CN103448919A - Carbon-fiber skin and stringer reinforced bearing cylinder for satellite structure - Google Patents
Carbon-fiber skin and stringer reinforced bearing cylinder for satellite structure Download PDFInfo
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- CN103448919A CN103448919A CN2013103453526A CN201310345352A CN103448919A CN 103448919 A CN103448919 A CN 103448919A CN 2013103453526 A CN2013103453526 A CN 2013103453526A CN 201310345352 A CN201310345352 A CN 201310345352A CN 103448919 A CN103448919 A CN 103448919A
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Abstract
The invention provides a carbon-fiber skin and stringer reinforced bearing cylinder for a satellite structure. The carbon-fiber skin and stringer reinforced bearing cylinder comprises a taper section and a column section connected with each other and formed integrally. Both the taper section and the column section are covered with the skin; the upper end of the column section extends out of an upper end frame, the joint of the column section and the taper section extends out of a middle end frame, and the lower end of the taper section extends out of a lower end frame; a circular flange for providing a lower flange mounting face to a propellant storage tank is adhered to the inner side of the middle end frame, and a circular flange for providing an upper flange mounting face to the propellant storage tank is adhered to the inner side of the middle of the column section. The carbon-fiber skin and stringer reinforced bearing cylinder has the advantages of light weight, simple structure, low manufacturing cost and high universality.
Description
Technical field
The present invention relates to a kind of satellite main force support structure, be specifically related to a kind of carbon fiber skin stringer reinforcement loaded cylinder structure of using for satellite structure.
Background technology
Loaded cylinder is a kind of main force support structure of satellite, is positioned at satellite longitudinal center place, and lower end is connected by band, fixture block etc. with carrier rocket, the support that provides the satellite and the rocket to separate; Upper end and middle-end are connected with the apparatus installation plate of satellite.In addition, on this structure, propellant tank can be installed.Therefore, loaded cylinder is the key structure that affects satellite coupling stiffness, whole star dynamic response characteristic and the performances such as the satellite and the rocket separate.
Summary of the invention
For defect of the prior art, the purpose of this invention is to provide a kind of lightweight loaded cylinder, for the satellite structure primary load bearing, use.
For achieving the above object, the present invention has adopted following technical scheme:
A kind of stringer of the carbon fiber skin for satellite structure reinforcement loaded cylinder, comprise the cone section and the shell of column that are connected, the cone section is one-body molded with shell of column, all be equipped with covering on cone section and shell of column, the upper end frame is extended in the upper end of shell of column, shell of column extends the middle-end frame with the junction of cone section, the lower end frame is extended in the lower end of cone section, the middle-end frame is inboard glueds joint one for the circular flange of propellant tank lower flange attachment face is provided, and the shell of column middle part is inboard glueds joint one for the circular flange of propellant tank upper flange attachment face is provided.
Preferably, described propellant tank lower flange attachment face adopts that carbon fiber epoxy resin is composite material moulded to be formed.
Preferably, described propellant tank upper flange attachment face adopts that carbon fiber epoxy resin is composite material moulded to be formed.
Preferably, described upper end frame, middle-end frame, lower end frame all adopt the laying of carbon fiber epoxy resin composite material to form.
Preferably, also comprise stringer and lower stringer, wherein, upper stringer is arranged on the shell of column outer wall to strengthen support, and lower stringer is arranged on cone section outer wall and supports with reinforcement.
Preferably, the quantity of upper stringer is many, and evenly arranges at the shell of column outer wall, and the quantity of lower stringer is many, and evenly arranges at cone section outer wall.
Preferably, the quantity of upper stringer is 8, and the quantity of lower stringer is 8.
Preferably, described upper stringer and lower stringer all adopt that carbon fiber epoxy resin is composite material moulded to be formed.
Preferably, the lower end frame is in order to connect satellite satellite and the rocket separating part, and the middle-end frame is in order to apparatus installation plate connecting interface to be provided, and the upper end frame is for providing apparatus installation plate connecting interface.
Preferably, the cone section is used carbon fiber composite material to glued joint moulding with shell of column.
Owing to having adopted above technical scheme, make the present invention there is following advantage and good effect:
At first, loaded cylinder provided by the present invention, adopt carbon fiber skin stringer reinforced structure, because loaded cylinder adopts composite material forming fully, the parameters such as size and shape to covering thickness, stringer are optimized design, therefore, have advantages of that quality is light, simple in structure, low cost of manufacture.
Secondly, loaded cylinder provided by the present invention adopts the primary load bearing face of propellant tank lower flange attachment face as propellant tank, and propellant tank upper flange attachment face plays the cross travel restriction, meets the installation requirements of propellant tank " lower-rigid-upper-flexible ".
Again, the laying quantity of covering, the thickness of stringer are adjusted a little, just can be met the demand of different quality satellite, have higher commonality, application prospect is extensive.
The accompanying drawing explanation
By reading the detailed description of non-limiting example being done with reference to the following drawings, it is more obvious that other features, objects and advantages of the present invention will become:
Fig. 1 is the schematic diagram of loaded cylinder of the present invention;
Fig. 2 is the constructional drawing of loaded cylinder of the present invention.
The specific embodiment
Below in conjunction with specific embodiment, the present invention is described in detail.Following examples will contribute to those skilled in the art further to understand the present invention, but not limit in any form the present invention.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.
Core concept of the present invention is, adopt carbon fiber composite material to manufacture a kind of stringer of the carbon fiber skin for satellite structure primary load bearing reinforcement loaded cylinder, in the loaded cylinder outside, reinforced rib evenly is set, play the effect of reinforcement, adopt the mode of increase and decrease covering laying quantity, stringer thickness to meet the different quality demand of different satellites to the loaded cylinder carrying.
Below in conjunction with accompanying drawing, preferred embodiment of the present invention is done and is described in further detail, so that understand.
Embodiment mono-
Please refer to Fig. 2, be hollow structure according to loaded cylinder provided by the invention, comprise cone section covering 1, propellant tank lower flange attachment face 2, propellant tank upper flange attachment face 3, shell of column covering 4, upper end frame 5, upper stringer 6, middle-end frame 7, lower stringer 8 and lower end frame 9.The loaded cylinder carbon fiber composite material glueds joint moulding, and top is cylindrical, and bottom is truncated cone shape.
Please refer to Fig. 1, loaded cylinder of the present invention is cone post one loaded cylinder.
Please refer to Fig. 2, the propellant tank lower flange attachment face 2 primary load bearing faces as propellant tank, 3 cross travel restrictions of propellant tank upper flange attachment face, for installing propellant tank.
In the present embodiment, loaded cylinder whole height 1100 ㎜, cylindrical upper end frame 5 external diameter Φ 730 ㎜, truncated cone shape lower end frame 9 external diameter Φ 950mm, truncated cone shape middle-end frame 7 external diameter Φ 730mm, tank lower flange attachment face 2 internal diameter Φ 630mm, the thickness of cone section covering 1 is 0.9mm, the thickness of shell of column covering 4 is 1.1mm, upper stringer 6, lower stringer 8 thickness 1.5mm.
Loaded cylinder is used carbon fiber composite material to glued joint moulding fully.
That carbon fiber skin for satellite structure stringer reinforcement loaded cylinder provided by the invention has reached is simple in structure, technical maturity, reliable in quality, lower-cost purpose, can realize the carrying of 1.5 tons of left and right.And this loaded cylinder, quality is about 12kg, has met preferably the requirement of system, for the Performance Match of satellite and carrier rocket, is significant.
In addition, as long as the laying quantity of covering, the thickness of stringer are suitably adjusted, just can meet the carrying needs of different quality satellite, thereby improve the comformability to load.
Above specific embodiments of the invention are described.It will be appreciated that, the present invention is not limited to above-mentioned specific implementations, and those skilled in the art can make various distortion or modification within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (10)
1. the stringer of the carbon fiber skin for a satellite structure reinforcement loaded cylinder, it is characterized in that, comprise the cone section and the shell of column that are connected, the cone section is one-body molded with shell of column, all be equipped with covering on cone section and shell of column, the upper end frame is extended in the upper end of shell of column, shell of column extends the middle-end frame with the junction of cone section, the lower end frame is extended in the lower end of cone section, the middle-end frame is inboard glueds joint one for the circular flange of propellant tank lower flange attachment face is provided, and the shell of column middle part is inboard glueds joint one for the circular flange of propellant tank upper flange attachment face is provided.
2. the stringer of the carbon fiber skin for satellite structure reinforcement loaded cylinder according to claim 1, is characterized in that, described propellant tank lower flange attachment face adopts that carbon fiber epoxy resin is composite material moulded to be formed.
3. the stringer of the carbon fiber skin for satellite structure reinforcement loaded cylinder according to claim 1, is characterized in that, described propellant tank upper flange attachment face adopts that carbon fiber epoxy resin is composite material moulded to be formed.
4. the stringer of the carbon fiber skin for satellite structure reinforcement loaded cylinder according to claim 1, is characterized in that, described upper end frame, middle-end frame, lower end frame all adopt the carbon fiber epoxy resin composite material to lay and form.
5. the stringer of the carbon fiber skin for satellite structure reinforcement loaded cylinder according to claim 1, it is characterized in that, also comprise stringer and lower stringer, wherein, upper stringer is arranged on the shell of column outer wall to strengthen support, and lower stringer is arranged on cone section outer wall and supports with reinforcement.
6. the stringer of the carbon fiber skin for satellite structure reinforcement loaded cylinder according to claim 5, is characterized in that, the quantity of upper stringer is many, and evenly arranges at the shell of column outer wall, and the quantity of lower stringer is many, and evenly arrange at cone section outer wall.
7. the stringer of the carbon fiber skin for satellite structure reinforcement loaded cylinder according to claim 5, is characterized in that, the quantity of upper stringer is 8, and the quantity of lower stringer is 8.
8. the stringer of the carbon fiber skin for satellite structure reinforcement loaded cylinder according to claim 7, is characterized in that, described upper stringer and lower stringer all adopt that carbon fiber epoxy resin is composite material moulded to be formed.
9. the stringer of the carbon fiber skin for satellite structure reinforcement loaded cylinder according to claim 1, it is characterized in that, the lower end frame is in order to connect satellite satellite and the rocket separating part, and the middle-end frame is in order to apparatus installation plate connecting interface to be provided, and the upper end frame is for providing apparatus installation plate connecting interface.
10. the stringer of the carbon fiber skin for satellite structure reinforcement loaded cylinder according to claim 1, is characterized in that, the cone section is used carbon fiber composite material to glued joint moulding with shell of column.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013103453526A CN103448919A (en) | 2013-08-08 | 2013-08-08 | Carbon-fiber skin and stringer reinforced bearing cylinder for satellite structure |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2013103453526A CN103448919A (en) | 2013-08-08 | 2013-08-08 | Carbon-fiber skin and stringer reinforced bearing cylinder for satellite structure |
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| CN103448919A true CN103448919A (en) | 2013-12-18 |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2508693A (en) * | 2012-10-15 | 2014-06-11 | Boeing Co | Spacecraft propellant tank mount |
| CN103935529A (en) * | 2014-04-29 | 2014-07-23 | 上海卫星工程研究所 | Rapid response satellite structure |
| CN105034355A (en) * | 2015-06-26 | 2015-11-11 | 上海复合材料科技有限公司 | Preparing method of bearing cylinder |
| CN106482589A (en) * | 2016-12-13 | 2017-03-08 | 中国运载火箭技术研究院 | A kind of stringer housing |
| CN106564618A (en) * | 2016-10-14 | 2017-04-19 | 上海微小卫星工程中心 | Spacecraft pneumatic structure |
| CN106586035A (en) * | 2016-12-09 | 2017-04-26 | 大连理工大学 | Launch vehicle low-temperature composite storage tank with triangular sandwich wall and processing method of tank |
| US9643739B2 (en) | 2012-05-11 | 2017-05-09 | The Boeing Company | Methods and apparatus for performing propulsion operations using electric propulsion systems |
| CN107323698A (en) * | 2017-05-18 | 2017-11-07 | 上海卫星工程研究所 | Satellite-rocket docking uses the load barrel structure of composite end frame |
| CN107738761A (en) * | 2017-09-06 | 2018-02-27 | 上海卫星工程研究所 | Mounting structure is can adjust suitable for the high large size, thin walled tank of rail satellite |
| CN109835504A (en) * | 2019-02-26 | 2019-06-04 | 北京空间飞行器总体设计部 | A kind of tapered loaded cylinder of high-mechanic |
| 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 |
| JP2021172263A (en) * | 2020-04-28 | 2021-11-01 | 株式会社Ｉｈｉエアロスペース | Fuel loading structure and method for manufacturing the same |
| CN114061379A (en) * | 2021-11-16 | 2022-02-18 | 天津爱思达新材料科技有限公司 | Front cabin T-shaped frame reinforcing structure |
| US11286066B2 (en) | 2012-05-11 | 2022-03-29 | The Boeing Company | Multiple space vehicle launch system |
| CN117948845A (en) * | 2023-12-18 | 2024-04-30 | 北京中科宇航技术有限公司 | Box interval structure |
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| CA2097104A1 (en) * | 1993-05-27 | 1994-11-28 | James C. Hastie | Tether, and foot restraining device, securing handrail bracket |
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Cited By (24)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11708181B2 (en) | 2012-05-11 | 2023-07-25 | The Boeing Company | Methods and apparatus for performing propulsion operations using electric propulsion systems |
| US10689132B2 (en) | 2012-05-11 | 2020-06-23 | The Boeing Company | Methods and apparatus for performing propulsion operations using electric propulsion systems |
| US9643739B2 (en) | 2012-05-11 | 2017-05-09 | The Boeing Company | Methods and apparatus for performing propulsion operations using electric propulsion systems |
| US10543938B2 (en) | 2012-05-11 | 2020-01-28 | The Boeing Company | Methods and apparatus for performing propulsion operations using electric propulsion systems |
| US11286066B2 (en) | 2012-05-11 | 2022-03-29 | The Boeing Company | Multiple space vehicle launch system |
| US8973873B2 (en) | 2012-10-15 | 2015-03-10 | The Boeing Company | Spacecraft propellant tank mount |
| GB2508693B (en) * | 2012-10-15 | 2014-12-17 | Boeing Co | Spacecraft propellant tank mount |
| GB2508693A (en) * | 2012-10-15 | 2014-06-11 | Boeing Co | Spacecraft propellant tank mount |
| CN103935529A (en) * | 2014-04-29 | 2014-07-23 | 上海卫星工程研究所 | Rapid response satellite structure |
| CN103935529B (en) * | 2014-04-29 | 2018-01-12 | 上海卫星工程研究所 | A kind of quick response satellite structure |
| CN105034355A (en) * | 2015-06-26 | 2015-11-11 | 上海复合材料科技有限公司 | Preparing method of bearing cylinder |
| CN106564618A (en) * | 2016-10-14 | 2017-04-19 | 上海微小卫星工程中心 | Spacecraft pneumatic structure |
| CN106564618B (en) * | 2016-10-14 | 2020-05-19 | 上海微小卫星工程中心 | Spacecraft pneumatic configuration |
| CN106586035B (en) * | 2016-12-09 | 2018-11-13 | 大连理工大学 | Carrier rocket low-temperature composite material tank and its processing method with triangular sandwich wall |
| CN106586035A (en) * | 2016-12-09 | 2017-04-26 | 大连理工大学 | Launch vehicle low-temperature composite storage tank with triangular sandwich wall and processing method of tank |
| CN106482589A (en) * | 2016-12-13 | 2017-03-08 | 中国运载火箭技术研究院 | A kind of stringer housing |
| CN107323698A (en) * | 2017-05-18 | 2017-11-07 | 上海卫星工程研究所 | Satellite-rocket docking uses the load barrel structure of composite end frame |
| CN107738761A (en) * | 2017-09-06 | 2018-02-27 | 上海卫星工程研究所 | Mounting structure is can adjust suitable for the high large size, thin walled tank of rail satellite |
| CN109835504A (en) * | 2019-02-26 | 2019-06-04 | 北京空间飞行器总体设计部 | A kind of tapered loaded cylinder of high-mechanic |
| JP2021172263A (en) * | 2020-04-28 | 2021-11-01 | 株式会社Ｉｈｉエアロスペース | Fuel loading structure and method for manufacturing the same |
| JP7398331B2 (en) | 2020-04-28 | 2023-12-14 | 株式会社Ｉｈｉエアロスペース | Fuel loading structure and its manufacturing method |
| 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 |
| CN114061379A (en) * | 2021-11-16 | 2022-02-18 | 天津爱思达新材料科技有限公司 | Front cabin T-shaped frame reinforcing structure |
| CN117948845A (en) * | 2023-12-18 | 2024-04-30 | 北京中科宇航技术有限公司 | Box interval structure |
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Application publication date: 20131218 |