CN105459474A - Low-density and high-performance composite sandwich structure and preparation method thereof - Google Patents
Low-density and high-performance composite sandwich structure and preparation method thereof Download PDFInfo
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- CN105459474A CN105459474A CN201510907314.4A CN201510907314A CN105459474A CN 105459474 A CN105459474 A CN 105459474A CN 201510907314 A CN201510907314 A CN 201510907314A CN 105459474 A CN105459474 A CN 105459474A
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- 239000002131 composite material Substances 0.000 title claims abstract description 38
- 238000002360 preparation method Methods 0.000 title claims abstract description 10
- 239000000463 material Substances 0.000 claims description 25
- 229920005989 resin Polymers 0.000 claims description 25
- 239000011347 resin Substances 0.000 claims description 25
- 239000011159 matrix material Substances 0.000 claims description 12
- 150000001875 compounds Chemical class 0.000 claims description 11
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- 229920000049 Carbon (fiber) Polymers 0.000 claims description 7
- 239000004917 carbon fiber Substances 0.000 claims description 7
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 7
- 239000003822 epoxy resin Substances 0.000 claims description 6
- 229920000647 polyepoxide Polymers 0.000 claims description 6
- 239000012528 membrane Substances 0.000 claims description 5
- 238000003491 array Methods 0.000 claims description 4
- 229910052751 metal Inorganic materials 0.000 claims description 4
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- HBGPNLPABVUVKZ-POTXQNELSA-N (1r,3as,4s,5ar,5br,7r,7ar,11ar,11br,13as,13br)-4,7-dihydroxy-3a,5a,5b,8,8,11a-hexamethyl-1-prop-1-en-2-yl-2,3,4,5,6,7,7a,10,11,11b,12,13,13a,13b-tetradecahydro-1h-cyclopenta[a]chrysen-9-one Chemical compound C([C@@]12C)CC(=O)C(C)(C)[C@@H]1[C@H](O)C[C@]([C@]1(C)C[C@@H]3O)(C)[C@@H]2CC[C@H]1[C@@H]1[C@]3(C)CC[C@H]1C(=C)C HBGPNLPABVUVKZ-POTXQNELSA-N 0.000 claims description 2
- PFRGGOIBYLYVKM-UHFFFAOYSA-N 15alpha-hydroxylup-20(29)-en-3-one Natural products CC(=C)C1CCC2(C)CC(O)C3(C)C(CCC4C5(C)CCC(=O)C(C)(C)C5CCC34C)C12 PFRGGOIBYLYVKM-UHFFFAOYSA-N 0.000 claims description 2
- 229920000271 Kevlar® Polymers 0.000 claims description 2
- 239000004696 Poly ether ether ketone Substances 0.000 claims description 2
- SOKRNBGSNZXYIO-UHFFFAOYSA-N Resinone Natural products CC(=C)C1CCC2(C)C(O)CC3(C)C(CCC4C5(C)CCC(=O)C(C)(C)C5CCC34C)C12 SOKRNBGSNZXYIO-UHFFFAOYSA-N 0.000 claims description 2
- JUPQTSLXMOCDHR-UHFFFAOYSA-N benzene-1,4-diol;bis(4-fluorophenyl)methanone Chemical compound OC1=CC=C(O)C=C1.C1=CC(F)=CC=C1C(=O)C1=CC=C(F)C=C1 JUPQTSLXMOCDHR-UHFFFAOYSA-N 0.000 claims description 2
- 229910052799 carbon Inorganic materials 0.000 claims description 2
- 239000004643 cyanate ester Substances 0.000 claims description 2
- 239000003365 glass fiber Substances 0.000 claims description 2
- 239000004761 kevlar Substances 0.000 claims description 2
- 239000013500 performance material Substances 0.000 claims description 2
- 238000000053 physical method Methods 0.000 claims description 2
- 229920013655 poly(bisphenol-A sulfone) Polymers 0.000 claims description 2
- 229920002530 polyetherether ketone Polymers 0.000 claims description 2
- 239000010453 quartz Substances 0.000 claims description 2
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 2
- 229920005992 thermoplastic resin Polymers 0.000 claims description 2
- 229920001187 thermosetting polymer Polymers 0.000 claims description 2
- 239000011162 core material Substances 0.000 abstract description 13
- 239000000805 composite resin Substances 0.000 abstract 2
- 239000010410 layer Substances 0.000 description 20
- 238000007493 shaping process Methods 0.000 description 12
- 238000010276 construction Methods 0.000 description 8
- 238000004026 adhesive bonding Methods 0.000 description 2
- 239000004411 aluminium Substances 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 229920006231 aramid fiber Polymers 0.000 description 2
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
- B32B9/005—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising one layer of ceramic material, e.g. porcelain, ceramic tile
- B32B9/007—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising one layer of ceramic material, e.g. porcelain, ceramic tile comprising carbon, e.g. graphite, composite carbon
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
- B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
- B32B3/18—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by an internal layer formed of separate pieces of material which are juxtaposed side-by-side
- B32B3/20—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by an internal layer formed of separate pieces of material which are juxtaposed side-by-side of hollow pieces, e.g. tubes; of pieces with channels or cavities
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/02—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by a sequence of laminating steps, e.g. by adding new layers at consecutive laminating stations
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/12—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
- B32B7/04—Interconnection of layers
- B32B7/12—Interconnection of layers using interposed adhesives or interposed materials with bonding properties
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
- B32B9/04—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
- B32B2260/02—Composition of the impregnated, bonded or embedded layer
- B32B2260/021—Fibrous or filamentary layer
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
- B32B2260/04—Impregnation, embedding, or binder material
- B32B2260/046—Synthetic resin
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/106—Carbon fibres, e.g. graphite fibres
Landscapes
- Engineering & Computer Science (AREA)
- Ceramic Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Laminated Bodies (AREA)
Abstract
The invention discloses a low-density and high-performance composite sandwich structure and a preparation method thereof. The sandwich structure comprises a core sandwich structure, an upper skin layer arranged on the upper bottom surface of the core sandwich structure and a lower skin layer arranged on the lower bottom surface of the core sandwich structure, wherein the core sandwich structure is formed by arranging a plurality of rod parts in parallel; each rod part is made of a fiber-reinforced resin-based composite. The rod parts made of the fiber-reinforced resin-based composites are spliced in a bonding or physical fixing manner to form the core sandwich structure, so that the core material has designability in mechanical property and hydrothermal property and has formability of complicated molded surfaces, and the high-precision, high-stability and complicated honeycomb sandwich structure is manufactured.
Description
Technical field
What the present invention relates to is a kind of low density and high performance composite material sandwich structure and preparation method thereof, particularly, relates to the preparation method of a kind of low-density, Ultralight, intensity, rigidity and functional programmable composite material sandwich structure.
Background technology
Along with the development of survey of deep space technology, spacecraft operating ambient temperature increasing extent is large, more and more higher to the requirement of platform structure loss of weight, wherein composite material element is the important directions of development in the stability of the medium-sized surface accuracy of space environment and reliability and structure-function integration.
Composite honeycomb core material with metallic plate or composite panel for covering, existing main with metallic aluminium honeycomb, aramid fiber honeycomb for core structure.Be mainly used in honeycomb sandwich construction plate, antenna reflective face, wave transparent radome etc.
Wherein honeycomb sandwich construction plate requires high heat conduction, profile stable accuracy; Antenna reflective face is generally hyperboloid, requires that profile precision is high, good stability of the dimension in space environment.
Aluminium honeycomb good heat conductivity, but thermal coefficient of expansion is large, large with the thermal expansion coefficient difference of composite material skin plate, the two coupling easily causes honeycomb internal stress, in high accuracy honeycomb sandwich construction, heat distortion amount is large, and the change of profile precision greatly, can not meet the required precision of high precision high stability.Aramid fiber comb core thermal coefficient of expansion is little, but heat conductivility is poor, and in space environment, vacuum deflation rate is high, can not meeting spatial environmental applications demand.Two kinds of cores are shaping or are drawn into the shape that sheet material aft-loaded airfoil becomes needs, and difficulty of processing is large, and accessible profile precision is not high.
Summary of the invention
For the defect of prior art, the object of this invention is to provide a kind of low density and high performance composite material sandwich structure and preparation method thereof, fiber-reinforced resin matrix compound material rod member is spliced into sandwich structure by the mode of glueing joint or physics is fixing, make core have designability at mechanical property, Hygrothermal Properties, and there is the formability of complex profile.Realize the manufacture of high accuracy, high stable, labyrinth honeycomb sandwich construction.
The object of the invention is to be achieved through the following technical solutions:
The invention provides a kind of low density and high performance composite material sandwich structure, it is characterized in that, comprise sandwich structure, be arranged at sandwich structure upper bottom surface upper skinning layer and be arranged at the lower skinning layer of sandwich structure bottom surface; Described sandwich structure is formed by multiple rod member laid out in parallel; Described rod member is made up of fiber-reinforced resin matrix compound material.
Preferably, described bar cross section is one or more in circular cross-section, polygonal cross-section, odd-shaped cross section, and rod member inside is hollow structure.
Preferably, the fiber of described fiber-reinforced resin matrix compound material comprises one or more in carbon fiber, glass fibre, quartz fibre, kevlar fiber, PBO; Resin comprise in thermosetting resin, thermoplastic resin one or more.
Preferably, described resin comprises one or more in epoxy resin, cyanate ester resin, PEEK, PSF.
Preferably, described fiber-reinforced resin matrix compound material is carbon fiber reinforced epoxy resin-based composite.The rod member that carbon fiber reinforced epoxy resin-based composite is made is bonded to low density and high performance Composite Sandwich structure, its mechanical property, damp and hot expansion character can design, be easy to shaping, various complex-curved shape can be formed, meet the demand of various mechanisms high-performance sandwich.
Preferably, described rod member height is 0.1mm ~ 1000mm; Rod member wall thickness is 0.01mm ~ 4mm; Diameter 1.0mm ~ 150mm when rod member is circular cross-section, when rod member is polygonal cross-section, the length of side is 0.5mm ~ 20mm.Rod member height is determined by product thickness, and rod member wall thickness, diameter (length of side) are responsible for degree calculating according to extrudate density, bending strength and profile and are determined.
Preferably, connected by one or more modes in splicing or physical method between described rod member and rod member, the gap between rod member and rod member or rod member inside also can light filling foamed material or ablators.Its intensity is improved, the mutual alignment between fixed beam under the low-density prerequisite of guarantee sandwich.
Preferably, described sandwich structure upper bottom surface and upper skinning layer, bottom surface and lower skinning layer all bond each via glued membrane or resin solidification.
Preferably, the density of described sandwich structure is 5kg/m
3~ 180kg/m
3, thermal coefficient of expansion is 0 ~ 10
-5, hygral expansion coefficient is 0 ~ 10
-3, intensity, modulus can design according to the ply sequence of different materials.
Present invention also offers a kind of preparation method of low density and high performance composite material sandwich structure, comprise the following steps:
A, the resin-based satisfied the demands according to composite Materials Design Theoretical Design mechanics, damp and hot and functional performance and reinforcing material and ply sequence, the ply sequence of rod member sandwich layer determine the mechanical property of sandwich layer (as bending, shear), hot expansibility and heat conductivility;
B, by being wound around laying or roll laying, again curing molding fiber-reinforced resin matrix compound material, form long pole;
C, be processed into needs according to profile demand rod member length after, rod member is vertically placed on lower covering, close-packed arrays, then covers covering, by glued membrane, upper and lower covering and rod member are gluedd joint, normal temperature cure; Or
Lower covering prepreg is first laid on mould, then the rod member processed vertically is arranged closely on lower covering, then on rod member upper bottom surface lay covering prepreg, vacuum bag cure;
Obtain low density and high performance composite material sandwich structure.
Preferably, in step B, described winding or roll laying and be specially two-layer or more layer fiber prepreg material is twisted on metal die respectively according to a certain direction.This laying can make Mechanics of Bar performance reach accurate isotropic, and through-thickness thermal conductivity is higher.
The laying angle of rod member can design adjustment, can design the density of sandwich structure, thermal coefficient of expansion, hygral expansion coefficient, intensity, modulus etc.
Preferably, in step C, the described normal temperature cure time is 1-24 hour; The vacuum bag cure time is 1-24 hour, and temperature is 20-200 DEG C.
Preferably, rod member further processing is to 30mm, and bar cross section shape can be circular, and rod member overall diameter 5mm, rod member wall thickness is 0.06mm ~ 4mm.
Between upper and lower covering, place rod member Post RDBMS shaping, develop the honeycomb sandwich construction consistent with skin-covering face.
Sandwich layer of the present invention can for various profile: comprise circle, hexagon, rectangle etc., rod member carries out Lay up design by unidirectional fibre, is namely made up of special ply sequence, and its forming method is for being wound around, rolling or continuously shaped.
The upper and lower covering of the present invention can distinguish shaping after with laminboard layer pass through glued membrane compound, also can with prepreg and sandwich layer co-curing shaping, can guarantee that upper and lower covering is consistent with sandwich layer profile like this, be particularly useful for complex profile (as hyperboloid) composite element.
Compared with prior art, the present invention has following beneficial effect:
1, sandwich material performance is more mated with covering: when sandwich material is carbon fiber enhancement resin base composite material, consistent with the damp and hot expansion character of skin material, can not product internal stress, performance and dimensional accuracy more stable;
2, core material performance designability is strong: can according to user demand, carries out designing and calculating, make structural design optimization to the mechanical property of core material, Hygrothermal Properties, thermal conductivity, density and electrical property etc.;
3, can realize complex-curved manufacture: between upper and lower covering, directly realize the shaping of honeycomb sandwich construction by quarter butt in this invention, rod member can, along complex-curved placement, realize, with the laminating of covering, guaranteeing the profile precision of sandwich.
Accompanying drawing explanation
By reading the detailed description done non-limiting example with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:
Fig. 1 is low density and high performance Composite Sandwich structure sectional view;
Fig. 2 is low density and high performance composite material sandwich structure schematic diagram;
Wherein, 1 is upper skinning layer; 2 is sandwich structure; 3 is lower skinning layer.
Detailed description of the invention
Below in conjunction with specific embodiment, the present invention is described in detail.Following examples will contribute to those skilled in the art and understand the present invention further, but not limit the present invention in any form.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, some distortion and improvement can also be made.These all belong to protection scope of the present invention.
embodiment 1
The shaping sandwich of round bar is an example, and see accompanying drawing 1a and Fig. 2, this sandwich is made up of upper skinning layer 1, lower skinning layer 3 and sandwich structure 2, and described upper skinning layer and lower skinning layer all adopt composite.Sandwich structure 2 is formed by multiple rod member laid out in parallel, the density 60kg/m of rod member
3, flat crushing strength 3.2Mpa, thermal coefficient of expansion 1.7 × 10
-6.
1) design of material
Select sandwich material resin matrix and reinforcing material according to user demand, select T300/3K carbon fiber herein, epoxy resin; Ply sequence is 0/+60/-60.
2) rod member processing and forming
Be that the fiber-reinforced resin matrix compound material prepreg of 0.03mm is cut into strip by thickness in monolayer, one deck 0 degree, one deck+60 is spent, one deck-60 is spent, three layers of fiber prepreg material are twisted on the metal die that overall diameter is 4.8mm according to the direction of 0/+60/-60, after curing molding, by the demoulding of composite rod member, be machined to the quarter butt that length is 20mm.
3) sandwich preformed
Be fixed in frock by lower covering, the composite rod member proper alignment processed is put well on covering, and periphery foxing enclosing, to guarantee sandwich size, covers covering, checks the fit clearance of upper and lower covering and frock;
4) sandwich is shaping
Rubberizing film on upper and lower covering, is placed on working plate by lower covering, and will be placed on lower covering after the rod member lateral wall gluing be pre-installed, close-packed arrays, guarantees to glued joint between rod member, cover covering, solidifies after 24 hours at normal temperatures, removes frock;
5) machined
Honeycomb sandwich construction after shaping can be processed into various shape.
embodiment 2
The sandwich that a kind of regular hexagon bar is shaping.As shown in accompanying drawing 1b, Fig. 2, the density 68kg/m of rod member
3, flat crushing strength 4.6Mpa, thermal coefficient of expansion 1.1 × 10
-6.
1) design of material
Select sandwich material resin matrix and reinforcing material according to user demand, select M55/6K carbon fiber herein, epoxy resin; Ply sequence is 0/90/+45/-45.
2) rod member processing and forming
Be that the fiber-reinforced resin matrix compound material prepreg of 0.15mm is cut into strip by thickness in monolayer, one deck 0 degree, one deck 90 degree, one deck+45 is spent, one deck-45 is spent, and is wrapped on metal die, after curing molding by four layers of fiber prepreg material according to the direction of 0/90/+45/-45 by winding process, by the demoulding of composite rod member, be machined to the quarter butt that length is 60mm.
3) covering and interlayer lay
Lower covering prepreg is laid on mould, the composite rod member proper alignment processed is put well on covering, close-packed arrays, and periphery foxing enclosing is to guarantee sandwich size, covering prepreg on lay, checks the fit clearance of upper and lower covering and frock;
4) sandwich is shaping
Do vacuum bag, baking oven heats, vacuumizes solidification; Solidify after 8 hours at 70 DEG C, remove frock;
5) machined
Honeycomb sandwich construction after shaping can be processed into various shape.
Above specific embodiments of the invention are described.It is to be appreciated that the present invention is not limited to above-mentioned particular implementation, those skilled in the art can make various distortion or amendment within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (10)
1. a low density and high performance composite material sandwich structure, is characterized in that, comprises sandwich structure, is arranged at the upper skinning layer of sandwich structure upper bottom surface and is arranged at the lower skinning layer of sandwich structure bottom surface; Described sandwich structure is formed by multiple rod member laid out in parallel; Described rod member is made up of fiber-reinforced resin matrix compound material.
2. low density and high performance composite material sandwich structure as claimed in claim 1, is characterized in that, described bar cross section is one or more in circular cross-section, polygonal cross-section, odd-shaped cross section, and rod member inside is hollow structure.
3. low density and high performance composite material sandwich structure as claimed in claim 1, is characterized in that, the fiber of described fiber-reinforced resin matrix compound material comprise in carbon fiber, glass fibre, quartz fibre, kevlar fiber, PBO one or more; Resin comprise in thermosetting resin, thermoplastic resin one or more.
4. low density and high performance composite material sandwich structure as claimed in claim 3, is characterized in that, described resin comprise in epoxy resin, cyanate ester resin, PEEK, PSF one or more.
5. low density and high performance composite material sandwich structure as claimed in claim 2, it is characterized in that, described rod member height is 0.1mm ~ 1000mm; Rod member wall thickness is 0.01mm ~ 4mm; External diameter 1.0mm ~ 150mm when rod member is circular cross-section, when rod member is polygonal cross-section, the length of side is 0.5mm ~ 20mm.
6. low density and high performance composite material sandwich structure as claimed in claim 1, it is characterized in that, connected by one or more modes in splicing or physical method between described rod member and rod member, the gap between rod member and rod member or rod member inside can light filling foamed material or ablators.
7. low density and high performance composite material sandwich structure as claimed in claim 1, it is characterized in that, described sandwich structure upper bottom surface and upper skinning layer, bottom surface and lower skinning layer all bond each via glued membrane or resin solidification.
8. a preparation method for low density and high performance composite material sandwich structure as claimed in claim 1, is characterized in that, comprise the following steps:
A, the resin-based satisfied the demands according to composite Materials Design Theoretical Design mechanics, damp and hot and functional performance and reinforcing material and ply sequence;
B, by being wound around laying or roll laying, curing molding fiber-reinforced resin matrix compound material, form long pole;
C, be processed into needs according to profile demand rod member length after, rod member is vertically placed on lower covering, close-packed arrays, then covers covering, by glued membrane, upper and lower covering and rod member are gluedd joint, normal temperature cure; Or
Lower covering prepreg is first laid on mould, then the rod member processed vertically is arranged closely on lower covering, then on rod member upper bottom surface lay covering prepreg, vacuum bag cure;
Obtain low density and high performance composite material sandwich structure.
9. the preparation method of low density and high performance composite material sandwich structure as claimed in claim 8, it is characterized in that, in step B, described winding or roll laying and be specially two-layer or more layer fiber prepreg material is wound around according to a certain direction respectively or twists on metal die.
10. the preparation method of low density and high performance composite material sandwich structure as claimed in claim 8, it is characterized in that, in step C, the described normal temperature cure time is 1-24 hour; The vacuum bag cure time is 1-24h, and temperature is 20-200 DEG C.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510907314.4A CN105459474A (en) | 2015-12-09 | 2015-12-09 | Low-density and high-performance composite sandwich structure and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510907314.4A CN105459474A (en) | 2015-12-09 | 2015-12-09 | Low-density and high-performance composite sandwich structure and preparation method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105459474A true CN105459474A (en) | 2016-04-06 |
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|---|---|---|---|
| CN201510907314.4A Pending CN105459474A (en) | 2015-12-09 | 2015-12-09 | Low-density and high-performance composite sandwich structure and preparation method thereof |
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| Country | Link |
|---|---|
| CN (1) | CN105459474A (en) |
Cited By (10)
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| CN108023180A (en) * | 2017-11-29 | 2018-05-11 | 中国航空工业集团公司济南特种结构研究所 | A kind of antenna house of assorted fibre interlayer |
| CN108791951A (en) * | 2018-03-19 | 2018-11-13 | 中国南方航空股份有限公司 | A method of the anti-push part of aircraft is repaired using ablation |
| CN109796759A (en) * | 2017-11-16 | 2019-05-24 | 长春长光宇航复合材料有限公司 | A kind of high thermal conductivity coefficient cyanate base carbon fiber composite material and preparation method thereof |
| CN110299598A (en) * | 2019-05-24 | 2019-10-01 | 北京卫星制造厂有限公司 | A kind of aramid fiber covering-paper honeycomb interlayer barrel shell structure and its preparation method and application |
| CN111016211A (en) * | 2019-12-04 | 2020-04-17 | 天津爱思达新材料科技有限公司 | Unmanned aerial vehicle radome with lightweight special-shaped structure and forming method thereof |
| CN112537103A (en) * | 2020-04-13 | 2021-03-23 | 廊坊市飞泽复合材料科技有限公司 | Composite material structure of automobile covering part and forming method thereof |
| CN115008847A (en) * | 2022-05-18 | 2022-09-06 | 张长增 | Three-dimensional composite plate shell structure, aircraft, wind power blade shell and manufacturing method |
| CN116118290A (en) * | 2022-11-28 | 2023-05-16 | 上海复合材料科技有限公司 | Reflector structure capable of realizing rapid passive temperature equalization and preparation method thereof |
| CN117565406A (en) * | 2024-01-16 | 2024-02-20 | 成都飞机工业（集团）有限责任公司 | Aluminum alloy skin and honeycomb core gluing method |
| CN118046592A (en) * | 2024-04-15 | 2024-05-17 | 上海复合材料科技有限公司 | Pipe array structure and manufacturing method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109796759A (en) * | 2017-11-16 | 2019-05-24 | 长春长光宇航复合材料有限公司 | A kind of high thermal conductivity coefficient cyanate base carbon fiber composite material and preparation method thereof |
| CN109796759B (en) * | 2017-11-16 | 2021-12-24 | 长春长光宇航复合材料有限公司 | Cyanate ester-based carbon fiber composite material with high thermal conductivity coefficient and preparation method thereof |
| CN108023180A (en) * | 2017-11-29 | 2018-05-11 | 中国航空工业集团公司济南特种结构研究所 | A kind of antenna house of assorted fibre interlayer |
| CN108791951B (en) * | 2018-03-19 | 2022-03-08 | 中国南方航空股份有限公司 | Method for maintaining airplane reverse thrust component by ablation method |
| CN108791951A (en) * | 2018-03-19 | 2018-11-13 | 中国南方航空股份有限公司 | A method of the anti-push part of aircraft is repaired using ablation |
| CN110299598A (en) * | 2019-05-24 | 2019-10-01 | 北京卫星制造厂有限公司 | A kind of aramid fiber covering-paper honeycomb interlayer barrel shell structure and its preparation method and application |
| CN110299598B (en) * | 2019-05-24 | 2021-02-09 | 北京卫星制造厂有限公司 | Aramid fiber skin-paper honeycomb sandwich cylindrical shell structure and preparation method thereof |
| CN111016211A (en) * | 2019-12-04 | 2020-04-17 | 天津爱思达新材料科技有限公司 | Unmanned aerial vehicle radome with lightweight special-shaped structure and forming method thereof |
| CN112537103A (en) * | 2020-04-13 | 2021-03-23 | 廊坊市飞泽复合材料科技有限公司 | Composite material structure of automobile covering part and forming method thereof |
| CN115008847A (en) * | 2022-05-18 | 2022-09-06 | 张长增 | Three-dimensional composite plate shell structure, aircraft, wind power blade shell and manufacturing method |
| CN116118290A (en) * | 2022-11-28 | 2023-05-16 | 上海复合材料科技有限公司 | Reflector structure capable of realizing rapid passive temperature equalization and preparation method thereof |
| CN117565406A (en) * | 2024-01-16 | 2024-02-20 | 成都飞机工业（集团）有限责任公司 | Aluminum alloy skin and honeycomb core gluing method |
| CN117565406B (en) * | 2024-01-16 | 2024-04-12 | 成都飞机工业（集团）有限责任公司 | Aluminum alloy skin and honeycomb core gluing method |
| CN118046592A (en) * | 2024-04-15 | 2024-05-17 | 上海复合材料科技有限公司 | Pipe array structure and manufacturing method thereof |
| CN118046592B (en) * | 2024-04-15 | 2024-07-09 | 上海复合材料科技有限公司 | Pipe array structure and manufacturing method thereof |
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Application publication date: 20160406 |