CN104029827A - Fiber rod filling corrugated sandwich structure - Google Patents
Fiber rod filling corrugated sandwich structure Download PDFInfo
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- CN104029827A CN104029827A CN201410264475.1A CN201410264475A CN104029827A CN 104029827 A CN104029827 A CN 104029827A CN 201410264475 A CN201410264475 A CN 201410264475A CN 104029827 A CN104029827 A CN 104029827A
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- fiber rod
- layer flat
- flat board
- corrugated plating
- sandwich structure
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Abstract
The invention discloses a fiber rod filling corrugated sandwich structure. The structure comprises an outer layer flat plate, an inner layer flat plate, a corrugated plate, fiber rods and filling resin, wherein the outer layer flat plate is parallel to the inner layer flat plate; the corrugated plate is arranged between the outer layer flat plate and the inner layer flat plate; the extending direction of corrugation of the corrugated plate is parallel to the outer layer flat plate; the fiber rods are arranged in cavities surrounded by the outer layer flat plate and the corrugated plate and cavities surrounded by the inner layer flat plate and the corrugated plate, and the cavities are all filled with the filling resin. The structure disclosed by the invention can effectively withstand the impact damage of space debris to the outer structure and inner facilities of a spacecraft, so as to play a favourable protective effect and effectively reduce the additional protection quality.
Description
Technical field
The present invention relates to protection of space debris field, be specifically related to a kind of fiber rod filled type ripple sandwich structure.
Background technology
Along with the develop rapidly of space technology, the mankind's solar-system operation is day by day frequent, thereby causes space environment increasingly sophisticated, also increasing year by year of the quantity of space debris.The average relative that space debris and spacecraft clash into can reach 10 km/s, and the safe operation of spacecraft in-orbit in the mechanical damage effect serious threat that hypervelocity impact causes.Therefore, spacecraft shield structure design is the research emphasis in protection of space debris field.
The Whipple fail-safe structure that the space debris prevention structure generally adopting both at home and abroad at present mainly proposes in nineteen forty-seven based on Whipple.Up to now, the protection configurations such as single dash plate Whipple fail-safe structure, grid double buffering plate fail-safe structure, multilayer surge guard structure and interlayer composite protection structure been have have been designed and developed out on its basis.These traditional fail-safe structures have been obtained certain effect in protection of space debris, but along with the deterioration increasingly of space debris environment, spacecraft shield task is also more arduous, and traditional fail-safe structure has been difficult to meet protection requirements.In order to promote better the barrier propterty of spacecraft, reduce as much as possible the added mass of fail-safe structure simultaneously, fail-safe structure that must development of new is also developed advanced protective material.
China starts late to the research of protection of space debris problem, in relevant technical field, is in a backward condition always.The advanced design of fail-safe structure and the development of optimization and high-performance protective material are the emphasis direction of China in the research of spacecraft protection of space debris, realize with minimum fail-safe structure weight the focus target that maximum protective benefits is this type of research, therefore the lightweight protecting structure of development of new is imperative.
Summary of the invention
The object of the present invention is to provide a kind of fiber rod filled type ripple sandwich structure, can make spacecraft effectively resist the high-speed impact of space debris, realize the lightweight of fail-safe structure simultaneously.
The technical solution that realizes the object of the invention is: a kind of fiber rod filled type ripple sandwich structure, comprise outer dull and stereotyped, internal layer is dull and stereotyped, corrugated plating, fiber rod and potting resin; Outer dull and stereotyped parallel with internal layer flat board, described corrugated plating is arranged between outer flat board and internal layer flat board, the ripple bearing of trend of corrugated plating is with outer dull and stereotyped parallel, fiber rod is arranged in the cavity that skin is dull and stereotyped and corrugated plating surrounds and in the cavity that internal layer is dull and stereotyped and corrugated plating surrounds, and in above-mentioned cavity, all fills up potting resin.
The bellows-shaped of described corrugated plating is triangle or trapezoidal.
Described fiber bar structure is cylinder, and three contact surfaces of above-mentioned cylinder outside face and its place cavity are all tangent.
In three contact surfaces of above-mentioned cylinder external surface and its place cavity, must have a contact surface is outer flat board or internal layer flat board.
Described skin is dull and stereotyped, internal layer material dull and stereotyped and corrugated plating is identical, is aluminum alloy, titanium alloy or magnesium alloy.
Described fiber bar material is basalt fibre, carbon fiber or glass fibre.
Above-mentioned potting resin is epoxy resin.
The present invention compared with prior art, its remarkable advantage: the inside and outside layer flat board of (1) structure and corrugated plating all can effectively decompose the space debris of high-speed impact, its damage energy of disperse and dilute, three's applied in any combination makes space debris in the time clashing into this structure, to be subject to continuously stopping for three times, this will decompose more fully to space debris, and significantly reduce the speed of debris cloud, and protection effect is more remarkable;
(2) the fiber rod in structure has high intensity, can strengthen the bulk strength of fail-safe structure, prevent that structure from havoc occurring in the time being subject to impact from space debris, fiber rod can effectively stop passing of fragment simultaneously, cut down significantly the kinematic velocity of debris cloud, make fail-safe structure more effectively disperse the energy of debris cloud; In addition, the density of fiber rod is lower, can alleviate to a certain extent the quality of fail-safe structure;
(3) potting resin in structure also can carry out fragmentation and fusing to space debris, absorbs its Impact energy.
Brief description of the drawings
Fig. 1 is the assembling schematic diagram of fiber rod filled type ripple sandwich structure of the present invention, and wherein in figure (a), the bellows-shaped of corrugated plating is triangle, and in figure (b), the bellows-shaped of corrugated plating is trapezoidal.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is described in further detail.
A kind of fiber rod filled type ripple sandwich structure, comprises outer flat board 1, internal layer flat board 3, corrugated plating 2, fiber rod 4 and potting resin 5; Outer dull and stereotyped 1 is parallel with internal layer flat board 3, described corrugated plating 2 is arranged between outer flat board 1 and internal layer flat board 3, the ripple bearing of trend of corrugated plating 2 is parallel with outer flat board 1, fiber rod 4 be arranged at outer dull and stereotyped 1 and the cavity that surrounds of corrugated plating 2 in and in the cavity that surrounds of internal layer dull and stereotyped 3 and corrugated plating 2, and in above-mentioned cavity, all fill up potting resin 5.
The bellows-shaped of described corrugated plating 2 is triangle or trapezoidal.
Described fiber rod 4 structures are cylinder, and three contact surfaces of above-mentioned cylinder outside face and its place cavity are all tangent.
In three contact surfaces of above-mentioned cylinder external surface and its place cavity, must there is a contact surface for outer flat board 1 or internal layer flat board 3.
The material of described outer flat board 1, internal layer dull and stereotyped 3 and corrugated plating 2 is identical, is aluminum alloy, titanium alloy or magnesium alloy.
Described fiber rod 4 materials are basalt fibre, carbon fiber or glass fibre.
Above-mentioned potting resin 5 is epoxy resin.
Embodiment 1
With reference to Fig. 1 (a), a kind of fiber rod filled type ripple sandwich structure, comprises outer dull and stereotyped 1, internal layer flat board 3, is arranged on corrugated plating 2 in the middle of ectonexine flat board, is arranged on ectonexine flat board and corrugated plating surrounds the cylindrical fibre rod 4 in cavity and is filled in the resin 5 in space.The constituent material of outer flat board 1, corrugated plating 2 and internal layer flat board 3 can be selected alloy in lightweight, titanium alloy; The thickness of outer flat board 1, internal layer dull and stereotyped 3 and corrugated plating 2 can be identical; The bellows-shaped of corrugated plating is triangle; The material of fiber rod 4 is carbon fiber; Potting resin 5 is low density annulus epoxy resins; Outer flat board 1, corrugated plating 2 and internal layer flat board 3 are bonded as one by adhesive specially, fiber rod 4 inserts in the cavity that ectonexine is dull and stereotyped and corrugated plating surrounds, finally use low-density resin 5 to fill encapsulation, to form a kind of fiber rod filled type ripple sandwich structure.
Embodiment 2
With reference to Fig. 1 (b), a kind of fiber rod filled type ripple sandwich structure, comprises outer dull and stereotyped 1, internal layer flat board 3, is arranged on corrugated plating 2 in the middle of ectonexine flat board, is arranged on ectonexine flat board and corrugated plating surrounds the cylindrical fibre rod 4 in cavity and is filled in the resin 5 in space.The constituent material of outer flat board 1, corrugated plating 2 and internal layer flat board 3 can be selected alloy in lightweight, as aluminum alloy; The thickness of outer flat board 1, internal layer dull and stereotyped 3 and corrugated plating 2 can be identical; The bellows-shaped of corrugated plating is trapezoidal; Fiber rod 4 be basalt fibre; Potting resin 5 is low density annulus epoxy resins; Outer flat board 1, corrugated plating 2 and internal layer flat board 3 are bonded as one by adhesive specially, fiber rod 4 inserts in the cavity that ectonexine is dull and stereotyped and corrugated plating surrounds, finally use low-density resin 5 to fill encapsulation, to form a kind of fiber rod filled type ripple sandwich structure.
The outer flat board 1 of the present invention, internal layer dull and stereotyped 3 and corrugated plating 2 all can effectively decompose the space debris of high-speed impact, its damage energy of disperse and dilute, three's applied in any combination makes space debris in the time clashing into this structure, to be subject to continuously stopping for three times, this will decompose more fully to space debris, and significantly reducing the speed of debris cloud, protection effect is more remarkable.
Fiber rod 4 has high intensity, can strengthen the bulk strength of fail-safe structure, prevent that structure from havoc occurring in the time being subject to impact from space debris, fiber rod 4 can effectively stop passing of fragment simultaneously, cut down significantly the kinematic velocity of debris cloud, make fail-safe structure more effectively disperse the energy of debris cloud; In addition, the density of fiber rod 4 is lower, can alleviate to a certain extent the quality of fail-safe structure.
Potting resin 5 also can carry out fragmentation and fusing to space debris, absorbs its Impact energy.
In sum, space debris, through in the process of structure of the present invention, will be subject to the associating decementation of various piece, and damage energy will significantly be disperseed and absorb.Therefore, fiber rod filled type ripple sandwich structure of the present invention can be resisted the impact damage of space debris to spacecraft external structure and inner facility effectively, plays good protective action and effectively reduces additional protection quality.
Claims (7)
1. a fiber rod filled type ripple sandwich structure, is characterized in that: comprise outer dull and stereotyped (1), internal layer flat board (3), corrugated plating (2), fiber rod (4) and potting resin (5); Outer dull and stereotyped (1) is parallel with internal layer flat board (3), described corrugated plating (2) is arranged between outer dull and stereotyped (1) and internal layer flat board (3), the ripple bearing of trend of corrugated plating (2) is parallel with outer dull and stereotyped (1), in the cavity that fiber rod (4) is arranged in the cavity that outer dull and stereotyped (1) and corrugated plating (2) surround and internal layer flat board (3) and corrugated plating (2) surround, and in above-mentioned cavity, all fill up potting resin (5).
2. fiber rod filled type ripple sandwich structure according to claim 1, is characterized in that: the bellows-shaped of described corrugated plating (2) is triangle or trapezoidal.
3. fiber rod filled type ripple sandwich structure according to claim 1, is characterized in that: described fiber rod (4) structure is cylinder, three contact surfaces of above-mentioned cylinder outside face and its place cavity are all tangent.
4. fiber rod filled type ripple sandwich structure according to claim 3, is characterized in that: in three contact surfaces of above-mentioned cylinder external surface and its place cavity, must have a contact surface for outer flat board (1) or internal layer flat board (3).
5. fiber rod filled type ripple sandwich structure according to claim 1, is characterized in that: the material of described outer dull and stereotyped (1), internal layer flat board (3) and corrugated plating (2) is identical, is aluminum alloy, titanium alloy or magnesium alloy.
6. fiber rod filled type ripple sandwich structure according to claim 1, is characterized in that: described fiber rod (4) material is basalt fibre, carbon fiber or glass fibre.
7. fiber rod filled type ripple sandwich structure according to claim 1, is characterized in that: above-mentioned potting resin (5) is epoxy resin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410264475.1A CN104029827A (en) | 2014-06-13 | 2014-06-13 | Fiber rod filling corrugated sandwich structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410264475.1A CN104029827A (en) | 2014-06-13 | 2014-06-13 | Fiber rod filling corrugated sandwich structure |
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| CN104029827A true CN104029827A (en) | 2014-09-10 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410264475.1A Pending CN104029827A (en) | 2014-06-13 | 2014-06-13 | Fiber rod filling corrugated sandwich structure |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2623782C1 (en) * | 2016-03-02 | 2017-06-29 | Акционерное общество "Научно-производственное объединение им. С.А.Лавочкина" (АО "НПО Лавочкина") | Screen for spacecraft protection from high speed impact actions of the space environment particles |
| CN107140238A (en) * | 2017-05-08 | 2017-09-08 | 北京卫星环境工程研究所 | Kinetic energy efficiently dissipates space debris prevention structure |
| CN111116180A (en) * | 2020-02-12 | 2020-05-08 | 江西车田科技有限公司 | Integral net-shaped microporous ceramic corrugated packing and manufacturing method thereof |
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| RU2299838C1 (en) * | 2005-12-08 | 2007-05-27 | Михаил Михайлович Кононенко | Device for protection of spacecraft and space stations against high-velocity impact action of space medium particles |
| JP2011121476A (en) * | 2009-12-10 | 2011-06-23 | Wakichi Arai | Lightweight shield for space debris |
| US20110283873A1 (en) * | 2007-08-16 | 2011-11-24 | University Of Virginia Patent Foundation | Hybrid Periodic Cellular Material Structures, Systems, and Methods For Blast and Ballistic Protection |
| CN102490912A (en) * | 2011-11-08 | 2012-06-13 | 西安交通大学 | Space debris prevention structure of spacecraft |
| CN102514737A (en) * | 2011-11-08 | 2012-06-27 | 西安交通大学 | Lightweight filled composite protective structure for space debris |
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2014
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Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN1423593A (en) * | 2000-04-17 | 2003-06-11 | F·利奇泰里奥股份公司 | Reinforced multilayer fabric and method of preparation |
| RU2299838C1 (en) * | 2005-12-08 | 2007-05-27 | Михаил Михайлович Кононенко | Device for protection of spacecraft and space stations against high-velocity impact action of space medium particles |
| US20110283873A1 (en) * | 2007-08-16 | 2011-11-24 | University Of Virginia Patent Foundation | Hybrid Periodic Cellular Material Structures, Systems, and Methods For Blast and Ballistic Protection |
| JP2011121476A (en) * | 2009-12-10 | 2011-06-23 | Wakichi Arai | Lightweight shield for space debris |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2623782C1 (en) * | 2016-03-02 | 2017-06-29 | Акционерное общество "Научно-производственное объединение им. С.А.Лавочкина" (АО "НПО Лавочкина") | Screen for spacecraft protection from high speed impact actions of the space environment particles |
| CN107140238A (en) * | 2017-05-08 | 2017-09-08 | 北京卫星环境工程研究所 | Kinetic energy efficiently dissipates space debris prevention structure |
| CN107140238B (en) * | 2017-05-08 | 2020-07-28 | 北京卫星环境工程研究所 | Kinetic energy efficient dissipation protective screen |
| CN111116180A (en) * | 2020-02-12 | 2020-05-08 | 江西车田科技有限公司 | Integral net-shaped microporous ceramic corrugated packing and manufacturing method thereof |
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Application publication date: 20140910 |