CN106564620A - Satellite shell plate and satellite shell - Google Patents
Satellite shell plate and satellite shell Download PDFInfo
- Publication number
- CN106564620A CN106564620A CN201611001253.6A CN201611001253A CN106564620A CN 106564620 A CN106564620 A CN 106564620A CN 201611001253 A CN201611001253 A CN 201611001253A CN 106564620 A CN106564620 A CN 106564620A
- Authority
- CN
- China
- Prior art keywords
- satellite shell
- satellite
- shell plate
- module
- shell
- 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.)
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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
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Cooling Or The Like Of Electrical Apparatus (AREA)
- Casings For Electric Apparatus (AREA)
Abstract
The invention relates to a satellite shell plate. The satellite shell plate is composed of two layers of interfaces and an electronic motherboard which is placed between the two layers of interfaces. The electronic motherboard is a printed circuit board. The satellite shell plate is provided with inserting grooves which divide the satellite shell plate into areas. An electromechanical interface is installed in each area and is electrically connected with the printed circuit board. The satellite shell plate is used for assembling unit modules, then the unit modules are used for assembling a satellite shell, and the manufacturing work of the satellite shell can be simplified.
Description
Technical field
The present invention relates to a kind of satellite shell plate.
The invention further relates to the satellite shell being made up of satellite shell plate.
Background technology
Satellite shell as satellite structure part, for providing installation pedestal for load on all of star.Load is being defended on star
Mounting structure in star is showed by satellite shell.Once load mounting structure in the satel-lite is determined on star, satellite
Housing construction is also correspondingly determined.Satellite shell Jing often has unique construction.This satellite shell is unique because of its construction, past
It is past to be not easy manufacture.Meanwhile, this satellite shell is completed once manufacturing, and spatially extends satellite shell to carry newly-increased load
It is impossible.But, due to launch a satellite cost it is high, it is always desirable to complete as much as possible on a satellite
Experimental duties.Accordingly, it would be desirable to new satellite shell is meeting this demand of user.
The content of the invention
In order to neatly spatially extend satellite shell, the invention provides a kind of satellite shell plate, by two-layer
Interface and electronics motherboard are constituted.The electronics motherboard is as between two bed boundarys.The satellite shell plate is provided with slot, described
The satellite shell plate is divided into region by slot.One electromechanical interface is respectively installed in the region.The electromechanical interface and institute
State the electrical connection of electronics motherboard.
Preferably, the satellite shell plate, its length × a width of 30cm × 30cm.
Preferably, the slot is " well " font.
Preferably, the interface is by made by carbon fibre material.
Preferably, the electronics motherboard is printed circuit board (PCB).
A kind of satellite shell, by least one module composition.The module is cube shaped, and the cube includes at least 1
Satellite shell plate described in block, in the slot fin is provided with.
Preferably, the module is 2, extends the sky of the satellite shell between the module by connector fixation
Between.
Preferably, the module is 3, extends the sky of the satellite shell between the module by connector fixation
Between.
Preferably, the module is 4, extends the sky of the satellite shell between the module by connector fixation
Between.
It is an advantage of the current invention that satellite shell plate is used as satellite shell structural member, can be cancelled by neatly assembling and disassembling
To the operation welded on satellite shell.With the change of load mounting structure in the satel-lite on star, using satellite shell
The satellite shell of plate assembling also can be changed accordingly.The manufacture of this satellite shell disclosure satisfy that Parallel Design manufacturing activities.
This is that conventional satellite housing design manufacturing activities are unapproachable.Even if satellite shell is completed, need to extend satellite shell
To carry, newly-increased load is also very easy to be implemented in space.
Description of the drawings
Fig. 1 is a kind of satellite shell plate schematic diagram that the specific embodiment of the invention is provided.
Fig. 2 is the satellite shell plate sectional layer schematic diagram that the specific embodiment of the invention is provided.
Fig. 3 is a kind of satellite shell plate schematic diagram that the specific embodiment of the invention is provided.
Fig. 4 is a kind of satellite shell schematic diagram that the specific embodiment of the invention is provided.
Fig. 5 is a kind of satellite shell schematic diagram that the specific embodiment of the invention is provided.
Specific embodiment
The specific embodiment that the present invention is provided is elaborated below in conjunction with the accompanying drawings.
A kind of satellite shell plate schematic diagram and Fig. 2 present invention provided such as Fig. 1 specific embodiment of the invention is embodied as
Shown in the satellite shell plate sectional layer schematic diagram that mode is provided, a kind of satellite shell plate 1, by the first bed boundary 11, electronics motherboard
13 and second bed boundary 13 constitute.Electronics motherboard 13 is as between the first bed boundary 11 and the second bed boundary 13.Electronics motherboard 13
It is by made by printed circuit board (PCB).First bed boundary 11 and the second bed boundary 13 are by made by carbon fiber.On satellite shell plate 1
Slot 2 is provided with, 1 point by satellite shell plate of slot 2 is region.One electromechanical interface 3 is respectively installed in each region.Electromechanical interface
3 electrically connect with printed circuit board (PCB) 12.Electronics motherboard 12 is placed between the first bed boundary 11 and the second bed boundary 13 with to electronics
Motherboard is protected.Electronics motherboard 12 is encapsulated in its appearance as electronic product using the first bed boundary 11 and the second bed boundary 13
It is prevented from electronic main plate line short.On the other hand, using the first bed boundary 11 and the encapsulation of the second bed boundary 13 electronics motherboard
After 12, on the first bed boundary 11 and the second bed boundary 13 slot 2 can be opened up.It can be assembling satellite shell plate to open up slot 2
Support member is provided or radiating piece is provided to conduct satellite load heat.After electronics motherboard 12 is connected with each electromechanical interface 3, each machine
Connection when electrical interface is distributed on the first bed boundary 11 or the second bed boundary 13 in order to use.For the ease of connection, electricity
Mother baby plate circuit adopts array circuit, and each element circuit is distributed in a region, each region and the first bed boundary 11
Or second the region that separated by slot 2 of bed boundary 13 it is corresponding.
It is a kind of mode to output slot 2 according to " well " font on the first bed boundary 11 and the second bed boundary 13.In order to make
Micro-nano satellite is made, formula is originally embodied as and is selected length × a width of 30cm × 30cm satellite shells plate.This shell plates is micro- for assembling
Nano satellite housing is particularly suitable.
As shown in a kind of satellite shell plate schematic diagram that Fig. 3 specific embodiment of the invention is provided, a kind of satellite shell plate
1, it is made up of the first bed boundary 11, the bed boundary 13 of electronics motherboard 13 and second.Electronics motherboard 13 is as the first bed boundary 11 and
Between two bed boundarys 13.Satellite shell plate 1 is provided with slot 2, and 1 point by satellite shell plate of slot 2 is region.All of slot 2
" well " font is formed on satellite shell plate 1.In order that satellite shell plate 1 adapts to install satellite load, using slot closed plate 4
Some slots 2 and electromechanical interface 3 are covered, so as to obtain adapting to the satellite shell plate 1 that satellite load is installed.This housing
After some slots 2 and electromechanical interface 3 are covered using closed plate 4, closed plate 4 links together plate 1 with star shell plates 1 so that
Load with linked together by smooth closed plate 4 and satellite shell plate 1, to increase the connection of satellite shell plate 1 and load
Area.So load will increase with the tie point of satellite shell plate 1.
The satellite shell module of Unit one can be assembled into using at least 1 block above-mentioned satellite shell plate.By this list
First satellite shell module assembled is into satellite shell.This satellite shell is by least one satellite shell module composition.Satellite shell mould
Block is cube shaped, and fin is provided with slot.
As shown in a kind of satellite shell schematic diagram that Fig. 4 specific embodiment of the invention is provided, this satellite shell is by 4
Satellite shell module composition.Satellite shell module extends satellite shell space according to short transverse superposition.Each satellite shell mould
Connected by connector between block.It is in cube shaped load that this satellite shell is applied to carrying overall.
Certainly by 2 or 3 satellite shell modules, and the space of the satellite shell is extended by connector fixation
It is also possible.This extension extends according to the volume of load.
As shown in a kind of satellite shell schematic diagram that Fig. 5 specific embodiment of the invention is provided, a kind of satellite shell is illustrated
Shown in figure, this satellite shell is by 4 satellite shell module compositions.Satellite shell module extends according to length direction superposition to be defended
Star shell space.Connected by connector between each satellite shell module.It is in prolate that this satellite shell is applied to carrying overall
The load of shape.
With the change of satellite load shape, satellite shell can be assembled expansion.Using this satellite shell plate and defending
Star housing changes conventional satellite and manufactures and designs operation, makes satellite load design no longer by being limited to satellite shell shape；Make
The installation of satellite load is no longer influenced by the restriction of satellite shell shape, and its installation steps is flexible.
The above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
Member, under the premise without departing from the principles of the invention, can also make some improvements and modifications, and these improvements and modifications also should be regarded as
Protection scope of the present invention.
Claims (9)
1. a kind of satellite shell plate, it is characterised in that be made up of two bed boundarys and electronics motherboard, the electronics motherboard is as two-layer
Between interface；The satellite shell plate is provided with slot, and the satellite shell plate is divided into region by the slot；In the region
One electromechanical interface is respectively installed；The electromechanical interface is electrically connected with the electronics motherboard.
2. satellite shell plate according to claim 1, it is characterised in that its length × a width of 30cm × 30cm.
3. satellite shell plate according to claim 2, it is characterised in that the slot is " well " font.
4. satellite shell plate according to claim 3, it is characterised in that the interface is by made by carbon fibre material.
5. satellite shell plate according to claim 1, it is characterised in that the electronics motherboard is printed circuit board (PCB).
6. a kind of satellite shell, it is characterised in that by least one module composition, the module is cube shaped, the module bag
At least 1 satellite shell plate as described in any one of claim 1 to 5 is included, fin is installed in the slot.
7. satellite shell according to claim 6, it is characterised in that the module is 2, by connection between the module
Part is fixed to extend the space of the satellite shell.
8. satellite shell according to claim 6, it is characterised in that the module is 3, by connection between the module
Part is fixed to extend the space of the satellite shell.
9. satellite shell according to claim 6, it is characterised in that the module is 4, by connection between the module
Part is fixed to extend the space of the satellite shell.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611001253.6A CN106564620B (en) | 2016-11-14 | 2016-11-14 | Satellite shell plate and satellite shell |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611001253.6A CN106564620B (en) | 2016-11-14 | 2016-11-14 | Satellite shell plate and satellite shell |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106564620A true CN106564620A (en) | 2017-04-19 |
| CN106564620B CN106564620B (en) | 2019-03-29 |
Family
ID=58542764
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611001253.6A Active CN106564620B (en) | 2016-11-14 | 2016-11-14 | Satellite shell plate and satellite shell |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106564620B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110217409A (en) * | 2019-05-30 | 2019-09-10 | 北京卫星制造厂有限公司 | In-orbit fast assembling-disassembling micro-nano satellite platform structure |
| CN111409878A (en) * | 2020-03-19 | 2020-07-14 | 上海卫星工程研究所 | Open type assembled module platform cabin structure |
| CN111762338A (en) * | 2020-05-25 | 2020-10-13 | 航天科工空间工程发展有限公司 | Folding flat satellite structure |
| CN113022888A (en) * | 2021-05-28 | 2021-06-25 | 北京最终前沿深空科技有限公司 | Satellite structure and satellite assembly method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201115118Y (en) * | 2007-07-19 | 2008-09-10 | 上海航天局第八○九研究所 | Satellite electronic system standalone device |
| CN103612775A (en) * | 2013-11-20 | 2014-03-05 | 西北工业大学 | Multifunctional load-bearing structure for miniature satellites |
| JP2014076757A (en) * | 2012-10-11 | 2014-05-01 | Next Generation Space System Technology Research Association | Artificial satellite body structure |
| CN105905316A (en) * | 2016-05-10 | 2016-08-31 | 中国人民解放军国防科学技术大学 | Multi-functional bulkhead structure for microsatellite system |
| CN105923171A (en) * | 2016-05-19 | 2016-09-07 | 中国空间技术研究院 | Modular integrated satellite multifunctional structure and polymers |
| CN105947235A (en) * | 2016-05-10 | 2016-09-21 | 国防科学技术大学 | Electric energy and mechanical environment management multifunctional structure |
-
2016
- 2016-11-14 CN CN201611001253.6A patent/CN106564620B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201115118Y (en) * | 2007-07-19 | 2008-09-10 | 上海航天局第八○九研究所 | Satellite electronic system standalone device |
| JP2014076757A (en) * | 2012-10-11 | 2014-05-01 | Next Generation Space System Technology Research Association | Artificial satellite body structure |
| CN103612775A (en) * | 2013-11-20 | 2014-03-05 | 西北工业大学 | Multifunctional load-bearing structure for miniature satellites |
| CN105905316A (en) * | 2016-05-10 | 2016-08-31 | 中国人民解放军国防科学技术大学 | Multi-functional bulkhead structure for microsatellite system |
| CN105947235A (en) * | 2016-05-10 | 2016-09-21 | 国防科学技术大学 | Electric energy and mechanical environment management multifunctional structure |
| CN105923171A (en) * | 2016-05-19 | 2016-09-07 | 中国空间技术研究院 | Modular integrated satellite multifunctional structure and polymers |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110217409A (en) * | 2019-05-30 | 2019-09-10 | 北京卫星制造厂有限公司 | In-orbit fast assembling-disassembling micro-nano satellite platform structure |
| CN110217409B (en) * | 2019-05-30 | 2020-10-23 | 北京卫星制造厂有限公司 | On-orbit quick dismounting micro-nano satellite platform structure |
| CN111409878A (en) * | 2020-03-19 | 2020-07-14 | 上海卫星工程研究所 | Open type assembled module platform cabin structure |
| CN111409878B (en) * | 2020-03-19 | 2021-08-24 | 上海卫星工程研究所 | Open type assembled module platform cabin structure |
| CN111762338A (en) * | 2020-05-25 | 2020-10-13 | 航天科工空间工程发展有限公司 | Folding flat satellite structure |
| CN113022888A (en) * | 2021-05-28 | 2021-06-25 | 北京最终前沿深空科技有限公司 | Satellite structure and satellite assembly method |
| CN113022888B (en) * | 2021-05-28 | 2021-08-10 | 北京最终前沿深空科技有限公司 | Satellite structure and satellite assembly method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106564620B (en) | 2019-03-29 |
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| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20170817 Address after: 200050 Changning Road, Shanghai, No. 865, No. Applicant after: Shanghai Institute of Microsystem and Information Technology, Chinese Academy of Sciences Applicant after: Shanghai Engineering Center for Microsatellites Applicant after: University of Chinese Academy of Sciences Address before: 201203 Shanghai city Pudong New Area Hartcourt Road No. 99 Applicant before: Shanghai Engineering Center for Microsatellites |
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| TA01 | Transfer of patent application right | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |