanism |
| CN110217409A (en) * | 2019-05-30 | 2019-09-10 | 北京卫星制造厂有限公司 | In-orbit fast assembling-disassembling micro-nano satellite platform structure |
| 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 |
| CN114476125A (en) * | 2021-12-08 | 2022-05-13 | 浙江时空道宇科技有限公司 | Satellite platform structure |
| CN116280255A (en) * | 2023-03-08 | 2023-06-23 | 中国空间技术研究院 | Universal satellite platform suitable for batch production |
| CN120773930A (en) * | 2025-09-11 | 2025-10-14 | 哈尔滨工大卫星技术有限公司 | Satellite cabin board coupling and connecting mechanism, satellite and satellite cabin board coupling and connecting method |
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Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104176272A (en) * | 2014-08-06 | 2014-12-03 | 上海卫星工程研究所 | Eight-bar connection non-contact satellite platform configuration |
| CN104787359A (en) * | 2014-12-30 | 2015-07-22 | 上海新跃仪表厂 | Small monitoring satellite structure |
| CN104842219A (en) * | 2015-02-12 | 2015-08-19 | 上海卫星装备研究所 | Satellite structure platform multi-procedure intensive type repairing system and method |
| CN106043741A (en) * | 2016-08-05 | 2016-10-26 | 深圳航天东方红海特卫星有限公司 | Satellite configuration design method adapting to one-rocket multi-satellite launching |
| CN106043741B (en) * | 2016-08-05 | 2018-08-07 | 深圳航天东方红海特卫星有限公司 | A kind of satellite configuration design method adapting to several satellite in a rocket transmitting |
| CN109969429B (en) * | 2019-02-13 | 2022-03-18 | 上海卫星工程研究所 | Switching mechanism |
| CN109969429A (en) * | 2019-02-13 | 2019-07-05 | 上海卫星工程研究所 | Changeover mechanism |
| CN109878761A (en) * | 2019-02-14 | 2019-06-14 | 上海卫星工程研究所 | Wedge shape space physics field measurement satellite configuration and its assembly method |
| CN109878761B (en) * | 2019-02-14 | 2020-09-08 | 上海卫星工程研究所 | Wedge-shaped space physical field measurement satellite configuration and assembling method thereof |
| CN109850186A (en) * | 2019-02-28 | 2019-06-07 | 中国空间技术研究院 | A kind of flat-rack satellite structure and assembly method for several satellite in a rocket parallel connection transmitting |
| CN110217409A (en) * | 2019-05-30 | 2019-09-10 | 北京卫星制造厂有限公司 | In-orbit fast assembling-disassembling micro-nano satellite platform structure |
| CN110217409B (en) * | 2019-05-30 | 2020-10-23 | 北京卫星制造厂有限公司 | On-orbit quick dismounting micro-nano satellite platform structure |
| 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 |
| CN114476125A (en) * | 2021-12-08 | 2022-05-13 | 浙江时空道宇科技有限公司 | Satellite platform structure |
| CN114476125B (en) * | 2021-12-08 | 2023-08-15 | 浙江时空道宇科技有限公司 | Satellite platform structure |
| CN116280255A (en) * | 2023-03-08 | 2023-06-23 | 中国空间技术研究院 | Universal satellite platform suitable for batch production |
| CN120773930A (en) * | 2025-09-11 | 2025-10-14 | 哈尔滨工大卫星技术有限公司 | Satellite cabin board coupling and connecting mechanism, satellite and satellite cabin board coupling and connecting method |
| CN120773930B (en) * | 2025-09-11 | 2025-11-14 | 哈尔滨工大卫星技术有限公司 | Satellite cabin board coupling and connecting mechanism, satellite and satellite cabin board coupling and connecting method |
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| Publication number | Publication date |
|---|---|
| CN103448917B (en) | 2016-12-28 |
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