CN105122964B - Grapefruit satellite platform loaded cylinder - Google Patents
Grapefruit satellite platform loaded cylinderInfo
- Publication number
- CN105122964B CN105122964B CN200710306468.3A CN200710306468A CN105122964B CN 105122964 B CN105122964 B CN 105122964B CN 200710306468 A CN200710306468 A CN 200710306468A CN 105122964 B CN105122964 B CN 105122964B
- Authority
- CN
- China
- Prior art keywords
- shell
- cylindrical shell
- column
- end frame
- carbon
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 240000000560 Citrus x paradisi Species 0.000 title claims abstract description 11
- 239000003292 glue Substances 0.000 claims abstract description 11
- 239000004593 Epoxy Substances 0.000 claims description 24
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 17
- 229910052799 carbon Inorganic materials 0.000 claims description 17
- 239000002131 composite material Substances 0.000 claims description 15
- 238000000034 method Methods 0.000 claims description 12
- 239000000463 material Substances 0.000 claims description 10
- 239000004411 aluminium Substances 0.000 claims description 8
- 229910052782 aluminium Inorganic materials 0.000 claims description 8
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 7
- 239000004917 carbon fiber Substances 0.000 claims description 7
- 238000010276 construction Methods 0.000 claims description 7
- 239000011159 matrix material Substances 0.000 claims description 7
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 7
- 239000012779 reinforcing material Substances 0.000 claims description 7
- 239000011347 resin Substances 0.000 claims description 7
- 229920005989 resin Polymers 0.000 claims description 7
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 6
- 239000003795 chemical substances by application Substances 0.000 claims description 6
- 238000002360 preparation method Methods 0.000 claims description 6
- 229910052751 metal Inorganic materials 0.000 claims description 4
- 239000002184 metal Substances 0.000 claims description 4
- 239000000853 adhesive Substances 0.000 claims description 3
- 230000001070 adhesive effect Effects 0.000 claims description 3
- 238000000748 compression moulding Methods 0.000 claims description 3
- 238000007711 solidification Methods 0.000 claims description 3
- 238000007743 anodising Methods 0.000 claims description 2
- 230000006978 adaptation Effects 0.000 abstract description 2
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 238000005516 engineering process Methods 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 230000010354 integration Effects 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 208000020442 loss of weight Diseases 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
Abstract
The invention discloses a kind of grapefruit satellite platform loaded cylinder, comprising: cylindrical shell [2], it has shell of column and cone section; The embedding glue of its upper end shell of column has a upper end frame [1], and the embedding glue in bottom of lower end cone section has a lower end frame [4]; The outer wall of cylindrical shell [2] glueds joint a middle-end frame [3] in the intermediate location of shell of column and cone section, is connected with satellite structure plate; The inwall that the inwall of cylindrical shell [2] shell of column glueds joint has installing frame [6] on a tank, cylindrical shell [2] to bore section glueds joint installing frame [7] under a tank; Four shell of column stringers [5] are evenly arranged around the shell of column of cylindrical shell [2], four cones section stringer [8] are evenly arranged around the cone section of cylindrical shell [2], the invention solves the problems such as loaded cylinder quality is large, separating interface is many, weak to load adaptation, response characteristic is poor, achieve the beneficial effects such as structure is simple, quality light, strong adaptability.<pb pnum="1" />
Description
Technical field
The present invention relates to the load-carrying construction of satellite Main Load, be specifically related to a kind of platform loaded cylinder being applied to grapefruit satellite.
Background technology
Loaded cylinder is the load-carrying construction of carrying satellite Main Load, it is the core of satellite structure assembling, the apparatus installation plate of it and surrounding is connected to become satellite main structure, the propulsion system installation of tank, satellite directly can be provided to connect with carrier rocket the interface be separated, design, manufacture, assembling, the benchmark of precision measure and test, the support of transport and the interface of ground-support equipment can be provided for satellite interface again.Therefore, loaded cylinder is the crucial main force support structure affecting the performances such as satellite platform structural strength, coupling stiffness and whole star dynamic response characteristic.
At present, the loaded cylinder applied of grapefruit satellite (quality about a ton) platform adopts the metal construction of component design, and quality is large, separating interface is many, satellite to the comformability of load and response characteristic poor.
Do not find explanation and the report of technology similar to the present invention at present, not yet collect domestic similar data yet.
Summary of the invention
In order to solve in prior art the deficiencies such as loaded cylinder quality is large, separating interface is many, weak to load adaptation, response characteristic is poor.The object of the present invention is to provide a kind of grapefruit satellite platform loaded cylinder.The invention provides the honeycomb sandwich construction loaded cylinder of a kind of integration, light-weight design, be used for solving the problems of the technologies described above.
In order to reach foregoing invention object, the present invention is to provide a kind of grapefruit satellite platform loaded cylinder for the technical scheme that its technical matters of solution adopts, and this device comprises: the cylindrical shell with shell of column and cone section; The embedding glue of its upper end shell of column has a upper end frame, and the embedding glue in bottom of lower end cone section has a lower end frame; The outer wall of cylindrical shell glueds joint a middle-end frame in the intermediate location of shell of column and cone section, is connected with satellite structure plate; The inwall that the inwall of cylindrical shell shell of column glueds joint has installing frame on a tank, cylindrical shell to bore section glueds joint installing frame under a tank; Be evenly arranged four stringers around the shell of column of cylindrical shell and cone section, comprise: four shell of column stringers and four cone section stringers.
Above-mentioned cylindrical shell comprises inside and outside covering and honeycomb core; Inside and outside covering is carbon/epoxy composite material, and reinforcing material is T300-3k carbon fiber, and basis material is epoxy 648/BF3MEA resin matrix; Shell of column panel laying is ± 45 °/0 °/90 °, cone section panel laying is ± 45 °/0 °/
45 °; The porose durability aluminium honeycomb of honeycomb core adopts that material is LF2Y, highly to be 6.5mm, specification be 4-0.04; The J-7890 DEG C of consolidated structures adhesion agent that inside and outside covering and aluminium honeycomb core adopt thickness to be not less than 0.2mm glueds joint.
Above-mentioned cylindrical shell adopts female mould forming; The preparation of carbon/epoxy composite material covering and the preparation of loaded cylinder cylindrical shell sandwich structure adopt vacuum bag-solidification of hot-press tank forming process; Various carbon/epoxy composite material profiled piece adopts hand to stick with paste a compression-moulding methods; Metal parts adopts conventional machine-tooled method; Utilize former both ends of the surface as the reference plane of assembling upper end frame, lower end frame, and glued joint upper and lower end frame after adopting Redux420 adhesion agent; All the other respectively hold frame, stringer to adopt the technique of Redux420 adhesive glue one spiral shell Hybrid connections equally.
Grapefruit satellite platform loaded cylinder of the present invention, owing to carrying out specific selection to covering, honeycomb, end frame, stringer etc., laying optimization has been carried out to covering, opposite end frame, connection between stringer and cylindrical shell carry out customized design, therefore, not only reach the requirement of the aspect such as integration, lightweight, and loaded cylinder can bear the load weight of about a ton, achieve the beneficial effects such as structure is simple, quality light, strong adaptability, application prospect is extensive.
Accompanying drawing explanation
Accompanying drawing is the structural representation of the small-sized compact platform loaded cylinder of the present invention.
Be labeled as in figure: 1. installing frame, 8. vertebra section stringer under installing frame, 7. tank on upper end frame, 2. cylindrical shell, 3. middle-end frame, 4. lower end frame, 5. shell of column stringer, 6. tank.
Detailed description of the invention
Below in conjunction with accompanying drawing, the preferred embodiments of the present invention are described.
Loaded cylinder of the present invention adopts and is cylindrical shell with carbon/epoxy covering-aluminium honeycomb sandwich construction, is aided with the array configuration of end frame and stringer, is overallly made up of shell of column and vertebra section two parts.
Accompanying drawing is the structural representation of grapefruit satellite platform loaded cylinder of the present invention.As shown in accompanying drawing embodiment, this device comprises:
Cylindrical shell 2, it has shell of column and cone section; Play the embedding glue of upper end shell of column and have a upper end frame 1, the embedding glue in bottom of lower end cone section has a lower end frame 4; The outer wall of cylindrical shell 2 glueds joint a middle-end frame 3 in the intermediate location of shell of column and cone section, realizes the connection with satellite structure plate; The inwall of cylindrical shell 2 shell of column glueds joint the inwall of installing frame 6 on a tank, cylindrical shell 2 section of cone to glued joint to have installing frame 7 under a tank, provides the installation of satellite tank and realizes upper flexible and lower rigid connection.Be evenly arranged four stringers around the shell of column of cylindrical shell 2 and cone section, comprise: shell of column stringer 5 and shell of column stringer 8.
Lower end frame 4 adopts LD10CS, and the satellite and the rocket burbling area contacted with Clamp band fixture block adopts colourless anodizing; All the other four ends frame (on middle-end frame 3, upper end frame 1, tank under installing frame 6, tank installing frame 7) are carbon/epoxy composite material, the reinforcing material of carbon/epoxy composite material end frame is T700-12K carbon fiber, and basis material is epoxy 648/BF3MEA resin matrix.
Above-mentioned shell of column stringer 5, cone section stringer 8 realize the connection with satellite structure plate.Stringer is carbon/epoxy composite material, and reinforcing material is T700-12k carbon fiber, and basis material is epoxy 648/BF3MEA resin matrix.
In the present embodiment, loaded cylinder whole height 1238mm.Cylindrical shell shell of column external diameter φ 500mm, height 698mm; External diameter height φ 910mm bottom cone section, height 480mm.
Cylindrical shell 2 is made up of inside and outside covering and honeycomb core.Inside and outside covering is carbon/epoxy composite material, and reinforcing material is T300-3k carbon fiber, and basis material is epoxy 648/BF3MEA resin matrix; Shell of column panel laying be [± 45 °/0 °/90 °], cone section face laying for [± 45 °/0 °/
45 °].The porose durability aluminium honeycomb of honeycomb core adopts that material is LF2Y, highly to be 6.5mm, specification be 4-0.04.The J-7890 DEG C of consolidated structures adhesion agent that inside and outside covering and aluminium honeycomb core adopt thickness to be not less than 0.2mm glueds joint.
For ensureing the oad precision of loaded cylinder, adopt female mould forming loaded cylinder cylindrical shell.The preparation of carbon/epoxy composite material covering and the preparation of loaded cylinder cylindrical shell sandwich structure adopt vacuum bag-solidification of hot-press tank forming process.Various carbon/epoxy composite material profiled piece adopts hand paste-compression-moulding methods.Metal parts adopts conventional machine-tooled method, utilizes former both ends of the surface as the reference plane of assembling upper and lower end frame, and glueds joint upper and lower end frame after adopting Redux420 adhesion agent, to ensure the accuracy of form and position of its high request.All the other respectively hold frame, stringer to adopt the process of Redux420 adhesive glue one spiral shell Hybrid connections equally, and glued joint frock after design specialized to guarantee the assembly precision of each frame.
Touch the tests such as state, vibration, noise to prove through satellite, grapefruit satellite platform loaded cylinder of the present invention reaches the object that structure is simple, increase damping, reduce response, can realize the carrying of about 1 ton; As long as suitably adjust the laying of covering, just can meet the carrying needs of different loads, thus improve the comformability to load.The honeycomb sandwich construction loaded cylinder of this integration, light-weight design, the quality of production is about 22kg, meets the requirement of system preferably, is significant for satellite structure loss of weight.
Claims (1)
1. a grapefruit satellite platform loaded cylinder, is characterized in that, this loaded cylinder adopts carbon/epoxy covering-aluminium honeycomb sandwich construction to be cylindrical shell, is aided with the array configuration of end frame and stringer;
Wherein said cylindrical shell [2] is post cone one, has shell of column and cone section; Cylindrical shell [2] comprises inside and outside covering and honeycomb core; Inside and outside covering is carbon/epoxy composite material, and reinforcing material is T300-3k carbon fiber, and basis material is epoxy 648/BF3MEA resin matrix; Shell of column panel laying is ± 45 °/0 °/90 °, cone section panel laying is ± 45 °/0 °/
45 °, the porose durability aluminium honeycomb of honeycomb core adopts that material is LF2Y, highly to be 6.5mm, specification be 4-0.04, the J-7890 DEG C of consolidated structures adhesion agent that inside and outside covering and aluminium honeycomb core adopt thickness to be not less than 0.2mm glueds joint;
The embedding glue in upper end of cylindrical shell [2] shell of column has a upper end frame [1], and the embedding glue in bottom of cylindrical shell [2] cone section has a lower end frame [4]; The outer wall of cylindrical shell [2] glueds joint a middle-end frame [3] in the intermediate location of shell of column and cone section, realizes the connection with satellite structure plate; The inwall that the inwall of cylindrical shell [2] shell of column glueds joint has installing frame [6] on a tank, cylindrical shell [2] to bore section glueds joint installing frame [7] under a tank; Described lower end frame [4] adopts LD10CS, and the satellite and the rocket burbling area contacted with Clamp band fixture block adopts colourless anodizing; On described middle-end frame [3], upper end frame [1], tank, under installing frame [6], tank, installing frame [7] is carbon/epoxy composite material, the reinforcing material of carbon/epoxy composite material end frame is T700-12K carbon fiber, and basis material is epoxy 648/BF3MEA resin matrix;
Four shell of column stringers [5] are evenly arranged around the shell of column of cylindrical shell [2], four cones section stringer [8] are evenly arranged around the cone section of cylindrical shell [2], described shell of column stringer [5], cone section stringer [8] realize the connection with satellite structure plate, be carbon/epoxy composite material, reinforcing material is T700-12k carbon fiber, and basis material is epoxy 648/BF3MEA resin matrix;
Described cylindrical shell [2] adopts female mould forming; The preparation of carbon/epoxy composite material covering and the preparation of loaded cylinder cylindrical shell sandwich structure adopt vacuum bag-solidification of hot-press tank forming process; Various carbon/epoxy composite material profiled piece adopts hand paste-compression-moulding methods; Metal parts adopts conventional machine-tooled method; Utilize former both ends of the surface as the reference plane of assembling upper end frame [1], lower end frame [4], and glued joint upper and lower end frame after adopting Redux420 adhesion agent, all the other respectively hold frame, stringer to adopt the technique of Redux420 adhesive glue one spiral shell Hybrid connections equally.
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105122964B true CN105122964B (en) | 2012-07-25 |
Family
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104608915A (en) * | 2015-01-30 | 2015-05-13 | 中国人民解放军国防科学技术大学 | Multilayer grating bearing cylinder and preparation method thereof |
| CN104668804A (en) * | 2013-12-03 | 2015-06-03 | 北京宇航系统工程研究所 | Tank bottom and cylinder section butt joint structure for rocket propellant 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 |
| CN107600460A (en) * | 2017-07-27 | 2018-01-19 | 上海卫星工程研究所 | A kind of cryogenic opticses satellite configuration being applied under the conditions of big oval Frozen Orbit complex illumination |
| CN106915474B (en) * | 2017-01-20 | 2018-12-21 | 北京空间飞行器总体设计部 | A kind of lightweight carbon fiber-reinforced resin composite materials Stiffened Plate and Shell main force support structure |
| CN109703786A (en) * | 2018-12-28 | 2019-05-03 | 上海空间推进研究所 | The main force support structure of liquid rail control dynamical system |
| 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 |
| CN106564618B (en) * | 2016-10-14 | 2020-05-19 | 上海微小卫星工程中心 | Spacecraft pneumatic configuration |
| CN111422377A (en) * | 2020-03-10 | 2020-07-17 | 上海卫星工程研究所 | Structure suitable for satellite and facilitating assembly of double-layer flange type bearing cylinder and laminate |
| CN113459602A (en) * | 2021-07-07 | 2021-10-01 | 北华航天工业学院 | Light corrugated sandwich type composite material bearing cylinder |
| 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 |
| CN114659415A (en) * | 2022-03-01 | 2022-06-24 | 航天科工火箭技术有限公司 | Lightweight cabin section structure of carrier |
| CN111762343B (en) * | 2020-06-09 | 2023-09-08 | 上海宇航系统工程研究所 | Throwable double-component annular storage tank for spacecraft |
Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104668804A (en) * | 2013-12-03 | 2015-06-03 | 北京宇航系统工程研究所 | Tank bottom and cylinder section butt joint structure for rocket propellant tank |
| CN104668804B (en) * | 2013-12-03 | 2017-01-25 | 北京宇航系统工程研究所 | Tank bottom and cylinder section butt joint structure for rocket propellant tank |
| CN104608915A (en) * | 2015-01-30 | 2015-05-13 | 中国人民解放军国防科学技术大学 | Multilayer grating bearing cylinder and preparation method thereof |
| CN106564618B (en) * | 2016-10-14 | 2020-05-19 | 上海微小卫星工程中心 | Spacecraft pneumatic configuration |
| CN106482589A (en) * | 2016-12-13 | 2017-03-08 | 中国运载火箭技术研究院 | A kind of stringer housing |
| CN106915474B (en) * | 2017-01-20 | 2018-12-21 | 北京空间飞行器总体设计部 | A kind of lightweight carbon fiber-reinforced resin composite materials Stiffened Plate and Shell main force support structure |
| CN107600460A (en) * | 2017-07-27 | 2018-01-19 | 上海卫星工程研究所 | A kind of cryogenic opticses satellite configuration being applied under the conditions of big oval Frozen Orbit complex illumination |
| CN109703786A (en) * | 2018-12-28 | 2019-05-03 | 上海空间推进研究所 | The main force support structure of liquid rail control dynamical system |
| CN109703786B (en) * | 2018-12-28 | 2021-02-09 | 上海空间推进研究所 | Main bearing structure of liquid attitude and orbit control power system |
| 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 |
| CN111422377A (en) * | 2020-03-10 | 2020-07-17 | 上海卫星工程研究所 | Structure suitable for satellite and facilitating assembly of double-layer flange type bearing cylinder and laminate |
| CN111422377B (en) * | 2020-03-10 | 2021-10-15 | 上海卫星工程研究所 | Structure suitable for satellite and facilitating assembly of double-layer flange type bearing cylinder and laminate |
| CN111762343B (en) * | 2020-06-09 | 2023-09-08 | 上海宇航系统工程研究所 | Throwable double-component annular storage tank for spacecraft |
| CN113459602A (en) * | 2021-07-07 | 2021-10-01 | 北华航天工业学院 | Light corrugated sandwich type composite material bearing cylinder |
| CN113459602B (en) * | 2021-07-07 | 2022-08-02 | 北华航天工业学院 | Light corrugated sandwich type composite material bearing cylinder |
| 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 |
| CN114659415A (en) * | 2022-03-01 | 2022-06-24 | 航天科工火箭技术有限公司 | Lightweight cabin section structure of carrier |
| CN114659415B (en) * | 2022-03-01 | 2024-02-09 | 航天科工火箭技术有限公司 | Light cabin section structure of carrier |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR03 | Grant of secret patent right | ||
| DC01 | Secret patent status has been lifted | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20120725 |