CN105035360A - Cabin-segmentation type separable platform configuration based on four-point connection - Google Patents
Cabin-segmentation type separable platform configuration based on four-point connection Download PDFInfo
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- CN105035360A CN105035360A CN201510466049.0A CN201510466049A CN105035360A CN 105035360 A CN105035360 A CN 105035360A CN 201510466049 A CN201510466049 A CN 201510466049A CN 105035360 A CN105035360 A CN 105035360A
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Abstract
The invention provides a cabin-segmentation type separable platform configuration based on four-point connection, which comprises a platform cabin and a propelling cabin, wherein the platform cabin has a square-hexahedral box-plate type configuration, and the propelling cabin has a square frame type configuration; installation interfaces of explosive bolts are reserved in the same positions of a baseplate of the platform cabin and a baseplate of the propelling cabin, the platform cabin is connected to the propelling cabin by the four explosive bolts, and the propelling cabin is connected to a carrier rocket by the four explosive bolts. In the cabin-segmentation type separable platform configuration based on the four-point connection provided by the invention, both the connection between the platform cabin and the propelling cabin and the connection between the propelling cabin and the propelling rocket adopt the same four-point connection form, and the platform cabin can also be used and independently launched as a satellite structure when the propelling cabin is not used; and if the propelling cabin is not needed after a satellite enters a orbit, the propelling cabin can also be unlocked and separated by the explosive bolts. The cabin-segmentation type separable platform configuration based on the four-point connection provided by the invention expands applicability of a satellite platform.
Description
Technical field
The present invention relates to satellite platform construction techniques field, particularly, relate to a kind of separable platform configuration of cabin segmentation connected based on 4.
Background technology
Public satellite platform towards multitask demand, can adapt to different capacity weights, therefore significantly reduces satellite development cost and lead time.
, usually there is following shortcoming in existing public satellite platform:
Existing public satellite platform, usually the problem that Interface Matching is coordinated and is separated in-orbit is not considered when carrying out subdivision design, make the intersegmental type of attachment in cabin complicated, each cabin section cannot be used alone, satellier injection rear deck section cannot be separated, and can not meet the application demand of following micro-nano satellite seriation, commercialization.
Summary of the invention
For the above-mentioned defect existed in prior art, the object of this invention is to provide a kind of separable platform configuration of cabin segmentation connected based on 4, meet following multitask application and operating needs, make when not needing propulsion module, platform cabin also can be launched separately as satellite structure; If do not need propulsion module after satellier injection, also can be unlocked by explosive bolt and be separated; The present invention extends the comformability of satellite platform.
For achieving the above object, the present invention is achieved by the following technical solutions.
A kind of separable platform configuration of cabin segmentation connected based on 4, for carrier rocket, comprise: platform cabin, described platform cabin adopts square hexahedron boxboard typed configuration, comprise platform ceiling board, platform ceiling board and platform cabin side plate, described platform ceiling board and platform ceiling board are connected to the two ends up and down of described platform cabin side plate respectively.
Preferably, also comprise propulsion module, described propulsion module adopts square frame-type configuration, and comprise propulsion module base plate, propulsion module dividing plate, rood beam and propulsion module side plate, described propulsion module base plate, rood beam, propulsion module side plate are all connected with propulsion module dividing plate;
Described platform cabin is connected with propulsion module by platform ceiling board, and described propulsion module is connected with carrier rocket by propulsion module base plate.
Preferably, described platform ceiling board and propulsion module base plate are equipped with explosive bolt interface, described platform ceiling board is connected with described propulsion module by platform cabin explosive bolt; Described propulsion module base plate is connected with carrier rocket by propulsion module explosive bolt.
Preferably, the explosive bolt interface consistent size on described platform ceiling board and propulsion module base plate.
Preferably, described propulsion module dividing plate is multiple, and multiple propulsion module dividing plate to be centered around around described propulsion module base plate and to be arranged between described propulsion module base plate and described rood beam.
Preferably, the inner side edge of arbitrary described propulsion module dividing plate is curved arc structure.
Preferably, described platform ceiling board, platform ceiling board and platform cabin side plate include carbon fiber and bury frame and honeycomb sandwich panel, and described honeycomb sandwich panel is arranged at carbon fiber and buries in frame.
Preferably, described propulsion module base plate, propulsion module dividing plate and propulsion module side plate include carbon fiber and bury frame and honeycomb sandwich panel, and described honeycomb sandwich panel is arranged at carbon fiber and buries in frame.
Compared with prior art, the present invention has following beneficial effect:
The separable platform configuration of cabin segmentation connected based on 4 provided by the invention, its platform cabin and the connection mode of propulsion module adopt four types of attachment identical with delivery, and when not using propulsion module, platform cabin also can be launched separately as satellite structure; If do not need propulsion module after satellier injection, also can be unlocked by explosive bolt and be separated; The present invention extends the comformability of satellite platform.
Accompanying drawing explanation
By reading the detailed description done non-limiting example with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:
Fig. 1 the present invention is based on 4 cabin segmentation separable platform configuration schematic diagrams connected; Wherein, (a) is platform cabin structure schematic diagram, and (b) is propulsion module structural representation.
In figure: 1 is propulsion module base plate, 2 is propulsion module dividing plate, and 3 is rood beam, and 4 is propulsion module side plate, and 5 is propulsion module explosive bolt, and 6 is platform ceiling board, and 7 is platform ceiling board, and 8 is platform cabin side plate, and 9 is platform cabin explosive bolt.
Detailed description of the invention
Below embodiments of the invention are elaborated: the present embodiment is implemented under premised on technical solution of the present invention, give detailed embodiment and concrete operating process.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, can also make some distortion and improvement, these all belong to protection scope of the present invention.
A kind of separable platform configuration of cabin segmentation connected based on 4, for carrier rocket, comprise: platform cabin, described platform cabin adopts square hexahedron boxboard typed configuration, comprise platform ceiling board, platform ceiling board and platform cabin side plate, described platform ceiling board and platform ceiling board are connected to the two ends up and down of described platform cabin side plate respectively.
Further, also comprise propulsion module, described propulsion module adopts square frame-type configuration, and comprise propulsion module base plate, propulsion module dividing plate, rood beam and propulsion module side plate, described propulsion module base plate, rood beam, propulsion module side plate are all connected with propulsion module dividing plate;
Described platform cabin is connected with propulsion module by platform ceiling board, and described propulsion module is connected with carrier rocket by propulsion module base plate.
Further, described platform ceiling board and propulsion module base plate are equipped with explosive bolt interface, described platform ceiling board is connected with described propulsion module by platform cabin explosive bolt; Described propulsion module base plate is connected with carrier rocket by propulsion module explosive bolt.
Further, the explosive bolt interface consistent size on described platform ceiling board and propulsion module base plate.
Further, described propulsion module dividing plate is multiple, and multiple propulsion module dividing plate to be centered around around described propulsion module base plate and to be arranged between described propulsion module base plate and described rood beam.
Further, the inner side edge of arbitrary described propulsion module dividing plate is curved arc structure.
Further, described platform ceiling board, platform ceiling board and platform cabin side plate include carbon fiber and bury frame and honeycomb sandwich panel, and described honeycomb sandwich panel is arranged at carbon fiber and buries in frame.
Further, described propulsion module base plate, propulsion module dividing plate and propulsion module side plate include carbon fiber and bury frame and honeycomb sandwich panel, and described honeycomb sandwich panel is arranged at carbon fiber and buries in frame.
Below in conjunction with accompanying drawing, the present embodiment is further described.
As shown in Fig. 1 (a) He Fig. 1 (b), platform cabin is square hexahedron boxboard typed configuration, comprises platform ceiling board 6, platform ceiling board 7 and platform cabin side plate 8; Propulsion module is square frame-type configuration, comprises propulsion module base plate 1, propulsion module dividing plate 2, rood beam 3 and propulsion module side plate 4; Platform ceiling board 6 and platform ceiling board 7 are connected to the two ends up and down of described platform cabin side plate 8 respectively, and propulsion module base plate 1, rood beam 3, propulsion module side plate 4 are all connected with propulsion module dividing plate 2.Platform cabin is connected with propulsion module by four platforms cabin explosive bolt 9, and propulsion module is connected with carrier rocket by four propulsion module explosive bolts 5.
Further, platform cabin is square hexahedron boxboard typed configuration, and external envelope is of a size of 590mm × 590mm × 300mm; Propulsion module is square frame-type configuration, and external envelope is of a size of 520mm × 500mm × 475mm.
Particularly:
Platform ceiling board oad is 500mm × 500mm × 15mm, adopts the carbon fiber of high specific strength to bury frame, light weight cellular sandwich plate material; Platform ceiling board oad is 590mm × 590mm × 10mm, adopts the carbon fiber of high specific strength to bury frame, light weight cellular sandwich plate material; Platform cabin side plate totally 4 pieces, wherein 2 pieces of oads are 520mm × 290mm × 10mm, and another 2 pieces of oads are 500mm × 290mm × 10mm, adopt light durable honeycomb interlayer plate material, are connected by screw with platform ceiling board, platform ceiling board; Propulsion module base plate oad is 500mm × 500mm × 15mm, adopts the carbon fiber of high specific strength to bury frame, light weight cellular sandwich plate material; Rood beam external envelope is of a size of 500mm × 500mm × 5mm, adopts aluminum alloy; Propulsion module side plate oad is 500mm × 475mm × 10mm, adopts the carbon fiber of high specific strength to bury frame, light weight cellular sandwich plate material; Propulsion module dividing plate oad is 455mm × 210mm × 10mm, adopts the carbon fiber of high specific strength to bury frame, light weight cellular sandwich plate material, is connected by screw with propulsion module base plate, rood beam, propulsion module side plate.Platform ceiling board and propulsion module base plate all adopt 4 M8 explosive bolts to be connected, and mounting interface pitch circle diameter is Ф 650mm.
The explosive bolt interface of platform ceiling board and the explosive bolt interface size of described propulsion module base plate completely the same.
Configuration body also comprises multiple propulsion module dividing plate, and each described propulsion module dividing plate to be centered around around described propulsion module base plate and to be arranged between described propulsion module base plate and described rood beam.
Platform ceiling board, platform ceiling board, platform cabin side plate, propulsion module base plate, propulsion module dividing plate and propulsion module side plate all adopt the carbon fiber of high specific strength to bury frame, light weight cellular sandwich plate material is made.
The separable platform configuration of cabin segmentation connected based on 4 that the present embodiment provides, its fitting process is as follows:
First, the assembling of platform cabin comprises the following steps, the first step: assembly floor cabin side plate on platform ceiling board; Second step: assembly floor ceiling board on the side plate of platform cabin.
Afterwards, propulsion module assembling comprises the following steps, the first step: assemble propulsion module dividing plate on propulsion module base plate; Second step: assemble rood beam on propulsion module dividing plate; 3rd step: assemble propulsion module side plate on propulsion module dividing plate.
Finally, explosive bolt is used to be connected with propulsion module in platform cabin.
The separable platform configuration of cabin segmentation connected based on 4 that the present embodiment provides, its platform cabin and the connection mode of propulsion module adopt four types of attachment identical with delivery, when not using propulsion module, platform cabin also can be launched separately as satellite structure; If do not need propulsion module after satellier injection, also can be unlocked by explosive bolt and be separated, extend the comformability of satellite platform.
Above specific embodiments of the invention are described.It is to be appreciated that the present invention is not limited to above-mentioned particular implementation, those skilled in the art can make various distortion or amendment within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (8)
1. the separable platform configuration of cabin segmentation connected based on 4, for carrier rocket, it is characterized in that, comprise: platform cabin, described platform cabin adopts square hexahedron boxboard typed configuration, comprise platform ceiling board, platform ceiling board and platform cabin side plate, described platform ceiling board and platform ceiling board are connected to the two ends up and down of described platform cabin side plate respectively.
2. the separable platform configuration of cabin segmentation connected based on 4 according to claim 1, it is characterized in that, also comprise propulsion module, described propulsion module adopts square frame-type configuration, comprise propulsion module base plate, propulsion module dividing plate, rood beam and propulsion module side plate, described propulsion module base plate, rood beam, propulsion module side plate are all connected with propulsion module dividing plate;
Described platform cabin is connected with propulsion module by platform ceiling board, and described propulsion module is connected with carrier rocket by propulsion module base plate.
3. the separable platform configuration of cabin segmentation connected based on 4 according to claim 2, it is characterized in that, described platform ceiling board and propulsion module base plate are equipped with explosive bolt interface, and described platform ceiling board is connected with described propulsion module by platform cabin explosive bolt; Described propulsion module base plate is connected with carrier rocket by propulsion module explosive bolt.
4. the separable platform configuration of cabin segmentation connected based on 4 according to claim 3, is characterized in that, the explosive bolt interface consistent size on described platform ceiling board and propulsion module base plate.
5. the separable platform configuration of cabin segmentation connected based on 4 according to claim 2, it is characterized in that, described propulsion module dividing plate is multiple, and multiple propulsion module dividing plate to be centered around around described propulsion module base plate and to be arranged between described propulsion module base plate and described rood beam.
6. the separable platform configuration of cabin segmentation connected based on 4 according to claim 5, it is characterized in that, the inner side edge of arbitrary described propulsion module dividing plate is curved arc structure.
7. the separable platform configuration of cabin segmentation connected based on 4 according to any one of claim 1 to 6, it is characterized in that, described platform ceiling board, platform ceiling board and platform cabin side plate include carbon fiber and bury frame and honeycomb sandwich panel, and described honeycomb sandwich panel is arranged at carbon fiber and buries in frame.
8. the separable platform configuration of cabin segmentation connected based on 4 according to any one of claim 2 to 6, it is characterized in that, described propulsion module base plate, propulsion module dividing plate and propulsion module side plate include carbon fiber and bury frame and honeycomb sandwich panel, and described honeycomb sandwich panel is arranged at carbon fiber and buries in frame.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105510734A (en) * | 2015-11-26 | 2016-04-20 | 中国空间技术研究院 | Satellite ground system grade electrical property verification platform |
| CN108791953A (en) * | 2018-06-15 | 2018-11-13 | 上海卫星工程研究所 | A kind of trapezoidal moonlet structure for adapting to carry |
| CN112455722A (en) * | 2020-12-07 | 2021-03-09 | 上海卫星工程研究所 | Integrated ultrastable structure system of double-supersatellite platform load cabin and thermal control method thereof |
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| CN103612774A (en) * | 2013-11-20 | 2014-03-05 | 西北工业大学 | Separable micro and nano-satellite configuration |
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| CN104260903A (en) * | 2014-09-16 | 2015-01-07 | 上海卫星工程研究所 | Propelling module structure with independent high-rail satellite platform function |
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2015
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Patent Citations (6)
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| GB2091194A (en) * | 1981-01-17 | 1982-07-28 | Erno Raumfahrttechnik Gmbh | Apparatus for carrying out experiments under conditions of weightlessness |
| CN203114850U (en) * | 2012-12-10 | 2013-08-07 | 上海航天精密机械研究所 | Explosive bolt protective device and cabin structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105510734A (en) * | 2015-11-26 | 2016-04-20 | 中国空间技术研究院 | Satellite ground system grade electrical property verification platform |
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| CN108791953A (en) * | 2018-06-15 | 2018-11-13 | 上海卫星工程研究所 | A kind of trapezoidal moonlet structure for adapting to carry |
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| CN112455722A (en) * | 2020-12-07 | 2021-03-09 | 上海卫星工程研究所 | Integrated ultrastable structure system of double-supersatellite platform load cabin and thermal control method thereof |
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Application publication date: 20151111 |