CN108859272A - Support construction and aluminum slice interlayer for aluminum slice interlayer - Google Patents
Support construction and aluminum slice interlayer for aluminum slice interlayer Download PDFInfo
- Publication number
- CN108859272A CN108859272A CN201811050175.8A CN201811050175A CN108859272A CN 108859272 A CN108859272 A CN 108859272A CN 201811050175 A CN201811050175 A CN 201811050175A CN 108859272 A CN108859272 A CN 108859272A
- Authority
- CN
- China
- Prior art keywords
- aluminum slice
- support construction
- interlayer
- support
- supporting surface
- 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
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 title claims abstract description 60
- 229910052782 aluminium Inorganic materials 0.000 title claims abstract description 60
- 239000011229 interlayer Substances 0.000 title claims abstract description 46
- 238000010276 construction Methods 0.000 title claims abstract description 45
- 238000009826 distribution Methods 0.000 claims abstract description 9
- 230000015572 biosynthetic process Effects 0.000 claims abstract description 6
- 230000000694 effects Effects 0.000 abstract description 11
- 241001536563 Panus Species 0.000 abstract description 8
- 239000004411 aluminium Substances 0.000 abstract description 5
- 239000000835 fiber Substances 0.000 abstract description 5
- 238000009792 diffusion process Methods 0.000 abstract description 3
- 239000004744 fabric Substances 0.000 abstract description 3
- 239000000178 monomer Substances 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 5
- 210000003850 cellular structure Anatomy 0.000 description 2
- 239000003292 glue Substances 0.000 description 2
- 239000010410 layer Substances 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000009828 non-uniform distribution Methods 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B31—MAKING ARTICLES OF PAPER, CARDBOARD OR MATERIAL WORKED IN A MANNER ANALOGOUS TO PAPER; WORKING PAPER, CARDBOARD OR MATERIAL WORKED IN A MANNER ANALOGOUS TO PAPER
- B31D—MAKING ARTICLES OF PAPER, CARDBOARD OR MATERIAL WORKED IN A MANNER ANALOGOUS TO PAPER, NOT PROVIDED FOR IN SUBCLASSES B31B OR B31C
- B31D3/00—Making articles of cellular structure, e.g. insulating board
- B31D3/02—Making articles of cellular structure, e.g. insulating board honeycombed structures, i.e. the cells having an essentially hexagonal section
Landscapes
- Laminated Bodies (AREA)
Abstract
The present invention relates to the support constructions and aluminum slice interlayer for aluminum slice interlayer, the support construction for aluminum slice interlayer includes at least three supporting surfaces, the inside frame of all supporting surfaces links together, to the supporter of the radial distribution of circumferencial direction centered on side frame within formation；The upper surface and the lower surface of the supporter is plane.Frame is separated by a distance on the outside of each supporting surface monomer of the present invention, is not contacted, is avoided the channelling effect of hexagonal structure in honeycomb, be conducive to the diffusion of panus, to provide more effective protection for spacecraft.It can be applied to the fields such as aluminium sheet sandwich structure and fiber cloth support.
Description
Technical field
The present invention relates to aluminum slice support technology fields, the more particularly, to support construction and aluminum slice of aluminum slice interlayer
Interlayer.
Background technique
Currently, the aluminium bee of higher-strength weight ratio is widely used with designability and had in spaceborne aluminium sheet interlayer
Nest is as support and safeguard structure.
In the fiber stuffed Whipple shield structure of spacecraft, the fiber cloth of filled layer is fixed and is propped up using aluminum honeycomb structure
Support, can be effectively reduced the weight of fiber filled layer additional structure, and can play the effect of dissipation panus kinetic energy, improve protection
The performance of structure.But using the aluminum honeycomb sandwich board of identical surface density and Whipple structure as control, aluminum honeycomb sandwich board
It is poor compared with the impact energy absorption and dissipation characteristic of Whipple structure, this is because honeycomb core lattice structure imitates the channel of panus
It should be unfavorable for the diffusion of panus；Also, the rear wall that honeycomb core lattice will cause spacecraft bulkhead to the convergence effect of panus is worn
Hole damage aggravates.
Therefore, against the above deficiency, it is desirable to provide a kind of new aluminum slice support construction had both been able to satisfy the requirement of lightweight,
It is avoided that channelling effect again, to form better protection to spacecraft.
Summary of the invention
The technical problem to be solved in the present invention is that for aluminum honeycomb in existing spacecraft shield structure channelling effect not
Conducive to the diffusion of panus, the defect of spacecraft bulkhead damage can be aggravated, a kind of support construction for aluminum slice interlayer is provided
And aluminum slice interlayer.
In order to solve the above-mentioned technical problems, the present invention provides a kind of support constructions for aluminum slice interlayer, it includes
The inside frame of at least three supporting surfaces, all supporting surfaces links together, to circumferencial direction centered on side frame within formation
The supporter of radial distribution；The upper surface and the lower surface of the supporter is plane.
It further include support shaft in the support construction according to the present invention for aluminum slice interlayer, all supporting surfaces
Inside frame linked together by support shaft.
In the support construction according to the present invention for aluminum slice interlayer, all adjacent support surfaces are along the circumferential direction
Angle it is identical.
In the support construction according to the present invention for aluminum slice interlayer, all supporting surfaces are plane.
In the support construction according to the present invention for aluminum slice interlayer, the structure of all supporting surfaces is identical.
In the support construction according to the present invention for aluminum slice interlayer, the supporting surface is three, wherein two
The structure of a supporting surface is identical, and the radical length of third supporting surface is longer than described two supporting surfaces；
Preferred embodiment is：The cross section of three supporting surfaces is Y-shaped, and the two of them supporting surface is with third supporting surface
Symmetry axis is arranged in mirror symmetry.
In the support construction according to the present invention for aluminum slice interlayer, at least one in all supporting surfaces
Cross section is curve.
In the support construction according to the present invention for aluminum slice interlayer, at least one in all supporting surfaces
Cross section is S-shaped.
In the support construction according to the present invention for aluminum slice interlayer, the supporter is multiple, formation battle array
Column arrangement.
The present invention also provides a kind of aluminum slice interlayer, filled out in the interlayer using support construction described in any of the above embodiments
It fills.
Implement the support construction and aluminum slice interlayer for aluminum slice interlayer of the invention, has the advantages that：This
Invention is used for the interbedded filling of aluminum slice, and supporting body structure is similar to the shape of paddle, each supporting surface monomer outside
Frame is separated by a distance, and is not contacted, and the channelling effect of hexagonal structure in honeycomb is avoided, and is conducive to the expansion of panus
It dissipates, to provide more effective protection for spacecraft.
Detailed description of the invention
Fig. 1 is a kind of exemplary structure schematic diagram of the support construction according to the present invention for aluminum slice interlayer；
Fig. 2 is the illustrative diagram with the support construction for aluminum slice interlayer of support shaft；
Fig. 3 is the exemplary cross section schematic diagram that supporting surface is curved surface；
Fig. 4 is the S-shaped illustrative diagram in the cross section of supporting surface；
Fig. 5 is the illustrative diagram of multiple supporter distributions in aluminum slice interlayer.
Specific embodiment
In order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below in conjunction with the embodiment of the present invention
In attached drawing, technical scheme in the embodiment of the invention is clearly and completely described, it is clear that described embodiment is
A part of the embodiments of the present invention, instead of all the embodiments.Based on the embodiments of the present invention, ordinary skill people
Member's every other embodiment obtained without making creative work, shall fall within the protection scope of the present invention.
Specific embodiment one：
As shown in connection with fig. 1, present embodiments provide for a kind of support constructions for aluminum slice interlayer, it includes at least three
The inside frame of a supporting surface 1, all supporting surfaces 1 links together, and radiates centered on side frame to circumferencial direction within formation
The supporter of shape distribution；The upper surface and the lower surface of the supporter is plane.
Present embodiments provide for a kind of support construction being used in aluminum slice interlayer different from honeycomb ceramics, supporting surfaces
1 laying form is similar to the distribution of blade.This support construction is between such as two panels aluminum slice, wherein per a piece of supporting surface
1 extends directly to lower aluminum slice from upper aluminum slice, and the outside frame of each 1 monomer of supporting surface is separated by a distance, does not contact, no
In the presence of the hexagonal structure in such as honeycomb, therefore convergence effect will not be generated to panus, can generate good protection
Effect.The support construction is easily worked, and can be obtained by legacy cellular structure of modification, for example, along each face of legacy cellular structure
Centre cut off and can directly obtain, have the characteristics that stability under loading.
The number of supporting surface 1 is selected with specifically used demand, in general, the structural stability of three supporting surfaces 1 is more preferable,
And 1 number of supporting surface is more, support strength is naturally more preferable.
As an example, the support construction can also include support shaft 2, the inside frame of all supporting surfaces 1 passes through support
Axis 2 links together.
The extension supporting axis 2 at the interconnection of supporting surface 1, is conducive to the machine-shaping of supporter.
As a kind of support construction, when its upper surface and the lower surface is plane, without excessive each supporting surface 1 of limitation it
Between orientation, already can be realized the function of support.Such as each supporting surface 1 can along the circumferential direction non-uniform Distribution, for can
The heavier position of stress that can be determined in the presence of experiment or experience can make the distribution of supporting surface 1 relatively intensive, and small for stress
Position, can make supporting surface 1 distribution it is relatively sparse.
And the use environment more balanced for stress, it is more preferable that supporting surface 1 is uniformly distributed support effect.As an example, can
So that angle is identical in the circumferential direction for all adjacent support surfaces 1.
As fairly simple form of implementation, all supporting surfaces 1 can be plane；The supporter of this form it is anti-extrusion and
The intensity of shock is good.
Further, the structure type of all supporting surfaces 1 can be identical, for example, in conjunction with shown in Fig. 1 and Fig. 2, three supporting surfaces
1 shapes and sizes can be completely the same, and the supporter of this form is easily worked, and integral form rule, intensity etc. are comprehensive
It is relatively good to close performance.
In actual use, the structure type of all supporting surfaces 1 can also be not exactly the same, for example, its radical length is different.
As an example, the supporting surface 1 is three, the structure of two of them supporting surface 1 is identical, third supporting surface 1
Radical length is longer than described two supporting surfaces 1；
Further preferred embodiment is：The cross section of three supporting surfaces 1 is Y-shaped, and the two of them supporting surface 1 is with third
A supporting surface 1 is that symmetry axis is arranged in mirror symmetry.Under this form, the angle of three supporting surfaces 1 can respectively be 120 degree,
The angle of the two of them supporting surface 1 can be made smaller, thus it is slightly larger with the angle of third supporting surface 1, it can reduce in this way
The requirement of machining accuracy.
In actual use, the shape of supporting surface 1 can also be not exactly the same, such as can make in all supporting surfaces 1 only
Having the cross section that one cross section is curved surface or two of them is curved surface, and all supporting surfaces 1 can also be made to be selected as song
Face can realize good support performance as shown in Figure 3 and Figure 4.The form of all supporting surfaces 1 can be not exactly the same, favorably
In the difficulty of processing for reducing supporting surface 1.
As an example, can be S-shaped with the cross section of at least one in all supporting surfaces 1, as shown in Figure 4.S-shaped curved surface to
The crooked radian of two sides is almost the same, and stable support can be formed to aluminum slice.
It, can be according to the number of filling space size and strength demand selection supporter as the support of aluminum slice interlayer；
The relationship that its distribution density and support strength can also be measured on the whole, the guidance standard as supporter arrangement density.Institute
There is supporter that can form array arrangement by predetermined arranging rule between aluminum slice interlayer.
Support construction described in present embodiment can be applied to the support construction etc. of aluminium sheet sandwich structure and fiber cloth.
As a comparison, it can be a with honeycomb core side length, be highly h, with a thickness of t, density ρ, the surface density of honeycomb core=
The support construction of design processing honeycomb style for 8ht ρ/(3 × 1.732a)；Then support construction of the invention can pass through by
The each edge of the support construction honeycomb core lattice of designed honeycomb style is cut off from centre to be obtained.All supporters of acquisition are each
From separating, after regular array, can be affixed on aluminium sheet with glue.Since each supporter can be separated from each other, with honeycomb style
Support construction compare, reduce surface density, therefore not only eliminate channelling effect, but also reduce consumptive material.
Specific embodiment two：
As shown in connection with fig. 5, present embodiments provide for a kind of aluminum slice interlayer, the interlayer is interior to use above-mentioned support construction
Filling.
In the support construction, the upper and lower surfaces of each supporter, which can be pasted with aluminum slice by glue, to be fixed.
Due to having used above-mentioned support construction as the filling of aluminum slice interlayer, then aluminum slice sandwich has naturally
Above-mentioned advantage, repeats no more.
In conclusion support construction of the present invention can be good at eliminating the channelling effect in honeycomb, it can be with
Safeguard structure as space flight bulkhead.
Finally it should be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations；Although
Present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that：It still may be used
To modify the technical solutions described in the foregoing embodiments or equivalent replacement of some of the technical features；
And these are modified or replaceed, technical solution of various embodiments of the present invention that it does not separate the essence of the corresponding technical solution spirit and
Range.
Claims (10)
1. a kind of support construction for aluminum slice interlayer, it is characterised in that：It includes at least three supporting surfaces (1), Suo Youzhi
The inside frame in support face (1) links together, to the supporter of the radial distribution of circumferencial direction centered on side frame within formation；
The upper surface and the lower surface of the supporter is plane.
2. the support construction according to claim 1 for aluminum slice interlayer, it is characterised in that：It further includes support shaft
(2), the inside frame of all supporting surfaces (1) is linked together by support shaft (2).
3. the support construction according to claim 1 or 2 for aluminum slice interlayer, it is characterised in that：All adjacent supports
Angle is identical in the circumferential direction in face (1).
4. the support construction according to any one of claim 1 to 3 for aluminum slice interlayer, it is characterised in that：It is all
Supporting surface (1) is plane.
5. the support construction according to any one of claim 1 to 4 for aluminum slice interlayer, it is characterised in that：It is all
The structure of supporting surface (1) is identical.
6. the support construction according to claim 1 or 2 for aluminum slice interlayer, it is characterised in that：The supporting surface (1)
It is three, the structure of two of them supporting surface (1) is identical, and the radical length of third supporting surface (1) is longer than described two supports
Face (1)；
Preferred embodiment is：The cross section of three supporting surfaces (1) is Y-shaped, and the two of them supporting surface (1) is with third supporting surface
(1) it is arranged for symmetry axis in mirror symmetry.
7. the support construction according to any one of claim 1 to 3 for aluminum slice interlayer, it is characterised in that：It is all
The cross section of at least one in supporting surface (1) is curve.
8. the support construction according to claim 7 for aluminum slice interlayer, it is characterised in that：In all supporting surfaces (1)
The cross section of at least one is S-shaped.
9. the support construction according to any one of claim 1 to 8 for aluminum slice interlayer, it is characterised in that：It is described
Supporter is multiple, formation array arrangement.
10. a kind of aluminum slice interlayer, it is characterised in that：Using branch as claimed in any one of claims 1-9 wherein in the interlayer
Support structure filling.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811050175.8A CN108859272A (en) | 2018-09-10 | 2018-09-10 | Support construction and aluminum slice interlayer for aluminum slice interlayer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811050175.8A CN108859272A (en) | 2018-09-10 | 2018-09-10 | Support construction and aluminum slice interlayer for aluminum slice interlayer |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108859272A true CN108859272A (en) | 2018-11-23 |
Family
ID=64323369
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811050175.8A Pending CN108859272A (en) | 2018-09-10 | 2018-09-10 | Support construction and aluminum slice interlayer for aluminum slice interlayer |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108859272A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111645884A (en) * | 2020-06-17 | 2020-09-11 | 中国空气动力研究与发展中心超高速空气动力研究所 | Frame honeycomb structure, honeycomb sandwich structure and fiber filling type protection configuration |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020197193A1 (en) * | 2000-01-13 | 2002-12-26 | Takashi Harada | Honeycomb structure |
| CN103481551A (en) * | 2013-04-28 | 2014-01-01 | 张瑞洋 | High-strength composite plate without weak stress lines and folder |
| CN105659746B (en) * | 2010-12-31 | 2014-02-19 | 北京空间飞行器总体设计部 | The large capacity satellite propelling module of structure and load integrated design |
| 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 |
| CN104495028A (en) * | 2014-12-18 | 2015-04-08 | 天津商业大学 | Four-piece integral package |
| CN204252384U (en) * | 2014-11-21 | 2015-04-08 | 稳特复合技术有限公司 | A kind of reinforced honeycomb composite floor |
| CN105701321A (en) * | 2016-03-11 | 2016-06-22 | 三峡大学 | Improvement similar-honeycomb sandwich structure and processing method |
| CN107792399A (en) * | 2017-09-25 | 2018-03-13 | 上海卫星工程研究所 | Tank test formula satellite platform structure |
| CN208745439U (en) * | 2018-09-10 | 2019-04-16 | 中国空气动力研究与发展中心超高速空气动力研究所 | Support construction and aluminum slice interlayer for aluminum slice interlayer |
-
2018
- 2018-09-10 CN CN201811050175.8A patent/CN108859272A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020197193A1 (en) * | 2000-01-13 | 2002-12-26 | Takashi Harada | Honeycomb structure |
| CN105659746B (en) * | 2010-12-31 | 2014-02-19 | 北京空间飞行器总体设计部 | The large capacity satellite propelling module of structure and load integrated design |
| CN103481551A (en) * | 2013-04-28 | 2014-01-01 | 张瑞洋 | High-strength composite plate without weak stress lines and folder |
| 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 |
| CN204252384U (en) * | 2014-11-21 | 2015-04-08 | 稳特复合技术有限公司 | A kind of reinforced honeycomb composite floor |
| CN104495028A (en) * | 2014-12-18 | 2015-04-08 | 天津商业大学 | Four-piece integral package |
| CN105701321A (en) * | 2016-03-11 | 2016-06-22 | 三峡大学 | Improvement similar-honeycomb sandwich structure and processing method |
| CN107792399A (en) * | 2017-09-25 | 2018-03-13 | 上海卫星工程研究所 | Tank test formula satellite platform structure |
| CN208745439U (en) * | 2018-09-10 | 2019-04-16 | 中国空气动力研究与发展中心超高速空气动力研究所 | Support construction and aluminum slice interlayer for aluminum slice interlayer |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111645884A (en) * | 2020-06-17 | 2020-09-11 | 中国空气动力研究与发展中心超高速空气动力研究所 | Frame honeycomb structure, honeycomb sandwich structure and fiber filling type protection configuration |
| CN111645884B (en) * | 2020-06-17 | 2021-11-19 | 中国空气动力研究与发展中心超高速空气动力研究所 | Frame honeycomb structure, honeycomb sandwich structure and fiber filling type protection configuration |
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