CN108502208A - A kind of spacecraft cellular board - Google Patents
A kind of spacecraft cellular board Download PDFInfo
- Publication number
- CN108502208A CN108502208A CN201810265381.4A CN201810265381A CN108502208A CN 108502208 A CN108502208 A CN 108502208A CN 201810265381 A CN201810265381 A CN 201810265381A CN 108502208 A CN108502208 A CN 108502208A
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- CN
- China
- Prior art keywords
- cellular board
- frame
- girder construction
- carbon fibre
- shaped girder
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- 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)
- Laminated Bodies (AREA)
Abstract
The present invention designs a kind of spacecraft cellular board, which includes：Covering, honeycomb core and fastener inserts, fastener inserts are glued with honeycomb core, and honeycomb core is glued with covering, and fastener inserts include：Integral carbon fibre frame and metal embedded part, metal embedded part are glued in integral carbon fibre lower portion.Integral carbon fibre frame includes：First U-shaped girder construction and the second U-shaped girder construction, the first U-shaped girder construction and the second U-shaped girder construction opening direction are opposite.Metal embedded part is glued in the first U-shaped girder construction of integral carbon fibre frame and/or the opening of the second U-shaped girder construction.Integral carbon fibre frame is the frame of the integrated molding by way of carbon fiber laying and/or winding.The cellular board have many advantages, such as can multi-angle support, light-weight, compact-sized, processing adjustment good manufacturability, stability is high, bearing capacity is strong, mechanical environment adaptability is good.
Description
Technical field
The present invention relates to AEROSPACE APPLICATION technical fields, and in particular to a kind of spacecraft cellular board.
Background technology
In spacecraft structure, it will usually be glued the cellular board formed as space flight by covering and honeycomb core using a kind of
Support construction in device design.It is carried since it improves spacecraft structure rigidity, reduces spacecraft structure quality and improves spacecraft
The characteristic of deformation accuracy, cellular board are widely used caused by the in-orbit hot alternation environment of lotus.
With the development of space technology, the load that cellular board is subjected to also increasingly increases, generally for raising cellular board
Built-in fitting can be arranged in the load that can bear in cellular board.The cellular board built-in fitting is as the interconnecting piece in Spacecraft guidance and control
Part is primarily subjected to pulling-out force and shearing force, while extraneous load is transmitted also by built-in fitting and is distributed in entire honeycomb.
Therefore, the structure type of built-in fitting directly influences reliability and the fatigue life of cellular board.
Currently, metal embedded part is often selected for the structure design of the cellular board containing built-in fitting, and it is directly pre-buried
In cellular board.Since the material property difference of covering and metal embedded part is larger, rigidity can discontinuously cause for such design
There is more serious stress concentration with covering interface location in metal embedded part, thus reduces the bearing capacity of entire cellular board.
Therefore, it is necessary to develop a kind of spacecraft to be solved the above problems with cellular board.
Invention content
To make up the deficiencies in the prior art, the application provides a kind of spacecraft cellular board, which has can be polygonal
Degree support, light-weight, compact-sized, processing adjustment good manufacturability, stability is high, bearing capacity is strong, mechanical environment adaptability is good
The advantages that.
The application on the one hand be to provide a kind of spacecraft cellular board, which includes：Covering, honeycomb core and pre-
Embedded component, fastener inserts are glued with honeycomb core, and honeycomb core is glued with covering, and fastener inserts include：Integral carbon fibre frame
Frame and metal embedded part, metal embedded part are glued in integral carbon fibre lower portion.
In some embodiments, integral carbon fibre frame includes：First U-shaped girder construction and the second U-shaped girder construction, first
U-shaped girder construction and the second U-shaped girder construction opening direction are opposite.
In some embodiments, metal embedded part is glued the first U-shaped girder construction in integral carbon fibre frame and/or the
In the opening of two U-shaped girder constructions.
In some embodiments, integral carbon fibre frame is integrated by way of carbon fiber laying and/or winding
Molding frame.
In some embodiments, the carbon fiber layer thickness of integral carbon fibre frame is 2mm.
In some embodiments, metal embedded part further comprises that load installs interface
In some embodiments, metal embedded part further comprises lightening hole.
In some embodiments, covering is carbon fibre composite laminate.
In some embodiments, honeycomb core is aluminum alloy honeycomb fuse.
In some embodiments, cellular board is satellite optical datum plate.
Description of the drawings
Presently filed embodiment is described in conjunction with the accompanying drawings, the application may be better understood, in attached drawing
In：
Fig. 1 is the front signal of the fastener inserts in a kind of spacecraft cellular board in one embodiment of the application
Figure；And
Fig. 2 is the schematic rear view of the fastener inserts in a kind of spacecraft cellular board shown in Fig. 1.
Drawing reference numeral explanation：
100：Fastener inserts；
101：Integral carbon fibre frame；
110:Frame metal built-in fitting；
111：First metal embedded part；
112：Second metal embedded part；
113：Third metal embedded part；
121：First load construction opening；
122：Second load construction opening；
123：Third load construction opening.
Specific implementation mode
Unless otherwise defined, the technical term or scientific terminology used in the present specification and claims is should be
The ordinary meaning that the personage with general technical ability is understood in the technical field of the invention.That enumerates herein is all from most
Low value to the numerical value between peak, refer to when between minimum and peak differ two units more than when, minimum with most
All numerical value obtained as increment using a unit between high level.
The specific implementation mode of the present invention explained below, it should be pointed out that in the specific descriptions of these embodiments
In the process, in order to carry out brief and concise description, this specification can not possibly make in detail all features of actual embodiment
Most description.
One embodiment of the application is related to a kind of spacecraft cellular board.The cellular board can pass through fastener and space flight
Device frame connects, and the fastener, which can be that screw, glued membrane, buckle etc. are any, closely to connect cellular board and spacecraft frame
The device or structure connect.In some embodiments, cellular board is satellite optical datum plate.
Cellular board includes：Covering, honeycomb core and fastener inserts 100.Fig. 1 is the exemplary embodiment of fastener inserts 100
Front schematic view, Fig. 2 be fastener inserts 100 exemplary embodiment schematic rear view.Fastener inserts 100 are located at cellular board
Inside, and with honeycomb core be glued.Honeycomb core is glued with covering.In some embodiments, covering is carbon fiber composite
Bed of material plywood.In further embodiments, honeycomb core can be aluminum alloy honeycomb fuse or aramid fiber paper material.It is specific at one
Embodiment in, fastener inserts 100 are located at by pre-buried form inside cellular board, multiple with aluminum alloy honeycomb fuse and carbon fiber
Condensation material laminate collectively constitutes carbon fiber skin/aluminium honeycomb core minor structure, and entire cellular board passes through screw and spacecraft frame
Connection.
In the embodiment of fastener inserts 100 as shown in Figures 1 and 2, fastener inserts 100 further comprise：Integration
Carbon fiber frame 101 and metal embedded part 110,111,112,113.Metal embedded part 110,111,112,113 is glued in one
Change inside carbon fiber frame 101.In some embodiments, 101 coefficient of thermal expansion of integral carbon fibre frame is small, and stability is high,
It is transferred on entire cellular board and spacecraft frame for bearing extraneous load, and by extraneous load, and the metal of single-point arrangement
Built-in fitting 110,111,112,113 is used to carry out local strengthening to integral carbon fibre frame 101.
In some embodiments, integral carbon fibre frame 101 uses the U-shaped girder construction of thin-walled.Specifically, integrated
Carbon fiber frame 101 includes：First U-shaped girder construction and the second U-shaped girder construction, the first U-shaped girder construction and the second U-shaped girder construction are opened
Mouth direction is opposite.The design method of such combination opening direction opposite the first U-shaped girder construction and the second U-shaped girder construction, can make
Integral carbon fibre frame 101 can bear Tensile or Compressive Loading simultaneously, improve the stability of integral carbon fibre frame 101.At some
In embodiment, metal embedded part 110,111,112,113 can be glued the first U-shaped beam knot in integral carbon fibre frame 101
In the opening of structure and/or the second U-shaped girder construction.
In some embodiments, when load installation interface is located at honeycomb back, integral carbon fibre frame 101 is taken
The first opening up U-shaped girder construction, meanwhile, metal embedded part 110,111,112,113 is positioned over integral carbon fibre frame
In the opening of first U-shaped beam of frame 101, and it is connected with integral carbon fibre frame 101 by way of splicing；When load is installed
When interface is located at cellular board front, integral carbon fibre frame 101 takes the downward opening second U-shaped girder construction, meanwhile, it will be golden
Belong to built-in fitting 110,111,112,113 to be positioned in the opening of the second U-shaped beam of integral carbon fibre frame 101, passes through splicing
Mode be connected with integral carbon fibre frame 101, ensure that when load is installed on cellular board, carbon fiber frame and metal
110,111,112,113 ontology of built-in fitting while stress.In some specific embodiments, metal embedded part 110,111,112,
113 are designed with load installation interface, while periphery carries out rounded corner processing, avoids the U-shaped beam with integral carbon fibre frame 101
Interference.In addition, lightening hole can also be designed on metal embedded part 110,111,112,113, to ensure the light of whole design
Quantization.The combined method for the metal embedded part 110,111,112,113 that the integral carbon fibre frame 101 is placed with single-point is protected
101 ontology of integral carbon fibre frame and 110,111,112,113 ontology of metal embedded part stress simultaneously have been demonstrate,proved, can have been effectively prevent
Only a single part or glued membrane stress in fastener inserts 100 and may caused by pull phenomenon.
Integral carbon fibre frame 101 can be the frame of the integrated molding by way of carbon fiber laying and/or winding
Frame, such manufacturing method ensure that the continuity of carbon fiber wire, improve the overall mechanical properties of carbon fiber frame.In some tools
In the embodiment of body, the carbon fiber layer thickness of integral carbon fibre frame 101 is 0.5mm to 7mm, it is preferred that can be 2mm.
By taking Fig. 1 and embodiment shown in Fig. 2 as an example, integral carbon fibre frame 101 is using the U-shaped girder construction of thin-walled, carbon
Fiber layer thickness is 2mm.Whole rectangular frame structure takes opening up U-shaped girder construction, and opening up U-shaped at this
The opening of girder construction is glued the frame metal built-in fitting 110 for having and enhancing its load-carrying ability.Simultaneously in view of quality of loads is laid out
Distribution increases an opening up U in the centre position of the first load construction opening 121 and third load construction opening 123
Type girder construction forms " day " font frame, to improve the mechanical property of general frame.First load construction opening and second
Near load construction opening, integral carbon fibre frame 101 takes downward opening U-shaped girder construction, while increasing auxiliary carbon
After fiber small baffle is reinforced, it is connected with " day " font frame；Near third load construction opening, take opening up
U-shaped girder construction, at the same increase auxiliary carbon fiber small baffle reinforced after, be connected with " day " font frame.The integration carbon fiber
Frame 101 is tieed up by the modes integrated molding such as carbon fiber laying, winding, ensure that the continuity of carbon fiber wire.Integrated carbon
The mode that the opening up U-shaped beam of fiber frame 101 and downward opening U-shaped beam are combined, ensure that integral carbon fibre frame
Frame 101 bears mechanical property when Tensile or Compressive Loading simultaneously.It is said it should be understood that the U-shaped beam opening direction of this embodiment is only demonstration
It is bright, and its unrestricted protection domain.
The above-mentioned description to embodiment is that this Shen can be understood and applied for the ease of those skilled in the art
Please.Person skilled in the art obviously easily can make various modifications to these embodiments, and described herein
General Principle is applied in other embodiments without paying performing creative labour.Therefore, the application is not limited to implementation here
Example, those skilled in the art make according to herein disclosed content in the case where not departing from the application scope and spirit
It improves and changes within all scope of the present application.
Claims (10)
1. a kind of spacecraft cellular board, which is characterized in that the cellular board includes：Covering, honeycomb core and fastener inserts, institute
It states fastener inserts with the honeycomb core to be glued, the honeycomb core is glued with the covering, and the fastener inserts include：One
Change carbon fiber frame and metal embedded part, the metal embedded part is glued in the integral carbon fibre lower portion.
2. cellular board according to claim 1, which is characterized in that the integral carbon fibre frame includes：First U-shaped beam
Structure and the second U-shaped girder construction, the first U-shaped girder construction and the second U-shaped girder construction opening direction are opposite.
3. cellular board according to claim 2, which is characterized in that the metal embedded part is glued in the integrated carbon fiber
It ties up in the first U-shaped girder construction of frame and/or the opening of the second U-shaped girder construction.
4. cellular board according to claim 1, which is characterized in that the integral carbon fibre frame is to be spread by carbon fiber
The frame of layer and/or the mode integrated molding of winding.
5. cellular board according to claim 1, which is characterized in that the carbon fiber layer thickness of the integral carbon fibre frame
For 2mm.
6. cellular board according to claim 1, which is characterized in that the metal embedded part further comprises that load installation connects
Mouthful.
7. cellular board according to claim 1, which is characterized in that the metal embedded part further comprises lightening hole.
8. cellular board according to claim 1, which is characterized in that the covering is carbon fibre composite laminate.
9. cellular board according to claim 1, which is characterized in that the honeycomb core is aluminum alloy honeycomb fuse.
10. according to the cellular board described in any one of claim 1-9, which is characterized in that the cellular board is satellite optical base
Quasi- plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810265381.4A CN108502208A (en) | 2018-03-28 | 2018-03-28 | A kind of spacecraft cellular board |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810265381.4A CN108502208A (en) | 2018-03-28 | 2018-03-28 | A kind of spacecraft cellular board |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108502208A true CN108502208A (en) | 2018-09-07 |
Family
ID=63379032
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810265381.4A Pending CN108502208A (en) | 2018-03-28 | 2018-03-28 | A kind of spacecraft cellular board |
Country Status (1)
| Country | Link |
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| CN (1) | CN108502208A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110901964A (en) * | 2019-12-31 | 2020-03-24 | 航天科工火箭技术有限公司 | Load board and satellite adapter device |
| CN112394597A (en) * | 2020-11-30 | 2021-02-23 | 北京空间机电研究所 | Full carbon fiber high stability space camera optical machine structure |
| CN113370594A (en) * | 2021-06-21 | 2021-09-10 | 航天科工火箭技术有限公司 | Method for designing and manufacturing honeycomb sandwich plate |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2003236940A (en) * | 2002-02-21 | 2003-08-26 | Toshiba Corp | Method for molding insert-embedded honeycomb sandwiched panel |
| CN103287588A (en) * | 2013-04-25 | 2013-09-11 | 上海卫星工程研究所 | High-carrying-capacity embedded frame composite material structural slab |
| CN104260903A (en) * | 2014-09-16 | 2015-01-07 | 上海卫星工程研究所 | Propelling module structure with independent high-rail satellite platform function |
| CN104401508A (en) * | 2014-10-27 | 2015-03-11 | 北京空间飞行器总体设计部 | Cross bracing main structure for spacecraft |
| CN106569247A (en) * | 2016-11-08 | 2017-04-19 | 中国科学院近代物理研究所 | Dark matter particle detection satellite plastic flash array detector system |
-
2018
- 2018-03-28 CN CN201810265381.4A patent/CN108502208A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2003236940A (en) * | 2002-02-21 | 2003-08-26 | Toshiba Corp | Method for molding insert-embedded honeycomb sandwiched panel |
| CN103287588A (en) * | 2013-04-25 | 2013-09-11 | 上海卫星工程研究所 | High-carrying-capacity embedded frame composite material structural slab |
| CN104260903A (en) * | 2014-09-16 | 2015-01-07 | 上海卫星工程研究所 | Propelling module structure with independent high-rail satellite platform function |
| CN104401508A (en) * | 2014-10-27 | 2015-03-11 | 北京空间飞行器总体设计部 | Cross bracing main structure for spacecraft |
| CN106569247A (en) * | 2016-11-08 | 2017-04-19 | 中国科学院近代物理研究所 | Dark matter particle detection satellite plastic flash array detector system |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110901964A (en) * | 2019-12-31 | 2020-03-24 | 航天科工火箭技术有限公司 | Load board and satellite adapter device |
| CN110901964B (en) * | 2019-12-31 | 2021-09-07 | 航天科工火箭技术有限公司 | Load board and satellite adapter device |
| CN112394597A (en) * | 2020-11-30 | 2021-02-23 | 北京空间机电研究所 | Full carbon fiber high stability space camera optical machine structure |
| CN113370594A (en) * | 2021-06-21 | 2021-09-10 | 航天科工火箭技术有限公司 | Method for designing and manufacturing honeycomb sandwich plate |
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Application publication date: 20180907 |
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