CN107738760A - Suitable for six points of even distribution type support meanss of Large-scale satellite platform structure - Google Patents
Suitable for six points of even distribution type support meanss of Large-scale satellite platform structure Download PDFInfo
- Publication number
- CN107738760A CN107738760A CN201710852788.2A CN201710852788A CN107738760A CN 107738760 A CN107738760 A CN 107738760A CN 201710852788 A CN201710852788 A CN 201710852788A CN 107738760 A CN107738760 A CN 107738760A
- Authority
- CN
- China
- Prior art keywords
- bulkhead
- points
- type support
- even distribution
- support meanss
- 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.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
Abstract
The invention discloses a kind of six points of even distribution type support meanss suitable for Large-scale satellite platform structure, it includes withstanding forces cylinder, upper bulkhead, lower bulkhead, bottom plate, connector, laminate, endurance cylinder, six lower bulkheads are all connected with bottom plate, six lower bulkheads are connected with endurance cylinder, endurance cylinder is connected with six upper bulkheads, upper bulkhead is connected by connector with lower bulkhead, and connector is connected with laminate.The present invention can use six upper bulkheads and six lower bulkhead even circumferential distributions, and the requirement in big bearing capacity and unit mounting arrangement space can be met by Optimal Structure Designing and using M55J materials, realizes the lightweight requirements of satellite structure again.
Description
Technical field
It is uniform more particularly to a kind of six points suitable for Large-scale satellite platform structure the present invention relates to a kind of supporting construction
Formula support meanss.
Background technology
Large-scale satellite platform structure mainly uses the configuration of Bearing cylinder formula.Generally, Bearing cylinder formula configuration is general
Using the combining structure of loaded cylinder and boxboard typed.This kind of structure can preferably realize big bearing capacity and provide effective unit cloth
Office space, but because boxboard typed structure loss of weight space is small, it is difficult to further realize the light-weight design of structure.
Therefore, for the satellite of big bearing capacity, design is a kind of to form combining structure with loaded cylinder, unit installing plate
Lightweight framework, while realization is without the emphasis and difficult point that cut-off unit installing space is current Large-scale satellite Platform Structure Design.
The content of the invention
The technical problems to be solved by the invention are to provide a kind of six points of even distribution types suitable for Large-scale satellite platform structure
Support meanss, it can use six upper bulkheads and six lower bulkhead even circumferential distributions, pass through Optimal Structure Designing and use
M55J materials can meet the requirement in big bearing capacity and unit mounting arrangement space, realize that the lightweight of satellite structure will again
Ask.
The present invention is that solve above-mentioned technical problem by following technical proposals：One kind is applied to Large-scale satellite platform knot
Six points of even distribution type support meanss of structure, it includes withstanding forces cylinder, upper bulkhead, lower bulkhead, bottom plate, connector, laminate, endurance
Cylinder, six lower bulkheads are all connected with bottom plate, and six lower bulkheads are connected with endurance cylinder, and endurance cylinder is connected with six upper bulkheads,
Upper bulkhead is connected by connector with lower bulkhead, and connector is connected with laminate.
Preferably, the upper bulkhead connects circumferentially shape with lower bulkhead and is evenly distributed on stress cylinder, and angle is 60 °.
Preferably, the upper bulkhead, the material of lower bulkhead all use M55J materials.
Preferably, the upper bulkhead, the sectional dimension of lower bulkhead are 40 × 40mm, the wall thickness 1mm of upper bulkhead, lower bulkhead
Wall thickness 1.2mm.
Preferably, the upper bulkhead, lower bulkhead are all built-up by the way of rod member and angle rubber alloy connect.
Preferably, the shape of the upper bulkhead is divided into the upper bulkhead of meter word bulkhead and Fei meter word bulkheads, wherein rice word bulkhead
Lower end outside brace be detachable brace.
Preferably, the lower end of the upper bulkhead does not have crossbeam.
Preferably, the material of the connector uses T700S-12K materials.
Compared with prior art, the present invention has following beneficial effect：The present invention is applied to the six of satellite platform structure
Divide even distribution type support frame to be played a supporting role using about six bulkhead uniform circular formulas distributions, coordinate satellite primary load bearing cylinder real
Show big bearing capacity of the satellite platform structure to payload, unit etc., while the layout that Large Copacity does not separate is provided as far as possible
Space.The present invention realizes the carrying to large-scale payload, and provides spaceborne unit the sufficient arrangement space without cut-off, together
When can also meet structure lightened requirement, meet the multi-functional demand of Large-scale satellite platform.
Brief description of the drawings
Fig. 1 is the structural representation of the present invention.
Embodiment
Present pre-ferred embodiments are provided below in conjunction with the accompanying drawings, to describe technical scheme in detail.
As shown in figure 1, six points of even distribution type support meanss that the present invention is applied to Large-scale satellite platform structure include endurance
Cylinder 10, upper bulkhead 11, lower bulkhead 12, bottom plate 13, connector 14, laminate 15, endurance cylinder 10, six lower bulkheads 12 all with bottom plate
13 are connected, and six lower bulkheads 12 are connected with endurance cylinder 10, and endurance cylinder 10 is connected with six upper bulkheads 11, and upper bulkhead 11 passes through
Connector 14 is connected with lower bulkhead 12, and connector 14 is connected with laminate 15.
The upper bulkhead 11 and lower bulkhead 12 connect circumferentially shape and are evenly distributed on stress cylinder 10, and angle is 60 °, so
It is simple in construction.
The upper bulkhead 11, the material of lower bulkhead 12 all use M55J materials, so improve bearing capacity, also real on material
The lightweight requirements of satellite are showed.
The upper bulkhead 11, the sectional dimension of lower bulkhead 12 are 40 × 40mm (millimeter), the wall thickness 1mm of upper bulkhead 11,
It the wall thickness 1.2mm of lower bulkhead 12, can so increase the stability of structure, realize the strength and stiffness design of integration.
The upper bulkhead 11, lower bulkhead 12 built-up, such convenient use all by the way of rod member and angle rubber alloy connect.
The shape of the upper bulkhead 11 is divided into the lower end of meter word bulkhead and Fei meter word bulkheads, the wherein upper bulkhead of rice word bulkhead
Outside brace is detachable brace, and such convenient use, installation and precision adjustment for bulkhead provide facility.
The lower end of the upper bulkhead 11 does not have crossbeam, and be achieved in that makes its layout unrestricted unit installation without cut-off
Large Copacity space.
The material of the connector 14 uses T700S-12K materials, can so mitigate weight.
Particular embodiments described above, technical problem, technical scheme and the beneficial effect of the solution to the present invention are carried out
It is further described, should be understood that the specific embodiment that the foregoing is only of the invention, be not limited to
The present invention, within the spirit and principles of the invention, any modification, equivalent substitution and improvements done etc., it should be included in this
Within the protection domain of invention.
Claims (8)
1. a kind of six points of even distribution type support meanss suitable for Large-scale satellite platform structure, it is characterised in that it includes endurance
Cylinder, upper bulkhead, lower bulkhead, bottom plate, connector, laminate, endurance cylinder, six lower bulkheads are all connected with bottom plate, six lower bulkheads
Be connected with endurance cylinder, endurance cylinder is connected with six upper bulkheads, and upper bulkhead is connected by connector with lower bulkhead, connector and
Laminate is connected.
2. it is applied to six points of even distribution type support meanss of Large-scale satellite platform structure as claimed in claim 1, it is characterised in that
The upper bulkhead connects circumferentially shape with lower bulkhead and is evenly distributed on stress cylinder, and angle is 60 °.
3. it is applied to six points of even distribution type support meanss of Large-scale satellite platform structure as claimed in claim 1, it is characterised in that
The upper bulkhead, the material of lower bulkhead all use M55J materials.
4. it is applied to six points of even distribution type support meanss of Large-scale satellite platform structure as claimed in claim 1, it is characterised in that
The upper bulkhead, the sectional dimension of lower bulkhead are 40 × 40mm, the wall thickness 1mm of upper bulkhead, the wall thickness 1.2mm of lower bulkhead.
5. it is applied to six points of even distribution type support meanss of Large-scale satellite platform structure as claimed in claim 1, it is characterised in that
The upper bulkhead, lower bulkhead are all built-up by the way of rod member and angle rubber alloy connect.
6. it is applied to six points of even distribution type support meanss of Large-scale satellite platform structure as claimed in claim 1, it is characterised in that
The shape of the upper bulkhead is divided into meter word bulkhead and Fei meter word bulkheads, and the lower end outside brace of the wherein upper bulkhead of rice word bulkhead is
Detachable brace.
7. it is applied to six points of even distribution type support meanss of Large-scale satellite platform structure as claimed in claim 1, it is characterised in that
The lower end of the upper bulkhead does not have crossbeam.
8. it is applied to six points of even distribution type support meanss of Large-scale satellite platform structure as claimed in claim 1, it is characterised in that
The material of the connector uses T700S-12K materials.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710852788.2A CN107738760A (en) | 2017-09-19 | 2017-09-19 | Suitable for six points of even distribution type support meanss of Large-scale satellite platform structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710852788.2A CN107738760A (en) | 2017-09-19 | 2017-09-19 | Suitable for six points of even distribution type support meanss of Large-scale satellite platform structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107738760A true CN107738760A (en) | 2018-02-27 |
Family
ID=61236054
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710852788.2A Pending CN107738760A (en) | 2017-09-19 | 2017-09-19 | Suitable for six points of even distribution type support meanss of Large-scale satellite platform structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107738760A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109050977A (en) * | 2018-07-02 | 2018-12-21 | 上海卫星工程研究所 | A kind of high rail satellite assembly method based on double elements unified propulsion system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6206327B1 (en) * | 1999-03-31 | 2001-03-27 | Lockheed Martin Corporation | Modular spacecraft bus |
| CN104260901A (en) * | 2014-09-11 | 2015-01-07 | 上海卫星工程研究所 | Modular two-component propulsion system |
| CN106688320B (en) * | 2013-02-05 | 2015-09-02 | 上海卫星工程研究所 | Framework primary load bearing satellite structure |
| CN107264839A (en) * | 2017-05-18 | 2017-10-20 | 上海卫星工程研究所 | Satellite booster pipe-line layout method |
-
2017
- 2017-09-19 CN CN201710852788.2A patent/CN107738760A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6206327B1 (en) * | 1999-03-31 | 2001-03-27 | Lockheed Martin Corporation | Modular spacecraft bus |
| CN106688320B (en) * | 2013-02-05 | 2015-09-02 | 上海卫星工程研究所 | Framework primary load bearing satellite structure |
| CN104260901A (en) * | 2014-09-11 | 2015-01-07 | 上海卫星工程研究所 | Modular two-component propulsion system |
| CN107264839A (en) * | 2017-05-18 | 2017-10-20 | 上海卫星工程研究所 | Satellite booster pipe-line layout method |
Non-Patent Citations (1)
| Title |
|---|
| 张铁亮: "卫星夹层结构分析与结构设计研究", 《南京航空航天大学博士学位论文》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109050977A (en) * | 2018-07-02 | 2018-12-21 | 上海卫星工程研究所 | A kind of high rail satellite assembly method based on double elements unified propulsion system |
| CN109050977B (en) * | 2018-07-02 | 2020-07-14 | 上海卫星工程研究所 | High-orbit satellite final assembly method based on double-component unified propulsion system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101381003A (en) | Main load-carrying structure of spacecraft | |
| CN205906208U (en) | Aircraft main landing gear supported joint structure | |
| CN105667836A (en) | Satellite strut structure | |
| CN102359779B (en) | High stability multi-angle and multi-freedom satellite releasing and bearing apparatus of space remote sensing camera | |
| CN107738760A (en) | Suitable for six points of even distribution type support meanss of Large-scale satellite platform structure | |
| CN102897329A (en) | Storage box installation structure applicable to trussed platform | |
| CN103192882B (en) | Framework type frame structure and concrete pump truck | |
| CN107757950A (en) | A kind of high rail Optical remote satellite structure | |
| CN207328850U (en) | A kind of aircraft photoelectric nacelle hanging structure | |
| FR2921898B1 (en) | FUSELAGE STRUCTURE FOR AIRCRAFT FUSELAGE IN COMPOSITE MATERIAL AND AIRCRAFT EQUIPPED WITH SUCH A FUSELAGE STRUCTURE | |
| CN104832786B (en) | Helium tank support | |
| CN206926839U (en) | A kind of instrument cabin structure of vehicle | |
| CN207985150U (en) | A kind of spitkit repair support device | |
| CN207739570U (en) | Reinforced Anti-electrostatic floor keel | |
| CN203473239U (en) | Mounting base for main landing gear of TB20 airplane | |
| CN206243513U (en) | Encircling type is adjustable install pointing accuracy sensor damping frame | |
| CN210028382U (en) | Protection mechanism for inspection unmanned aerial vehicle | |
| CN205203346U (en) | Close section baggage compartment bearing structure | |
| CN207984536U (en) | Supporting beam assembly and automobile | |
| CN204287474U (en) | A kind of Portable detachable omnidirectional radar target | |
| CN203793608U (en) | Supporting device for electronic speed regulators of agricultural unmanned aerial vehicle | |
| CN204979260U (en) | Helicopter carries equipment rack | |
| CN207588594U (en) | A kind of lightweight assembling motor housing | |
| CN202702246U (en) | Robot visual support system | |
| CN110395408A (en) | A kind of interface structure of grid type load-carrying construction |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180227 |
|
| RJ01 | Rejection of invention patent application after publication |