CN101468533A - Spacecraft magnesium alloy insert board - Google Patents
Spacecraft magnesium alloy insert board Download PDFInfo
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- CN101468533A CN101468533A CNA2007101729451A CN200710172945A CN101468533A CN 101468533 A CN101468533 A CN 101468533A CN A2007101729451 A CNA2007101729451 A CN A2007101729451A CN 200710172945 A CN200710172945 A CN 200710172945A CN 101468533 A CN101468533 A CN 101468533A
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- magnesium alloy
- alloy insert
- glued membrane
- spacecraft
- insert board
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Abstract
The invention relates to a structural plate for an aerospace craft, and discloses a magnesium alloy insert plate for the aerospace craft. The structural plate comprises an upper panel (1), an upper glue film (2), a honeycomb core (3), foaming glue (4), the magnesium alloy insert (5), a lower glue film (6) and a lower panel (7) which are laminated sequentially. The structural plate solves the problems of the weight of the aerospace craft, and low gluing strength between a magnesium alloy insert and an aluminum panel and has the advantages of reducing the launching cost, improving the capability of satellite carrying payload, improving satellite performance and so on.
Description
Technical field
The present invention relates to the aerospace craft structural panel, be specially a kind of magnesium alloy insert board material that is used for honeycomb sandwich construction.
Background technology
Before the present invention uses, generally adopt aluminum alloy materials or titanium alloy material as inserts in the honeycomb sandwich construction plate of spacecraft structure and other association area, the inserts that adopts stainless steel material is also arranged, it is exactly that density of material is big that these materials are used for the existing the most general problem of honeycomb sandwich construction, is respectively 2.7g/cm as the density of aluminium alloy and titanium alloy material
3And 4.5g/cm
3, higher as for the density of stainless steel material, so just improved the construction weight of honeycomb sandwich construction plate, for spacecraft, the increase of construction weight will cause the rising of launch cost, also retrain it simultaneously and carry more payload, carry out the ability of more scientific explorations and test.
Magnesium alloy materials is the lightest metal material during engineering is used, but, limited its application, before this in field of aerospace because there are problems such as intensity is low and perishable in it, used for magnesium alloy mostly is foundry goods series products or plate series products in spacecraft, does not see that magnesium alloy materials is used for honeycomb sandwich construction.
Summary of the invention
In order to solve the weight issue of spacecraft, the object of the present invention is to provide a kind of spacecraft magnesium alloy insert board, utilize the present invention, not only reach and alleviate spacecraft structure weight, reduce the requirement of launch cost, and can improve the ability that satellite carries payload, improve the ratio performance of satellite.
In order to reach the foregoing invention purpose, the technical scheme that the present invention is adopted for its technical problem of solution provides a kind of spacecraft magnesium alloy insert board, and this device comprises:
Successively the top panel of lamination, go up glued membrane, honeycomb core, foamed glue, magnesium alloy insert, glued membrane, lower panel down.Top panel and lower panel can be selected aluminum alloy materials or carbon fibre composite laminate for use, and last glued membrane and following glued membrane are warm structure glue in J47 series or the J78 series, and film thickness is 0.1mm to 0.3mm.Foamed glue is J47D type or J78D type, is filled in around the magnesium alloy insert in the 10mm scope.The honeycomb core specification is 4 * 0.04 or 5 * 0.04 aluminium alloy or aramid fiber paper material; Magnesium alloy insert glueds joint by foamed glue and honeycomb core and is one, again by last glued membrane with top panel, be connected into one, curing molding in autoclave by descending glued membrane and lower panel compound adhesive.
Spacecraft magnesium alloy insert board of the present invention, owing to take technique scheme, therefore, solved the low problem of glue-joint strength between the inserts of magnesium alloy materials and the aluminum deck, by surface treatment, improve the glue-joint strength of magnesium alloy materials and aluminum deck, reached more than the 18MPa, thereby satisfied the requirement that structure connects.Obtained and alleviated spacecraft weight, reduce launch cost, improve the ability that satellite carries payload, the beneficial effects such as ratio performance that improve satellite.
Description of drawings
Accompanying drawing is the structural representation of spacecraft magnesium alloy insert board of the present invention.
Numbering expression among the figure: 1-top panel 2-last glued membrane 3-honeycomb core 4-foamed glue 5-magnesium alloy insert 6-following glued membrane 7-lower panel.
The specific embodiment
Below in conjunction with description of drawings the preferred embodiments of the present invention.
Accompanying drawing 1 is the structural representation of spacecraft magnesium alloy insert board of the present invention, and accompanying drawing 2 is a front view, and shown in the embodiment of accompanying drawing, this device comprises:
Successively the top panel 1 of lamination, go up glued membrane 2, honeycomb core 3, foamed glue 4, magnesium alloy insert 5, glued membrane 6, lower panel 7 down.Top panel 1 can be selected aluminum alloy materials or carbon fibre composite laminate for use with lower panel 7, and last glued membrane 2 and following glued membrane 6 are warm structure glue in J47 series or the J78 series, and film thickness is 0.1mm to 0.3mm.Foamed glue 4 is J47D type or J78D type, is filled in around the magnesium alloy insert 5 in the 10mm scope.Honeycomb core 3 specifications are 4 * 0.04 or 5 * 0.04 aluminium alloy or aramid fiber paper material; Magnesium alloy insert 5 glueds joint by foamed glue 4 and honeycomb core 3 and is one, again by last glued membrane 2 and top panel 1, be connected into one, curing molding in autoclave by glued membrane 6 down with lower panel 7 compound adhesive.
From the above mentioned, the present invention replaces the aluminium in the present honeycomb sandwich construction plate, the inserts of titanium alloy material for alleviating honeycomb sandwich construction weight with magnesium alloy materials.And,, taked the surface anticorrosive processing, and utilized the adhesive film material in the sandwich effectively to intercept the erosion of external environment, thereby improved its ground storage capacity for solving the anticorrosion resistance to corrosion of magnesium alloy.
Claims (5)
1, a kind of spacecraft magnesium alloy insert board is characterized in that, this device comprises:
Successively the top panel of lamination [1], go up glued membrane [2], honeycomb core [3], foamed glue [4], magnesium alloy insert [5], glued membrane [6], lower panel [7] down; Described magnesium alloy insert [5] glueds joint by foamed glue [4] and honeycomb core [3] and is one, again by last glued membrane [2] and top panel [1], by under glued membrane [6] and lower panel [7] compound adhesive be connected into one, curing molding in autoclave.
2, magnesium alloy insert board according to claim 1 is characterized in that: described top panel [1] is aluminum alloy materials or carbon fibre composite laminate with lower panel [7].
3, magnesium alloy insert board according to claim 1 is characterized in that: described upward glued membrane [2] and following glued membrane [6] are warm structure glue in J47 series or the J78 series, and film thickness is 0.1mm to 0.3mm.
4, magnesium alloy insert board according to claim 1 is characterized in that: described foamed glue [4] is J47D type or J78D type, is filled in magnesium alloy insert [5] on every side in the 10mm scope.
5, magnesium alloy insert board according to claim 1 is characterized in that: described honeycomb core [3] is 4 * 0.04 or 5 * 0.04 aluminium alloy or aramid fiber paper material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200710172945 CN101468533B (en) | 2007-12-25 | 2007-12-25 | Spacecraft magnesium alloy insert board |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200710172945 CN101468533B (en) | 2007-12-25 | 2007-12-25 | Spacecraft magnesium alloy insert board |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101468533A true CN101468533A (en) | 2009-07-01 |
| CN101468533B CN101468533B (en) | 2012-11-28 |
Family
ID=40826451
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200710172945 Active CN101468533B (en) | 2007-12-25 | 2007-12-25 | Spacecraft magnesium alloy insert board |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101468533B (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102490910A (en) * | 2011-11-15 | 2012-06-13 | 上海卫星工程研究所 | Composite sandwich-structured bearing cylinder for spacecrafts |
| CN103075629A (en) * | 2011-10-26 | 2013-05-01 | 上海卫星工程研究所 | Large-sized embedded complicated small-deformation framework cellular board |
| CN103448304A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | Low-thermal-resistance honeycomb sandwich plate for satellite and manufacturing method of low-thermal-resistance honeycomb sandwich plate |
| CN105065896A (en) * | 2015-07-28 | 2015-11-18 | 中国电子科技集团公司第二十九研究所 | Closed-cell aluminum foam sandwich mounting board of load-carrying structure |
| CN105252768A (en) * | 2015-09-14 | 2016-01-20 | 沈阳飞机工业（集团）有限公司 | Verifying cover plate and verifying method used for formation of special-shaped composite material foam interlayer workpiece |
| CN110077093A (en) * | 2019-04-12 | 2019-08-02 | 北京空间飞行器总体设计部 | A kind of composite material structural slab method for fast mfg and manufacture auxiliary system |
| CN110561841A (en) * | 2019-09-17 | 2019-12-13 | 云南昆船电子设备有限公司 | cellular board capable of bearing concentrated load and processing method thereof |
| CN112895611A (en) * | 2021-02-19 | 2021-06-04 | 航天科工空间工程发展有限公司 | Satellite structure cabin board |
| CN117681503A (en) * | 2023-12-11 | 2024-03-12 | 浙江西子飞机部件有限公司 | Composite board for top plate of hand-push dining car of civil passenger plane |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2735093B1 (en) * | 1995-06-09 | 1997-08-29 | Aerospatiale | COMPOSITE MATERIAL SANDWICH PANEL AND MANUFACTURING METHOD |
| CN2289006Y (en) * | 1997-06-05 | 1998-08-26 | 严坤元 | Aluminium honeycomb sandwich laminate |
| CN1876364A (en) * | 2005-06-08 | 2006-12-13 | 巨科集团有限公司 | Stainless steel, aluminum composite honeycomb panel and processing method |
| CN2855736Y (en) * | 2005-12-15 | 2007-01-10 | 谭新荣 | Vitreous and simasphere honeycomb core type composite colour steel plate |
| CN1820937A (en) * | 2006-03-10 | 2006-08-23 | 大赢数控设备(深圳)有限公司 | Foam aluminium alloy composite material and its use |
-
2007
- 2007-12-25 CN CN 200710172945 patent/CN101468533B/en active Active
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103075629A (en) * | 2011-10-26 | 2013-05-01 | 上海卫星工程研究所 | Large-sized embedded complicated small-deformation framework cellular board |
| CN103075629B (en) * | 2011-10-26 | 2016-07-20 | 上海卫星工程研究所 | A kind of large-scale pre-buried complicated small deformation framework cellular board |
| CN102490910A (en) * | 2011-11-15 | 2012-06-13 | 上海卫星工程研究所 | Composite sandwich-structured bearing cylinder for spacecrafts |
| CN103448304A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | Low-thermal-resistance honeycomb sandwich plate for satellite and manufacturing method of low-thermal-resistance honeycomb sandwich plate |
| CN103448304B (en) * | 2013-08-08 | 2016-06-22 | 上海卫星工程研究所 | A kind of satellite low thermal resistance honeycomb sandwich panel and preparation method thereof |
| CN105065896A (en) * | 2015-07-28 | 2015-11-18 | 中国电子科技集团公司第二十九研究所 | Closed-cell aluminum foam sandwich mounting board of load-carrying structure |
| CN105252768A (en) * | 2015-09-14 | 2016-01-20 | 沈阳飞机工业（集团）有限公司 | Verifying cover plate and verifying method used for formation of special-shaped composite material foam interlayer workpiece |
| CN105252768B (en) * | 2015-09-14 | 2017-06-27 | 沈阳飞机工业（集团）有限公司 | A kind of verification cover plate and method of calibration for the shaping of special-shaped composite foam layer product |
| CN110077093A (en) * | 2019-04-12 | 2019-08-02 | 北京空间飞行器总体设计部 | A kind of composite material structural slab method for fast mfg and manufacture auxiliary system |
| CN110561841A (en) * | 2019-09-17 | 2019-12-13 | 云南昆船电子设备有限公司 | cellular board capable of bearing concentrated load and processing method thereof |
| CN112895611A (en) * | 2021-02-19 | 2021-06-04 | 航天科工空间工程发展有限公司 | Satellite structure cabin board |
| CN117681503A (en) * | 2023-12-11 | 2024-03-12 | 浙江西子飞机部件有限公司 | Composite board for top plate of hand-push dining car of civil passenger plane |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101468533B (en) | 2012-11-28 |
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