CN101973129A - Method for manufacturing composite material dot matrix laminboard by adopting fiber woven prepreg cloth - Google Patents
Method for manufacturing composite material dot matrix laminboard by adopting fiber woven prepreg cloth Download PDFInfo
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- CN101973129A CN101973129A CN201010522716XA CN201010522716A CN101973129A CN 101973129 A CN101973129 A CN 101973129A CN 201010522716X A CN201010522716X A CN 201010522716XA CN 201010522716 A CN201010522716 A CN 201010522716A CN 101973129 A CN101973129 A CN 101973129A
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Abstract
The invention discloses a method for manufacturing a composite material dot matrix laminboard by adopting fiber woven prepreg cloth and relates to a method for manufacturing a composite material dot matrix laminboard, aiming to solve the problems that the traditional fiber weaving method cannot be used for integral molding, the fiber bar piece structural property of the manufactured dot matrix laminboard is poor, and quantity production cannot be realized. The method comprises two schemes, wherein the first scheme comprises the following steps of: manufacturing a die; preparing two-way fiber weaving prepreg cloth; shearing the fiber weaving prepreg cloth according to the structure and the size of the die; treating; assembling a lower die; laying the fiber weaving prepreg cloth; laying silicon rubber; closing the dies; removing the dies; and forming the dot matrix laminboard structure. The second scheme is different from the first scheme in that the structure of the lower die is different from that in the first scheme. The invention is used for manufacturing the dot matrix laminboard.
Description
Technical field
The present invention relates to a kind of method for preparing composite dot-matrix sandwich panel.
Background technology
The preparation fiber reinforced composite dot matrix core board mainly contains several several down at present: mold hot platen press, assembly jig method, fibrage method, mechanical construction from part are arranged.The problem that analyze to exist respectively below: the shortcoming of mold hot platen press is that the fuse part is not a global formation, and rod member can not apply enough pressure, and rod member is embedded in the panel, and counter plate causes initial damage easily; The shortcoming of assembly jig method is that the node bond area is too little; The shortcoming of machinery construction from part be rod member in working angles, have error easily, bring rigging error to structure easily during interlocking like this, also there is the too little problem of bond area in the while.
Existing fibrage method can't global formation and the fiber rod member of the dot-matrix sandwich panel made thinner, can not give full play to fibre-reinforced characteristics; Because complex manufacturing process can't realize changing in batches product.
Summary of the invention
The fiber rod member structural behaviour of the dot-matrix sandwich panel that the objective of the invention is can't global formation in order to solve existing fibrage method, make is relatively poor and can't realize the problem of mass production providing a kind of method that adopts fibrage preimpregnation cloth to prepare composite dot-matrix sandwich panel.
The present invention is achieved by following proposal: scheme one: step 1: the preparation mould: mould is made of a plurality of counterdies and a plurality of patrix, the shape of cross section of each counterdie and patrix is trapezoidal, the many first party connected in stars of processing on an inclined-plane of each counterdie to connecting along this surface width direction, every pair of first party connected in star is the splayed setting, many with every pair of first party connected in star opposite position place processing on another inclined-plane of each counterdie to second party connected in stars along this surface width direction perforation, every pair of second party connected in star is the splayed setting, and the material of mould is a silicon rubber; Step 2, preparation two are to fibrage preimpregnation cloth: the position of square groove in according to mould, utilize filament preparation two to fibrage preimpregnation cloth; Step 3, according to mould structure and size, cutting fibrage preimpregnation cloth: utilize composite automatic cutting machines or engraving machine, be cut into the regulation shape to fibrage preimpregnation cloth with two; Step 4, processing, assembling counterdie: the outer surface that adopts mold cleaning agent or acetone soln cleaning die, then hole sealing agent and releasing agent are spread upon on the outer surface of mould successively, with anchor clamps a plurality of counterdies are fixed, the distance between per two counterdies is identical with the width of the upper surface of patrix; Step 5, lay down fibre braiding preimpregnation cloth: the fibrage preimpregnation cloth integral body that obtains in the step 2 successively is laid in the step 4 handle, in the counterdie after the assembling in the upper surface, second party connected in star of corresponding first party connected in star, counterdie and between two counterdies with the opposite position place, upper surface of patrix; Step 6, lay silicon rubber: after treating that fibrage preimpregnation cloth lay finishes, lay silicon rubber slice in first party connected in star and second party connected in star, the slice size is consistent with the width and the length of first party connected in star and second party connected in star; Step 7, matched moulds: the alternate tiling with counterdie of patrix is provided with the formation tabular, structural member after counterdie and the last die combination is placed on the cure under pressure of heating in the hot press, solidification temperature is 100～200 ℃, and solidifying pressure is 0.5～2Mpa, and be 1～3 hour hardening time; Step 8, the demoulding: the patrix after solidifying in the step 7 is pulled down, taken out composite dot-matrix sandwich, obtain composite dot-matrix sandwich; Step 9, formation truss core structure: composite laminated plate on the upper and lower end of the dot matrix fuse that obtains in step 7 respectively is bonding makes the composite dot-matrix sandwich structure.
Scheme two: step 1: the preparation mould: mould is made of a plurality of counterdies and a plurality of patrix, the shape of cross section of each counterdie and patrix is trapezoidal, the many first party connected in stars of processing on an inclined-plane of each counterdie to connecting along this surface width direction, every pair of first party connected in star is the splayed setting, the a plurality of third party's connected in stars that connect along this surface width direction of processing on another inclined-plane of each counterdie, the central axis of each third party's connected in star and every pair of first party connected in star is symmetrical arranged along the central axis of the upper surface of counterdie, and the material of mould is a silicon rubber; Step 2, preparation two are to fibrage preimpregnation cloth: the position of square groove in according to mould, utilize filament preparation two to fibrage preimpregnation cloth; Step 3, according to mould structure and size, cutting fibrage preimpregnation cloth: utilize composite automatic cutting machines or engraving machine, be cut into the regulation shape to fibrage preimpregnation cloth with two; Step 4, processing, assembling counterdie: the outer surface that adopts mold cleaning agent or acetone soln cleaning die, then hole sealing agent and releasing agent are spread upon on the outer surface of mould successively, with anchor clamps a plurality of counterdies are fixed, the distance between per two counterdies is identical with the width of the upper surface of patrix; Step 5, lay down fibre braiding preimpregnation cloth: the fibrage preimpregnation cloth integral body that obtains in the step 2 successively is laid in the step 4 handle, in the counterdie after the assembling in the upper surface, third party's connected in star of corresponding first party connected in star, counterdie and between two counterdies with the opposite position place, upper surface of patrix; Step 6, lay silicon rubber: after treating that fibrage preimpregnation cloth lay finishes, lay silicon rubber slice in first party connected in star and second party connected in star, the slice size is consistent with the width and the length of first party connected in star and second party connected in star; Step 7, matched moulds: the alternate tiling with counterdie of patrix is provided with the formation tabular, structural member after counterdie and the last die combination is placed on the cure under pressure of heating in the hot press, solidification temperature is 100～200 ℃, and solidifying pressure is 0.5～2Mpa, and be 1～3 hour hardening time; Step 8, the demoulding: the patrix after solidifying in the step 7 is pulled down, taken out composite dot-matrix sandwich, obtain composite dot-matrix sandwich; Step 9, formation truss core structure: composite laminated plate on the upper and lower end of the dot matrix fuse that obtains in step 7 respectively is bonding makes the composite dot-matrix sandwich structure.
The present invention compared with prior art has following beneficial effect: 1. the inventive method technology realizes simply utilizing fibrage preimpregnation cloth integral body to be laid in the mould, gets final product global formation dot matrix fuse; 2. the dot-matrix sandwich panel structural behaviour of the present invention's acquisition significantly improves, the rod member of dot matrix filled board is at enough forming under the pressure, and fuse part fiber is continuous, overall performance is strong, face external compression performance is 2 to 3 times of mould heat pressure forming method, and bond area can be adjusted, and so just can design bond area according to working condition requirement; 3. the inventive method can realize mass production, because fibrage preimpregnation cloth is automation mechanized operation, be easy to the big fibrage preimpregnation cloth of cutting area, integral body is placed in the mould, and be whole large tracts of land one-shot forming, can realize mass like this, reduce cost, promote the engineering practice.
Description of drawings
Fig. 1 is the structural representation of counterdie in the scheme one, Fig. 2 is the structural representation of patrix in the scheme one, Fig. 3 is in the specific embodiment one behind the step 7 matched moulds, the side structure schematic diagram of mould and fibrage preimpregnation cloth, Fig. 4 is the cross-sectional structure schematic diagram of the mould of the specific embodiment one, Fig. 5 is the structural representation of composite dot-matrix sandwich that step 8 obtains in the specific embodiment one, Fig. 6 is the structural representation of the fibrage preimpregnation cloth after the step 3 cutting in the specific embodiment one, Fig. 7 is the structural representation of counterdie in the scheme two, Fig. 8 is the structural representation of patrix in the scheme two, Fig. 9 is in the specific embodiment four behind the step 7 matched moulds, the side structure schematic diagram of mould and fibrage preimpregnation cloth, Figure 10 is the cross-sectional structure schematic diagram of mould in the specific embodiment four, Figure 11 is the structural representation of composite dot-matrix sandwich that step 8 obtains in the specific embodiment four, and Figure 12 is the structural representation of the fibrage preimpregnation cloth after the step 3 cutting in the specific embodiment four.
The specific embodiment
The specific embodiment one: specify present embodiment below in conjunction with Fig. 1-Fig. 6, the preparation method of present embodiment is finished by following steps:
Step 1: the preparation mould: mould is made of a plurality of counterdies 1 and a plurality of patrix 2, the shape of cross section of each counterdie 1 and patrix 2 is trapezoidal, the many first party connected in star 1-1 of processing on an inclined-plane of each counterdie 1 to connecting along this surface width direction, every couple of first party connected in star 1-1 is the splayed setting, many with every pair of first party connected in star 1-1 opposite position place processing on another inclined-plane of each counterdie 1 to second party connected in star 1-2 along this surface width direction perforation, every couple of second party connected in star 1-2 is the splayed setting, and the material of mould is a silicon rubber;
Mould adopts silastic material, is convenient to the mould pressurization and the demoulding.
Copy the mature technology of preparation 0/90 fibrage preimpregnation cloth, the fiber of both direction is woven according to every couple of first party connected in star 1-1 in the counterdie 1 and the orientation of every couple of second party connected in star 1-2, guarantee that every couple of first party connected in star 1-1 and every couple of second party connected in star 1-2 have identical fibrage preimpregnation cloth orientation, woven cloth must weave along 45/-45, cut, when putting into first party connected in star 1-1 and second party connected in star 1-2, just can take into account first party connected in star 1-1 and have identical mechanical property with second party connected in star 1-2; This step need guarantee two when fiber cloth is placed among first party connected in star 1-1 and the second party connected in star 1-2, along the direction of rod member the filament of maximum quantity is arranged, and two rod members has identical fiber orientation among the every couple of first party connected in star 1-1 and the every couple of second party connected in star 1-2;
Step 4, processing, assembling counterdie: the outer surface that adopts mold cleaning agent or acetone soln cleaning die, then hole sealing agent and releasing agent are spread upon on the outer surface of mould successively, with anchor clamps a plurality of counterdies 1 are fixed, the distance between per two counterdies 1 is identical with the width of the upper surface of patrix 2;
Step 5, lay down fibre braiding preimpregnation cloth: fibrage preimpregnation cloth 3 integral body that obtain in the step 2 successively are laid in the step 4 handle, in the counterdie after the assembling in the upper surface, second party connected in star 1-2 of corresponding first party connected in star 1-1, counterdie 1 and between two counterdies 1 with the opposite position place, upper surface of patrix 2;
Step 6, lay silicon rubber: after treating that fibrage preimpregnation cloth 3 laies finish, lay silicon rubber slice in first party connected in star 1-1 and second party connected in star 1-2, the slice size is consistent with width and the length of first party connected in star 1-1 and second party connected in star 1-2;
The thickness of slice size can be according to the thickness adjustment of fibrage preimpregnation cloth among first party connected in star 1-1 and the second party connected in star 1-2;
Step 7, matched moulds: patrix 2 and counterdie 1 alternate tiling are provided with the formation tabular, structural member after counterdie 1 and patrix 2 combinations is placed on the cure under pressure of heating in the hot press, solidification temperature is 100～200 ℃, and solidifying pressure is 0.5～2Mpa, and be 1～3 hour hardening time;
Step 8, the demoulding: the patrix 2 after solidifying in the step 7 is pulled down, taken out composite dot-matrix sandwich, obtain composite dot-matrix sandwich;
Step 9, formation truss core structure: composite laminated plate on the upper and lower end of the dot matrix fuse that obtains in step 7 respectively is bonding makes the composite dot-matrix sandwich structure.
The dot-matrix sandwich panel that present embodiment is prepared is the composite dot-matrix sandwich panel with three rod members.
The specific embodiment two: the material of fibrage preimpregnation cloth 3 is an epoxy resin in the step 2 of present embodiment.Other method step is identical with the specific embodiment one.
The specific embodiment three: solidification temperature is 120 ℃ in the step 7 of present embodiment, and solidifying pressure is 0.5Mpa, and be 1.5 hours hardening time.The solidification temperature of present embodiment, solidifying pressure and hardening time are to set according to the material of the fibre knitting cloth described in the step 1.Other method step is identical with the specific embodiment one or two.
The specific embodiment four: specify present embodiment below in conjunction with Fig. 7-Figure 12, the preparation method of present embodiment is finished by following steps: step 1: the preparation mould: mould is made of a plurality of counterdies 1 and a plurality of patrix 2, the shape of cross section of each counterdie 1 and patrix 2 is trapezoidal, the many first party connected in star 1-1 of processing on an inclined-plane of each counterdie 1 to connecting along this surface width direction, every couple of first party connected in star 1-1 is the splayed setting, the a plurality of third party's connected in star 1-3 that connect along this surface width direction of processing on another inclined-plane of each counterdie 1, the central axis of each third party's connected in star 1-3 and every couple of first party connected in star 1-1 is symmetrical arranged along the central axis of the upper surface of counterdie, and the material of mould is a silicon rubber;
Mould adopts silastic material, is convenient to the mould pressurization and the demoulding.
Copy the mature technology of preparation 0/90 fibrage preimpregnation cloth, the fiber of both direction is woven according to every couple of first party connected in star 1-1 in the counterdie 1 and the orientation of every couple of second party connected in star 1-2, guarantee that every couple of first party connected in star 1-1 and every couple of second party connected in star 1-2 have identical fibrage preimpregnation cloth orientation, woven cloth must weave along 45/-45, cut, when putting into first party connected in star 1-1 and second party connected in star 1-2, just can take into account first party connected in star 1-1 and have identical mechanical property with second party connected in star 1-2; This step need guarantee two when fiber cloth is placed among first party connected in star 1-1 and the second party connected in star 1-2, along the direction of rod member the filament of maximum quantity is arranged, and two rod members has identical fiber orientation among the every couple of first party connected in star 1-1 and the every couple of second party connected in star 1-2;
Step 4, processing, assembling counterdie: the outer surface that adopts mold cleaning agent or acetone soln cleaning die, then hole sealing agent and releasing agent are spread upon on the outer surface of mould successively, with anchor clamps a plurality of counterdies 1 are fixed, the distance between per two counterdies 1 is identical with the width of the upper surface of patrix 2;
Step 5, lay down fibre braiding preimpregnation cloth: fibrage preimpregnation cloth 3 integral body that obtain in the step 2 successively are laid in the step 4 handle, in the counterdie after the assembling in the upper surface, third party's connected in star 1-3 of corresponding first party connected in star 1-1, counterdie 1 and between two counterdies 1 with the opposite position place, upper surface of patrix 2;
Step 6, lay silicon rubber: after treating that fibrage preimpregnation cloth 3 laies finish, lay silicon rubber slice in first party connected in star 1-1 and second party connected in star 1-2, the slice size is consistent with width and the length of first party connected in star 1-1 and second party connected in star 1-2;
The slice size is consistent with width and the length of first party connected in star 1-1 and second party connected in star 1-2;
Step 7, matched moulds: patrix 2 and counterdie 1 alternate tiling are provided with the formation tabular, structural member after counterdie 1 and patrix 2 combinations is placed on the cure under pressure of heating in the hot press, solidification temperature is 100～200 ℃, and solidifying pressure is 0.5～2Mpa, and be 1～3 hour hardening time;
Step 8, the demoulding: the patrix 2 after solidifying in the step 7 is pulled down, taken out composite dot-matrix sandwich, obtain composite dot-matrix sandwich;
Step 9, formation truss core structure: composite laminated plate on the upper and lower end of the dot matrix fuse that obtains in step 7 respectively is bonding makes the composite dot-matrix sandwich structure.
This specific embodiment and the difference of the specific embodiment one are different according to the square groove quantity of processing in the bed die 1, prepare the different composite dot-matrix sandwich panel of rod member quantity, the dot-matrix sandwich panel that present embodiment is prepared is the composite dot-matrix sandwich panel with four rod members.
The specific embodiment five: the material of fibrage preimpregnation cloth 3 is an epoxy resin in the step 2 of present embodiment.Other method step is identical with the specific embodiment four.
The specific embodiment six: the solidification temperature described in the step 7 of present embodiment is 120 ℃, and solidifying pressure is 0.5Mpa, and be 1.5 hours hardening time.Other method step is identical with the specific embodiment four or five.
Claims (6)
1. method that adopts fibrage preimpregnation cloth to prepare composite dot-matrix sandwich panel is characterized in that described preparation method is finished by following steps:
Step 1: preparation mould: mould is made of a plurality of counterdies (1) and a plurality of patrix (2), the shape of cross section of each counterdie (1) and patrix (2) is trapezoidal, the many first party connected in stars (1-1) of processing on an inclined-plane of each counterdie (1) to connecting along this surface width direction, every pair of first party connected in star (1-1) is the splayed setting, many with the processing of every pair of first party connected in star (1-1) opposite position place on another inclined-plane of each counterdie (1) to second party connected in stars (1-2) along this surface width direction perforation, every pair of second party connected in star (1-2) is the splayed setting, and the material of mould is a silicon rubber;
Step 2, preparation two are to fibrage preimpregnation cloth: the position of square groove in according to mould, utilize filament preparation two to fibrage preimpregnation cloth (3);
Step 3, according to mould structure and size, cutting fibrage preimpregnation cloth: utilize composite automatic cutting machines or engraving machine, be cut into the regulation shape to fibrage preimpregnation cloth (3) with two;
Step 4, processing, assembling counterdie: the outer surface that adopts mold cleaning agent or acetone soln cleaning die, then hole sealing agent and releasing agent are spread upon on the outer surface of mould successively, with anchor clamps that a plurality of counterdies (1) are fixing, the distance between per two counterdies (1) is identical with the width of the upper surface of patrix (2);
Step 5, lay down fibre braiding preimpregnation cloth: with the fibrage preimpregnation cloth (3) that obtains in the step 2 whole successively be laid in the step 4 handle, in the counterdie after the assembling in the upper surface, second party connected in star (1-2) of corresponding first party connected in star (1-1), counterdie (1) and between two counterdies (1) with the opposite position place, upper surface of patrix (2);
Step 6, lay silicon rubber: after treating that fibrage preimpregnation cloth (3) lay finishes, lay silicon rubber slice in first party connected in star (1-1) and second party connected in star (1-2), the slice size is consistent with the width and the length of first party connected in star (1-1) and second party connected in star (1-2);
Step 7, matched moulds: patrix (2) and the alternate tiling of counterdie (1) are provided with the formation tabular, structural member after counterdie (1) and patrix (2) combination is placed on the cure under pressure of heating in the hot press, solidification temperature is 100～200 ℃, and solidifying pressure is 0.5～2Mpa, and be 1～3 hour hardening time;
Step 8, the demoulding: the patrix (2) after solidifying in the step 7 is pulled down, taken out composite dot-matrix sandwich, obtain composite dot-matrix sandwich;
Step 9, formation truss core structure: composite laminated plate on the upper and lower end of the dot matrix fuse that obtains in step 7 respectively is bonding makes the composite dot-matrix sandwich structure.
2. prepare the method for composite dot-matrix sandwich panel according to the described employing fibrage of claim 1 preimpregnation cloth, the material that it is characterized in that fibrage preimpregnation cloth (3) in the step 2 is an epoxy resin.
3. prepare the method for composite dot-matrix sandwich panel according to claim 1 or 2 described employing fibrage preimpregnation cloth, it is characterized in that the solidification temperature described in the step 7 is 120 ℃, solidifying pressure is 0.5Mpa, and be 1.5 hours hardening time.
4. method that adopts fibrage preimpregnation cloth to prepare composite dot-matrix sandwich panel is characterized in that described preparation method is finished by following steps:
Step 1: preparation mould: mould is made of a plurality of counterdies (1) and a plurality of patrix (2), the shape of cross section of each counterdie (1) and patrix (2) is trapezoidal, the many first party connected in stars (1-1) of processing on an inclined-plane of each counterdie (1) to connecting along this surface width direction, every pair of first party connected in star (1-1) is the splayed setting, the a plurality of third party's connected in stars (1-3) that connect along this surface width direction of processing on another inclined-plane of each counterdie (1), the central axis of each third party's connected in star (1-3) and every pair of first party connected in star (1-1) is symmetrical arranged along the central axis of the upper surface of counterdie, and the material of mould is a silicon rubber;
Step 2, preparation two are to fibrage preimpregnation cloth: the position of square groove in according to mould, utilize filament preparation two to fibrage preimpregnation cloth (3);
Step 3, according to mould structure and size, cutting fibrage preimpregnation cloth: utilize composite automatic cutting machines or engraving machine, be cut into the regulation shape to fibrage preimpregnation cloth (3) with two;
Step 4, processing, assembling counterdie: the outer surface that adopts mold cleaning agent or acetone soln cleaning die, then hole sealing agent and releasing agent are spread upon on the outer surface of mould successively, with anchor clamps that a plurality of counterdies (1) are fixing, the distance between per two counterdies (1) is identical with the width of the upper surface of patrix (2);
Step 5, lay down fibre braiding preimpregnation cloth: with the fibrage preimpregnation cloth (3) that obtains in the step 2 whole successively be laid in the step 4 handle, in the counterdie after the assembling in the upper surface, third party's connected in star (1-3) of corresponding first party connected in star (1-1), counterdie (1) and between two counterdies (1) with the opposite position place, upper surface of patrix (2);
Step 6, lay silicon rubber: after treating that fibrage preimpregnation cloth (3) lay finishes, lay silicon rubber slice in first party connected in star (1-1) and second party connected in star (1-2), the slice size is consistent with the width and the length of first party connected in star (1-1) and second party connected in star (1-2);
Step 7, matched moulds: patrix (2) and the alternate tiling of counterdie (1) are provided with the formation tabular, structural member after counterdie (1) and patrix (2) combination is placed on the cure under pressure of heating in the hot press, solidification temperature is 100～200 ℃, and solidifying pressure is 0.5～2Mpa, and be 1～3 hour hardening time;
Step 8, the demoulding: the patrix (2) after solidifying in the step 7 is pulled down, taken out composite dot-matrix sandwich, obtain composite dot-matrix sandwich;
Step 9, formation truss core structure: composite laminated plate on the upper and lower end of the dot matrix fuse that obtains in step 7 respectively is bonding makes the composite dot-matrix sandwich structure.
5. prepare the method for composite dot-matrix sandwich panel according to the described employing fibre knitting cloth of claim 4, the material that it is characterized in that fibrage preimpregnation cloth 3 in the step 2 is an epoxy resin.
6. prepare the method for composite dot-matrix sandwich panel according to claim 4 or 5 described employing fibrage preimpregnation cloth, it is characterized in that the solidification temperature described in the step 7 is 120 ℃, solidifying pressure is 0.5Mpa, and be 1.5 hours hardening time.
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| CN 201010522716 CN101973129B (en) | 2010-10-28 | 2010-10-28 | Method for manufacturing composite material dot matrix laminboard by adopting fiber woven prepreg cloth |
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| CN 201010522716 CN101973129B (en) | 2010-10-28 | 2010-10-28 | Method for manufacturing composite material dot matrix laminboard by adopting fiber woven prepreg cloth |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102275305A (en) * | 2011-04-29 | 2011-12-14 | 哈尔滨工业大学 | Method and mold for manufacturing dot matrix core and composite cylinder provided with matrix core |
| CN102785371A (en) * | 2012-08-28 | 2012-11-21 | 哈尔滨工业大学 | Method for making composite material lattice sandwich boards by prepreg fiber bundles |
| CN105196565A (en) * | 2015-09-23 | 2015-12-30 | 哈尔滨工业大学 | Pyramid-shaped lattice sandwich shell made of composites and preparation method of pyramid-shaped lattice core sandwich shell |
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| CN105479772A (en) * | 2016-01-20 | 2016-04-13 | 南京工业大学 | Quasi-three dimensional enhanced composite dot matrix interlayer structure and manufacturing method thereof |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5326513A (en) * | 1989-03-08 | 1994-07-05 | Sto Poraver Gmbh | Process and device for the production of plastic fiber boards |
| US20060093791A1 (en) * | 2004-10-29 | 2006-05-04 | Snell Mary E | Multi-layered structural corrosion resistant composite liner |
| CN101003190A (en) * | 2007-01-22 | 2007-07-25 | 哈尔滨工业大学 | Fiber enhanced foam core filled composite material plate, and fabricating method |
| CN101122362A (en) * | 2007-09-19 | 2008-02-13 | 哈尔滨工业大学 | Fibre-reinforced composite lattice sandwich plate and its preparing process |
| CN101708659A (en) * | 2009-10-30 | 2010-05-19 | 哈尔滨工业大学 | Fiber reinforced composite dot matrix core board mold and wet method preparation process |
-
2010
- 2010-10-28 CN CN 201010522716 patent/CN101973129B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5326513A (en) * | 1989-03-08 | 1994-07-05 | Sto Poraver Gmbh | Process and device for the production of plastic fiber boards |
| US20060093791A1 (en) * | 2004-10-29 | 2006-05-04 | Snell Mary E | Multi-layered structural corrosion resistant composite liner |
| CN101003190A (en) * | 2007-01-22 | 2007-07-25 | 哈尔滨工业大学 | Fiber enhanced foam core filled composite material plate, and fabricating method |
| CN101122362A (en) * | 2007-09-19 | 2008-02-13 | 哈尔滨工业大学 | Fibre-reinforced composite lattice sandwich plate and its preparing process |
| CN101708659A (en) * | 2009-10-30 | 2010-05-19 | 哈尔滨工业大学 | Fiber reinforced composite dot matrix core board mold and wet method preparation process |
Cited By (11)
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|---|---|---|---|---|
| CN102275305A (en) * | 2011-04-29 | 2011-12-14 | 哈尔滨工业大学 | Method and mold for manufacturing dot matrix core and composite cylinder provided with matrix core |
| CN102785371A (en) * | 2012-08-28 | 2012-11-21 | 哈尔滨工业大学 | Method for making composite material lattice sandwich boards by prepreg fiber bundles |
| CN102785371B (en) * | 2012-08-28 | 2014-08-13 | 哈尔滨工业大学 | Method for making composite material lattice sandwich boards by prepreg fiber bundles |
| CN105196565A (en) * | 2015-09-23 | 2015-12-30 | 哈尔滨工业大学 | Pyramid-shaped lattice sandwich shell made of composites and preparation method of pyramid-shaped lattice core sandwich shell |
| CN105241751A (en) * | 2015-09-28 | 2016-01-13 | 哈尔滨工业大学 | Assembly clamper for sandwich structure board lateral compression test |
| CN105241751B (en) * | 2015-09-28 | 2017-11-03 | 哈尔滨工业大学 | A kind of assembling fixture for sandwich structure plate lateral pressure test |
| CN105479772A (en) * | 2016-01-20 | 2016-04-13 | 南京工业大学 | Quasi-three dimensional enhanced composite dot matrix interlayer structure and manufacturing method thereof |
| CN106752020A (en) * | 2017-03-06 | 2017-05-31 | 东北林业大学 | A kind of preparation method of string reinforced resin based composites lattice structure |
| CN107599445A (en) * | 2017-09-08 | 2018-01-19 | 哈尔滨工程大学 | A kind of composite material dot matrix structure and preparation method |
| CN114083725A (en) * | 2021-11-19 | 2022-02-25 | 哈尔滨工业大学 | Mold for preparing pyramid lattice core and preparation method of pyramid lattice core |
| CN114083725B (en) * | 2021-11-19 | 2023-01-13 | 哈尔滨工业大学 | Mold for preparing pyramid lattice core and preparation method of pyramid lattice core |
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