CN103935533B - Novel satellite and the rocket connection ring structure - Google Patents
Novel satellite and the rocket connection ring structure Download PDFInfo
- Publication number
- CN103935533B CN103935533B CN201410177898.XA CN201410177898A CN103935533B CN 103935533 B CN103935533 B CN 103935533B CN 201410177898 A CN201410177898 A CN 201410177898A CN 103935533 B CN103935533 B CN 103935533B
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- satellite
- interface
- rocket
- connection ring
- ring structure
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Abstract
The present invention provides a kind of novel satellite and the rocket connection ring structure, including interconnective upper end and bottom, wherein, described upper end is polygon, described bottom is circular, and described bottom is provided with the delivery mounting interface of separating switch, the mounting interface of satellite separating switch, tank installing plate interface, satellite transport are parked and used support portion.The present invention achieves the beneficial effects such as simple in construction, light weight, offer various uses interface.
Description
Technical field
The present invention relates to the load-carrying construction of load transmission between satellite and carrier rocket, be specifically related to a kind of novel satellite and the rocket connection ring structure being applied to and being connected between satellite with carrier rocket.
Background technology
It is the attachment structure between a kind of satellite and carrier rocket that the satellite and the rocket connect ring, and between satellite and carrier rocket, the satellite and the rocket connect the upper end of ring and are connected with satellite, and the satellite and the rocket are connected the lower end of ring and are connected by band, fixture block etc. with carrier rocket.Additionally, satellite or delivery separating switch can be installed on this structure, and the support providing satellite to park, transporting.Therefore, the satellite and the rocket connect ring is the key structure affecting satellite coupling stiffness, whole star dynamic response characteristic and the performance such as the satellite and the rocket separate.
At present, the satellite and the rocket connection ring structure form that satellite platform is applied is complicated, quality is big, working place is limited.
Currently without finding the explanation with the same or like technology of the present invention or report, also not yet collect domestic similar data.
Summary of the invention
In order to solve the technical problem that in prior art, satellite and the rocket connection ring structure quality is big, version is complicated, working place is limited, it is an object of the invention to provide a kind of novel satellite and the rocket connection ring structure.Connection ring structure provided by the invention have simple in construction, light weight, easy to operate, be provided that the features such as various uses interface.
According to novel satellite and the rocket connection ring structure provided by the invention, including interconnective upper end and bottom, wherein, described upper end is polygon, described bottom is circular, and described bottom is provided with the delivery mounting interface of separating switch, the mounting interface of satellite separating switch, tank installing plate interface, satellite transport are parked and used support portion.
Preferably, upper and lower end all adopts surface through colourless anodized LD10CS aluminum alloy materials.
Preferably, also including the satellite and the rocket separation interface being provided with band, wherein, described satellite and the rocket separation interface is arranged on described bottom.
Preferably, also including satellite bearing cylinder cylinder interface, wherein, described satellite bearing cylinder cylinder interface is arranged on described bottom.
Preferably, the polygon corner place of described upper end is provided with equidistant Rouno Cormer Pregrinding Wheel R60.
Preferably, also including benchmark prism mounting interface, wherein, described benchmark prism mounting interface is arranged on described bottom.
Preferably, the specification of tank installing plate interface is 12-φ 6.5.
Preferably, satellite transport is parked by the specification of support portion is 16-M5.
Compared with prior art, the present invention has following beneficial effect:
The novel satellite and the rocket connection ring structure of the present invention, configuration and interface to satellite and the rocket connection ring structure have carried out specialized designs, achieve loaded cylinder lower end frame and be connected the integrated design of ring with the satellite and the rocket, therefore, achieve simple in construction, light weight, easy to operate, be provided that the beneficial effect of various uses interface, application prospect is extensive.
Accompanying drawing explanation
By reading detailed description non-limiting example made with reference to the following drawings, the other features, objects and advantages of the present invention will become more apparent upon:
Fig. 1 is the schematic diagram of novel satellite and the rocket connection ring structure provided by the present invention；
In figure: 1 be the delivery mounting interface of separating switch, 2 be the mounting interface of satellite separating switch, 3 be tank installing plate interface, 4 be satellite transport, the support interface parked.
Detailed description of the invention
Below in conjunction with specific embodiment, the present invention is described in detail.Following example will assist in those skilled in the art and are further appreciated by the present invention, but do not limit the present invention in any form.It should be pointed out that, to those skilled in the art, without departing from the inventive concept of the premise, it is also possible to make some deformation and improvement.These broadly fall into protection scope of the present invention.
Fig. 1 is the structural representation of novel satellite and the rocket connection ring structure provided by the invention.As shown in Figure 1, novel satellite and the rocket connection ring structure includes interconnective bottom and upper end, bottom is circular, and as satellite and the rocket parting surface and fixture block contact surface, upper end is provided with the support transported for satellite and the delivery mounting interface of separating switch, tank installing plate interface and satellite, park；Upper end is polygon, connects for satellite polygon loaded cylinder cylinder.
The satellite and the rocket connect ring and adopt LD10CS aluminium alloy to manufacture, and surface adopts colourless anodization reason, strengthens its erosion-resisting efficiency and anti-vacuum cold welding；Upper end polygon surface is polished, and increases itself and loaded cylinder cylinder glue-joint strength.
The bottom of satellite and the rocket connection ring structure is circular, and including the satellite and the rocket separation interface arranging band, external diameter is φ 660mm, and thickness is 3.5mm, 20 ° of chamfered transition.Upper end is polygon, wall thickness 6mm, and corner is provided with equidistant Rouno Cormer Pregrinding Wheel R60, is gluedd joint by Redux420 adhesive with satellite bearing cylinder cylinder, it is achieved that loaded cylinder lower end frame is connected the integrated design of ring with the satellite and the rocket.Select equidistant Rouno Cormer Pregrinding Wheel R60, make the cylinder of connection ring and loaded cylinder glued joint face laminating tightr.
Satellite and the rocket connection is equipped with multiple use interface, including:
1, the mounting interface of delivery and satellite separating switch；
2, φ 550mm cut circle on uniform 12-φ 6.5 through hole as advance tank installing plate interface；
3, the support interface that uniform 16-M5 screwed hole transports as satellite, parks on section circle of φ 605mm；
4, on upper end, it is provided with 4-φ 3.5 through hole mounting interface as benchmark prism bracket.
The satellite and the rocket connect ring with loaded cylinder through satellite mode, vibration, static(al), separation impact etc. it have been experienced that, the novel satellite and the rocket connection ring structure of the present invention has reached simple in construction, rigidity, intensity meet design requirement, reliable in quality, can realize the carrying of about 450kg.And these satellite and the rocket connect ring, quality is about 3.8kg, meets the requirement of system preferably, and the Performance Match for satellite Yu carrier rocket is significant.
As long as additionally, the thickness of opposite end frame suitably adjusts, just can meet the carrying needs of different quality satellite, thus improve the adaptability to load.
In sum, the novel satellite and the rocket connection ring structure of the present invention is by having carried out specialized designs to the configuration and interface that connect ring, achieve loaded cylinder lower end frame and be connected the integrated design of ring with the satellite and the rocket, therefore, achieve simple in construction, light weight, easy to operate, be provided that the beneficial effect of various uses interface, application prospect is extensive.
Above specific embodiments of the invention are described.It is to be appreciated that the invention is not limited in above-mentioned particular implementation, those skilled in the art can make various deformation or amendment within the scope of the claims, and this has no effect on the flesh and blood of the present invention.
Claims (1)
1. a novel satellite and the rocket connection ring structure, it is characterized in that, including interconnective upper end and bottom, wherein, described upper end is polygon, described bottom is circular, and described bottom is provided with the delivery mounting interface of separating switch, the mounting interface of satellite separating switch, tank installing plate interface, satellite transport are parked and used support portion；
Upper and lower end all adopts surface through colourless anodized LD10CS aluminum alloy materials；
Also including the satellite and the rocket separation interface being provided with band, wherein, described satellite and the rocket separation interface is arranged on described bottom；
Also including satellite bearing cylinder cylinder interface, wherein, described satellite bearing cylinder cylinder interface is arranged on described bottom；
The polygon corner place of described upper end is provided with equidistant Rouno Cormer Pregrinding Wheel R60；
Also including benchmark prism mounting interface, wherein, described benchmark prism mounting interface is arranged on described bottom；
The specification of tank installing plate interface is 12-φ 6.5；
It is 16-M5 that satellite transport is parked by the specification of support portion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410177898.XA CN103935533B (en) | 2014-04-29 | 2014-04-29 | Novel satellite and the rocket connection ring structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410177898.XA CN103935533B (en) | 2014-04-29 | 2014-04-29 | Novel satellite and the rocket connection ring structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103935533A CN103935533A (en) | 2014-07-23 |
| CN103935533B true CN103935533B (en) | 2016-07-27 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410177898.XA Expired - Fee Related CN103935533B (en) | 2014-04-29 | 2014-04-29 | Novel satellite and the rocket connection ring structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103935533B (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104296897B (en) * | 2014-09-12 | 2016-08-17 | 上海卫星工程研究所 | The satellite and the rocket six degree of freedom interfacial force computational methods of ring strain measurement are connected based on the satellite and the rocket |
| CN106347713A (en) * | 2016-11-29 | 2017-01-25 | 上海卫星工程研究所 | Direct bearing truss type structure suitable for large satellite and rocket connecting ring |
| CN107380487B (en) * | 2017-06-06 | 2020-11-24 | 上海卫星工程研究所 | Integrated square-to-round satellite-rocket connecting ring |
| CN109823576B (en) * | 2019-02-20 | 2020-11-24 | 上海卫星工程研究所 | Bearing connection structure for planetary lander |
| CN113385803B (en) * | 2021-06-22 | 2022-09-16 | 南昌航空大学 | Electromagnetic pulse material increase device and method for connecting ring of heavy carrier rocket |
| CN113911393A (en) * | 2021-09-29 | 2022-01-11 | 北京空间飞行器总体设计部 | Cone-prism transition type honeycomb interlayer bearing cylinder structure |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103738509A (en) * | 2014-01-21 | 2014-04-23 | 北京航空航天大学 | Novel multi-satellite separating, unlocking and releasing device |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2360852C2 (en) * | 2007-07-30 | 2009-07-10 | Федеральное государственное унитарное предприятие "Государственный космический научно-производственный центр имени М.В. Хруничева" (ФГУП "ГКНПЦ им. М.В. Хруничева") | Device for fixation of rotary platforms for fastening of useful loads |
| ES2386119T3 (en) * | 2009-11-18 | 2012-08-09 | Ruag Schweiz Ag | Zero Shock Separation System |
| FR2959490B1 (en) * | 2010-04-28 | 2012-07-13 | Astrium Sas | SATELLITE HAVING A SIMPLIFIED, ALLEGE AND ECONOMIC STRUCTURE AND ITS IMPLEMENTING METHOD |
| CN203806152U (en) * | 2014-04-29 | 2014-09-03 | 上海卫星工程研究所 | Novel star rocket adapter ring structure |
-
2014
- 2014-04-29 CN CN201410177898.XA patent/CN103935533B/en not_active Expired - Fee Related
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103738509A (en) * | 2014-01-21 | 2014-04-23 | 北京航空航天大学 | Novel multi-satellite separating, unlocking and releasing device |
Non-Patent Citations (1)
| Title |
|---|
| 卫星用大型中心承力筒轻量化设计与分析;方宝东等;《结构及多学科优化工程应用与理论研讨会》;20090903;第272-283页 * |
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| Publication number | Publication date |
|---|---|
| CN103935533A (en) | 2014-07-23 |
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Granted publication date: 20160727 |
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