CN100402278C - Composite section bar of fiber, pure titanium and gold foil, method for producing the same and solidifying mould thereof - Google Patents
Composite section bar of fiber, pure titanium and gold foil, method for producing the same and solidifying mould thereof Download PDFInfo
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- CN100402278C CN100402278C CNB2004100738089A CN200410073808A CN100402278C CN 100402278 C CN100402278 C CN 100402278C CN B2004100738089 A CNB2004100738089 A CN B2004100738089A CN 200410073808 A CN200410073808 A CN 200410073808A CN 100402278 C CN100402278 C CN 100402278C
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Abstract
The present invention relates to a composite section bar of fiber and pure titanium foil, a manufacturing method and a solidification mould thereof. The section bar comprises at least one layer of high-strength high-molding fiber cloth, at least one layer of pure titanium foil, all layers are arranged at intervals and connected by adhesives. In the method, step one is material preparation, and pure titanium foil and the high-strength high-moulding fiber cloth are respectively dipped in the adhesives and cut into the required size; step two is molding, one of materials prepared in step one is rolled and laid on a circumferential layer of a male mould coated with demoulding agents, the other material is subsequently and continuously laid at intervals according to the required number of layers, and then, the material is put in the mould after being rolled, laid and milling milled; step three is solidification, the solidification time is from 2 hours to 24 hours, and the solidification temperature is at the normal temperature or a heating temperature. The solidification mould comprises an upper mould, a lower mould and the male mould. The section bar has circular pipes with thin and thick walls, square pipes, special pipes, U-shaped pipes, single curved surface and double curved surfaces, and can be used as the structural members of fishing poles, structural pipes for kites and flying vehicles. The composite section bar of fiber and pure titanium foil has the advantages of high modulus of elasticity and rigidity and the favorable physical property of impact resistance and shear resistance, and the simple method can be easily operated.
Description
Technical field
The present invention relates to a kind of preparation method and processing mold thereof of layered-type section product, specifically, relate to a kind of fiber-pure titanium foil composite material and manufacture craft and curing mold.
Background technology
Composite is used on structural members such as fishing pole, kite structural tube, aircraft widely.These composites normally with carbon fiber one-way cloth shop layer, are realized the orientation of fibre reinforcement in composite material structural member, the reinforcement of position, bonding part.Also need simultaneously multiple angles,, as 0 °, ± 15 °, ± 30 °, ± 45 °, ± 60 °, 90 ° shop layers, be used for preventing that the stressed back of structural member directional fiber from strengthening body and producing displacement and cause structural member to rupture in advance.Common composite fiber strengthens body, and layer location, shop fiber materials are many, weight is big; Location fiber materials are few, directional fiber strengthens body and is easy to generate displacement ...
Intercalation section, the intercalation section of kite structural tube, multifunction aircraft tail with the made fishing pole of pure carbon fiber unidirectional cloth claim structural tube, spar ... when stressed, be easy to generate splitting, hold and hinder poor performance, the punching of can not slotting, bolt tightening, not shock resistance ...
Summary of the invention
The manufacture craft and the curing mold thereof that the purpose of this invention is to provide a kind of fiber-pure titanium foil composite material.
Fiber of the present invention-pure titanium foil composite material comprises the strong high modulus fiber cloth of at least one floor height and one deck pure titanium foil at least, and place each layer space, and is bonding with viscose glue.
Described high-strength high-modulus fibre cloth is carbon fiber one-way cloth, the two-way woven cloth of carbon fiber, the two-way woven cloth of aramid fiber, the two-way shuffling cloth of carbon fiber/aramid fiber, the two-way woven cloth of high-strength high-modulus polyethylene ballistic fiber, the two-way shuffling of high-strength high-modulus polyethylene (PE) ballistic fiber/carbon fiber is weaved cotton cloth or the two-way shuffling of high-strength high-modulus polyethylene (PE) ballistic fiber/aramid fiber is weaved cotton cloth.
Described viscose glue is epoxide-resin glue, phenolic resin glue, high-strength high-modulus polyethylene (PE) ballistic fiber resin thermal structure glue, high-strength high-modulus polyethylene (PE) ballistic fiber resin normal temperature structure glue, normal temperature cure high-performance organic structure glue or high-intensity inorganic structure glue.
The preparation method of fiber of the present invention-pure titanium foil composite material the steps include:
The first step is got the raw materials ready, and pure titanium foil and high-strength high-modulus fibre cloth separately behind the impregnation, are tailored required size, and this size can be that girth of outer surface of formpiston or two are more than the girth.
Second step was shaped, on formpiston, brush releasing agent, a kind of in the material that makes with step 1, behind volume shop one perisphere on the formpiston of brushing releasing agent, renew the another kind of material in shop, according to the needed number of plies, lay at interval successively, after rolling, the volume shop puts into curing mold, and with bolt that the upper and lower mould of mould is fastening.
The 3rd step solidified, and be 2 hours to 24 hours hardening time, and solidification temperature is to solidify at normal temperatures or heating cure.
Described heating cure is to make temperature be raised to 120-180 ℃ half an hour, and constant temperature one hour cools to 60 ℃ naturally in case, go out to solidify case, the demoulding.
The curing mold of making fiber of the present invention-pure titanium foil composite material comprises upper die and lower die and formpiston.The relative one side of described upper and lower mould is provided with groove, and the shape of this groove and the profile of products made thereby adapt, and the outer surface of described formpiston is consistent with the endoporus of products made thereby or inner surface, and upper and lower mould is provided with the through hole of symmetry, and is fastening with nut.
Method of the present invention also has two and adds die parts, and this adds die parts close formpiston between upper and lower mould, and this cross section that adds die parts is a T shape, and an end of close formpiston is a small end, and its shape is identical with the profile of products made thereby, and its other end is taper.
Described patrix has the bulge loop of the opposite planar that protrudes from upper and lower mould, and its counterdie has and the corresponding groove of the bulge loop of patrix, and the opposite face of bulge loop and groove has tapering.
Described formpiston is divided into a plurality of segmentations according to the outer surface of the section bar of made, spreads the employed material of section bar of required making at the outer surface volume of each segmentation, fits together then, forms the formpiston of required form.
The two ends of described formpiston have shoulder hole, and its aperture is a screwed hole, are provided with spring in the macropore, and the bolt that is set with taper sheath passes spring and is connected with screw, is slidingly connected by feather key between described pre-gland and the formpiston, also has two clips that internal taper hole is arranged.
Fiber of the present invention-pure titanium foil composite material is fit to make fishing pole, kite structural tube, each structural member of aircraft, parts.Each spreads the interbed of layer as fibre reinforcement with isotropic pure titanium foil material for it, can reduce the quantity of location fiber lay down layer that fibre reinforcement produces the change angle shop layer of displacement, made structural member is light more strong, have higher elastic modelling quantity, rigidity, shock resistance, shear-stable physical property, more excellent damage tolerance and residual intensity.Changed the not shock resistance of pure carbon fiber goods, defective such as the punching of can not slotting, bolt tightening.Be more suitable for the requirement of the aeroelasticity modulus structural member of aircraft, reduce the weight of aircraft, increased payload.
By selecting the different environment for use temperature configuration glue and the high-strength high-modulus fibre of different melting temperatures for use, can make fiber-pure titanium foil material for the multiple matrix that strengthens body can-60-500 ℃ operating mode is used superly mixes, the strong composite product of ultralight.Its manufacture craft is simple: pure titanium foil can be made thin-wall circular tube with common formpiston explained hereafter method for strengthening composite material; Also can be with two to the multidirectional position mold pressing of position matched moulds fixed diameter process method system thin-walled, thick-walled tube, square tube, special pipe, U-shaped, single-curved surface, hyperboloid section bar.In the process of mold pressing, curing,, can control the quantitative proportioning that strengthens body (fiber, pure titanium foil) and matrix glue exactly with the appropriate cooperation of diameter of yin, yang mould.The inside and outside footpath of the structural member of being made dimensional accuracy height, each position intensity, rigidity are even.Add the prestressing techniques method and can obtain to internal layer prestressed, advanced composite material (ACM) structural member being arranged by the top layer.
Description of drawings
Fig. 1 is the curing mold structural representation that the present invention makes square tube;
Fig. 2 is the curing mold structural representation that the present invention makes pipe;
Fig. 3 is the curing mold structural representation that the present invention makes special pipe;
Fig. 4 is the curing mold structural representation that the present invention makes similar U spare;
Fig. 5 is the structural representation of an embodiment touching of curing mold middle-jiao yang, function of the spleen and stomach;
Fig. 6 is the A-A profile of Fig. 5.
The specific embodiment
Fiber of the present invention-pure titanium foil composite material comprises the strong high modulus fiber cloth of at least one floor height and one deck pure titanium foil at least, and place each layer space, and is bonding with viscose glue.
Described high-strength high-modulus fibre cloth can be carbon fiber one-way cloth, and its thickness specification has: 0.04,0.075,0.125 or 0.18mm; The two-way woven cloth of carbon fiber, as: plain weave, twill, five heddle satin, 45 ° of stereo weaving cloth of eight pieces of satin weaves or two-way longitude and latitude, or the two-way woven cloth of aramid fiber, this cloth is with warp, weft yarn number set pattern lattice, have: 420,1100,1680 ... or the two-way shuffling cloth of carbon fiber/aramid fiber, this cloth is with thousand modulus set patterns of carbon fiber lattice, have: 1K, 3K, 6K or 12K, or the two-way woven cloth of high-strength high-modulus polyethylene (PE) ballistic fiber, this cloth is with warp, weft yarn number set pattern lattice have: 160,200,300,320,440,1100,1600 ... or the two-way shuffling of high-strength high-modulus polyethylene (PE) ballistic fiber/carbon fiber is weaved cotton cloth, or the two-way shuffling of high-strength high-modulus polyethylene (PE) ballistic fiber/aramid fiber is weaved cotton cloth.
The viscose glue that is adopted can be epoxide-resin glue, phenolic resin glue, high-strength high-modulus polyethylene (PE) ballistic fiber resin thermal structure glue, high-strength high-modulus polyethylene (PE) ballistic fiber resin normal temperature structure glue, normal temperature cure high-performance organic structure glue or high-intensity inorganic structure glue.
Fiber of the present invention-pure titanium foil composite material is tubing or U-shaped like material or T shape material.Described tubing can be pipe, square tube, rectangular tube or special pipe.Various materials can be made each structural member or the parts of fishing pole, kite structural tube, aircraft.
The step of the method for the invention is:
The first step is got the raw materials ready.
Pure titanium foil and high-strength high-modulus fibre cloth separately behind the impregnation, are tailored required size, and this size can be that girth of outer surface of formpiston or two are more than the girth;
When the section bar of made was one deck high-strength high-modulus fibre cloth and one deck pure titanium foil, two kinds of materials can be cut into a girth of formpiston outer surface respectively.If two-layer high-strength high-modulus fibre and one deck pure titanium foil, then high-strength high-modulus fibre need be cut out two girths into the formpiston outer surface, and pure titanium foil is cut out and is a girth of formpiston outer surface.If in the time of need being produced on the section bar that accompanies high-strength high-modulus fibre cloth in the two-layer pure titanium foil, pure titanium foil then carries two girths into the formpiston outer surface, high-strength high-modulus fibre cloth is cut out and is a girth of formpiston outer surface.
When making the heavy wall section bar, described formpiston outer surface should be the actual outer surface of the layer of spreading, so the size of " the formpiston outer surface girth " of each material is along with the increase of wall thickness changes.
In second step, be shaped.
On formpiston, brush releasing agent, a kind of in the material that makes with step 1, behind volume shop one perisphere on the formpiston of brushing releasing agent, renew the another kind of material in shop, according to the needed number of plies, the interval lay is put into curing mold after roll the volume shop successively, and is with bolt that the upper and lower mould of mould is fastening.
When the viscose glue that adopts is normal temperature cure high-performance organic structure glue and high-intensity inorganic structure glue, must be within behind pure titanium foil and the high-strength high-modulus fibre cloth impregnation 20 minutes fastening finishing.
The 3rd step, to solidify, be 2 hours to 24 hours hardening time, solidification temperature is to solidify at normal temperatures or heat to 120 ℃-180 ℃.
When the viscose glue that uses during as normal temperature cure high-performance organic structure glue and high-intensity inorganic structure glue, the fastening mould that the second step operation obtains keeps die sinking after 24 hours at normal temperatures.When if viscose glue is epoxy resin, high-strength high-modulus polyethylene (PE) ballistic fiber resin, phenolic resins, the fastening mould of the second step gained need be put into and solidify the case heating cure.
Described heating cure is to make temperature be raised to 120-180 ℃ half an hour, and constant temperature one hour cools to 60 ℃ naturally in case, go out to solidify case, the demoulding.
When wherein adopting epoxide-resin glue, solidification temperature is 140 ℃, and when adopting phenolic resins, its solidification temperature is 180 ℃, and when adopting high-strength high-modulus polyethylene (PE) ballistic fiber resin high-temp glue glue, its solidification temperature is 120 ℃.
Referring to Fig. 1 and Fig. 2, curing mold of the present invention comprises upper module 1, lower module 5 and sun (core) mould 4.Described upper and lower mould 1,5 relative one sides are provided with groove, and the shape of this groove can be rectangle, semicircle or the shape that adapts with the profile of products made thereby, and the outer surface of described formpiston 4 is consistent with the endoporus of products made thereby or inner surface.Upper and lower mould 1,5 is provided with the through hole of a plurality of symmetries, and bolt 6 passes through hole, uses nut screwing clamping.
Mould of the present invention also has two and adds die parts 2, and this adds die parts between upper and lower mould 1,5, near formpiston 4.This cross section that adds die parts 2 is a T shape, end near formpiston is a small end, its shape is identical with the profile of products made thereby, can be circular arc or planar shaped, its other end, promptly big end is taper, in fastening process, the extruding of upper and lower mould adds the tapering point of die parts, by multidirectional position mold pressing sizing, can make each layer of strengthening body 3, each position in conjunction with tight more, intensity is consistent with rigidity.
Referring to Fig. 3, the figure shows the curing mold of processing U-shaped like thing.The patrix of this mould has the bulge loop 13 of the opposite planar that protrudes from upper and lower mould 1,5, its counterdie has and the corresponding groove of the bulge loop of patrix, and the opposite face of bulge loop and groove has tapering, when pressurization, because the cooperation of bulge loop and groove makes the tight more and formpiston applying of work piece.
Referring to Fig. 4, the figure shows the curing mold of working special-shaped pipe.The formpiston 4 of this mould is divided into a plurality of segmentations according to the outer surface of the section bar of made, at the outer surface volume shop of each segmentation fiber-pure titanium foil composite 7, fits together then, forms the formpiston of required form.In a plurality of segmentations, one or two contact-making surface of one of them segmentation and adjacent sectional is the inclined plane, the segmentation face of face contact matches with its gradient therewith, under can the pressure when matched moulds, produce multidirectional position mold pressing sizing, make the whole covering of the two-way woven cloth of outer high-strength high-modulus fibre, middle closed type composite structure section bar 14, promptly foregoing enhancing body 3 by a plurality of enhancing body combinations.
Referring to Fig. 5 and Fig. 6, the two ends of described formpiston 4 have shoulder hole, its aperture is a screwed hole, be provided with spring 8 in the macropore, bolt 9 passes spring and is connected with screw, is set with the pre-gland 11 with conical head on bolt, be slidingly connected by feather key 10 between described pre-gland 11 and the formpiston 4, feather key can be singly-bound, two key or spline, also comprises two clips 12 with internal taper hole, and the hole taper of this clip is identical with the tapering of the conical head of pre-gland.When rolling up the shop, when the preimpregnation material prolongation of the volume required making in shop is uncured above the conical surface of pre-gland 11, clip 12 tightly is enclosed within on the pre-gland 11, loosens nut 9 then, can produce pulling force, make prestressing force section bar 3.
During use, bolt 9 is screwed into makes spring 8 compression in the screw, volume is spread impregnation then, pure titanium foil or fiber cloth after volume is completed, are contained in hoop sleeve on the taper module of finishing the shop layer, unclamp bolt, promptly discharge and have prestressed stage clip, be cured among putting into mould.Through the composite that prestressing techniques is handled, the fibre bundle of directed shop layer has stress, can bring into play the highest physical property of each bundle fiber of directed shop layer fully.Can prevent effectively that structural member from producing fracture in advance in stressed back.
With pure titanium foil and carbon cloth, as a kind of epoxide-resin glue that is soaked with separately in unidirectional cloth, two-way braiding plain weave, twill, five heddle satin, eight pieces of satin weaves or the two-way 45 stereo weaving cloth, making is the multidirectional position mold pressing of the pre-impregnated fabric fixed diameter process pipe that two perisphere carbon fibers of matrix are furnished with pure titanium foil material interlayer with epoxy resin.
To be soaked with the carbon cloth of epoxide-resin glue, be cut into length, be soaked with the pure titanium foil of epoxide-resin glue, cut out to having the length of an outer surface girth of formpiston with two outer surface girths of formpiston; Cross in precoating on the formpiston of releasing agent, there is the carbon cloth of two outer surface girths to spread volume sanction and is layered on a perisphere on the formpiston, titanium foil is tiled on another all carbon fiber one-way cloth that volume is spread, be put into to roll to roll up on the platform machine to spread and roll, put into curing mold then, with bolt that upper and lower module is fastening, put into again and solidify case, be warmed up to 140 ℃ half an hour, constant temperature solidified in one hour, in case, cool to 60 ℃ naturally, go out to solidify case, the demoulding.
Carbon cloth among this embodiment can with the two-way woven cloth of aramid fiber or two-way shuffling cloth of carbon fiber/aramid fiber or the two-way woven cloth of high-strength high-modulus polyethylene (PE) ballistic fiber or the two-way shuffling of high-strength high-modulus polyethylene (PE) ballistic fiber/carbon fiber be weaved cotton cloth or the two-way shuffling of high-strength high-modulus polyethylene (PE) ballistic fiber/aramid fiber is weaved cotton cloth alternative.
Be soaked with high-strength high-modulus polyethylene (PE) ballistic fiber resin glue separately with pure titanium foil and the two-way woven cloth of high-strength high-modulus polyethylene (PE) ballistic fiber, making with high-strength high-modulus polyethylene (PE) ballistic fiber resin glue is the multidirectional position of the pre-impregnated fabric die-pressing section that the two-way braiding of two perisphere high-strength high-modulus polyethylene (PE) ballistic fibers of matrix is furnished with pure titanium foil material interlayer.
The two-way woven cloth of high-strength high-modulus polyethylene (PE) ballistic fiber that is soaked with epoxide-resin glue is cut into the length of an outer surface girth with formpiston, and the pure titanium foil that will be soaked with high-strength high-modulus polyethylene (PE) ballistic fiber resin glue is cut out to having the length of two outer surface girths of formpiston; On the formpiston of brushing releasing agent in advance, at first pure titanium foil material volume is layered on the formpiston behind the perisphere, the two-way woven cloth of PE fiber of one perisphere is tiled in another girth of not rolling up the shop does not roll up on the pure titanium foil material of shop, continuation rolls rolling on the platform machine volume shop, make the uncured section bar of pure titanium foil material of (PE) fibrous interlayer, put into mould then, with bolt that upper and lower mould idol part is fastening, put into again and solidify case, be warmed up to 120 ℃ half an hour, constant temperature solidified in one hour, cooled to 60 ℃ in case naturally, go out to solidify case, the demoulding.
The two-way woven cloth of high-strength high-modulus polyethylene among this embodiment (PE) ballistic fiber can with various carbon cloths or two-way woven cloth of aramid fiber or the two-way shuffling cloth of carbon fiber/aramid fiber or the two-way shuffling of high-strength high-modulus polyethylene (PE) ballistic fiber/carbon fiber be weaved cotton cloth or the two-way shuffling of high-strength high-modulus polyethylene (PE) ballistic fiber/aramid fiber is weaved cotton cloth alternative.
Being soaked with separately with pure titanium foil and the two-way volume cloth of aramid fiber that phenolic resin glue makes with phenolic resins is the multidirectional position mold pressing of the pre-impregnated fabric fixed diameter process pipe that the two-way woven cloth of two perisphere aramid fibers of matrix has pure titanium foil material interlayer.
With the two-way woven cloth of the aramid fiber that is soaked with phenolic resin glue, be cut into length in advance with two outer surface girths of formpiston, be soaked with the pure titanium foil of phenolic resin glue, the pre-sanction to having the length of an outer surface girth of formpiston.Cross in precoating on the formpiston of releasing agent, there is the two-way woven cloth of the aramid fiber of two perisphere shop volume to be layered on the formpiston behind the perisphere sanction, titanium foil is tiled on the two-way woven cloth of another all aramid fiber that volume is not spread, be put into to roll to roll up on the platform machine to spread and roll, make the two-way braiding of the aramid fiber section bar pre-impregnated fabric, uncured of pure titanium foil interlayer, put into mould then, with bolt that upper and lower mould idol piece is fastening, put into again and solidify case, be warmed up to 180 ℃ half an hour, constant temperature solidified in one hour, cooled to 60 ℃ in case naturally, outlet, the demoulding.
The two-way woven cloth of aramid fiber among this embodiment can with various carbon cloths or two-way shuffling cloth of carbon fiber/aramid fiber or the two-way woven cloth of high-strength high-modulus polyethylene (PE) ballistic fiber or the two-way shuffling of high-strength high-modulus polyethylene (PE) ballistic fiber/carbon fiber be weaved cotton cloth or the two-way shuffling of high-strength high-modulus polyethylene (PE) ballistic fiber/aramid fiber is weaved cotton cloth alternative.
Being soaked with normal temperature cure high-performance organic structure glue separately with pure titanium foil and the two-way shuffling cloth of carbon fiber/aramid fiber, to make with normal temperature cure high performance structures glue be the multidirectional position mold pressing of the pre-impregnated fabric fixed diameter process pipe that two perisphere pure titanium foil materials of matrix have the two-way shuffling cloth of carbon fiber/aramid fiber interlayer.
The two-way shuffling cloth of carbon fiber/aramid fiber of normal temperature cure high-performance organic structure glue will be soaked with, be cut into length in advance with two outer surface girths of formpiston, be soaked with normal temperature cure high performance structures glue pure titanium foil, the pre-sanction to having the length of an outer surface girth of formpiston; Cross in precoating on the formpiston of releasing agent, there is the two-way shuffling yardage roll of carbon fiber/aramid fiber of two perisphere to be layered on a perisphere on the formpiston sanction, titanium foil is tiled on the two-way shuffling cloth of another all carbon fiber/aramid fiber that volume is not spread, be put into to roll to roll up on the platform machine to spread and roll, make carbon fiber/aramid fiber section bar two-way shuffling cloth, uncured of pure titanium foil interlayer, put into mould then, with bolt that upper and lower mould idol piece is fastening in 20 minutes, the demoulding after 24 hours reached maximum intensity in 72 hours.Described normal temperature cure high performance structures glue also available epoxy glue or phenolic resin as matrix resin substitutes.
The two-way shuffling cloth of carbon fiber/aramid fiber among this embodiment can with various carbon cloths or two-way woven cloth of aramid fiber or the two-way woven cloth of high-strength high-modulus polyethylene (PE) ballistic fiber or the two-way shuffling of high-strength high-modulus polyethylene (PE) ballistic fiber/carbon fiber be weaved cotton cloth or the two-way shuffling of high-strength high-modulus polyethylene (PE) ballistic fiber/aramid fiber is weaved cotton cloth alternative.
The normal temperature cure high-performance organic structure glue that is adopted can use high-strength high-modulus polyethylene (PE) ballistic fiber resin normal temperature glue, normal temperature cure high-performance organic structure glue or high-intensity inorganic structure glue for band.
Above-mentioned four embodiment make thin-wall section, make the heavy wall section bar as need, only need employed material is cut into the length that the made number of plies needs, and according to the preceding method operation, can obtain the heavy wall section bar.
Section bar of the present invention, with the pure titanium foil is the fibre reinforcement interbed, can make up arbitrarily with carbon cloth, the two-way woven cloth of aramid fiber, the two-way shuffling cloth of carbon fiber/aramid fiber or the two-way woven cloth of high-strength high-modulus polyethylene (PE) ballistic fiber, in with a kind of product, can use a kind of in the above-mentioned material, also can use in the above-mentioned material two or more.
The present invention has adopted the matrix (epoxy resin, phenolic resins, normal temp solidified high stvength structure glue, high-intensity inorganic structure glue) of multiple composite can make the composite product that heat curing-type, normal temperature cured type are the fibre reinforcement interbed with the pure titanium foil (pure titanium foil can use-60 ° of-500 ℃ of work condition environments midium or long terms).Also can make the pre-impregnated fabric of bi-component that the silicate inorganic thing forms to the two-way woven cloth of high-modules carbon fibre and make ultralight strong (can in the medium-term and long-term uses of 1700 ℃ of work condition environments) composite material structural member, parts with multidirectional position mold pressing sizing mould.
With high-strength high-modulus fibre/pure titanium foil material is the strong composite of multidirectional position mold pressing sizing prestressed super-light, technology, the mould that strengthens body, can produce that high elastic modulus more, rigidity, shock resistance, anti-shearing, excellent damage tolerance and residual intensity superly mix, the strong composite product of ultralight, be more suitable for structural member, parts that aeroelasticity modulus multi-functional, special device requires.
Claims (7)
1. the preparation method of fiber one pure titanium foil composite material the steps include:
The first step is got the raw materials ready, and pure titanium foil and high-strength high-modulus fibre cloth separately behind the impregnation, are tailored required size, and this size can be that girth of outer surface of formpiston or two are more than the girth;
Second step was shaped, on formpiston, brush releasing agent, a kind of in the material that makes with step 1, behind volume shop one perisphere on the formpiston of brushing releasing agent, renew the another kind of material in shop, according to the needed number of plies, lay at interval successively, after rolling, the volume shop puts into curing mold, and with bolt that the upper and lower mould of mould is fastening;
The 3rd step solidified, and be 2 hours to 24 hours hardening time, and solidification temperature is to solidify at normal temperatures or heating cure.
2. preparation method according to claim 1 is characterized in that described heating cure is to make temperature be raised to 120-180 ℃ half an hour, and constant temperature one hour cools to 60 ℃ naturally in case, go out to solidify case, the demoulding.
3. make the curing mold of fiber-pure titanium foil composite material, it is characterized in that comprising patrix (1), counterdie (5) and formpiston (4).The relative one side of described upper and lower mould (1,5) is provided with groove, the shape of this groove and the profile of products made thereby adapt, the outer surface of described formpiston (5) is consistent with the endoporus or the inner surface of products made thereby, and upper and lower mould (1,5) is provided with the through hole of symmetry, and is fastening with nut.
4. curing mold according to claim 3, it is characterized in that also having two and add die parts (2), this adds die parts and is positioned between the upper and lower mould (1,5) near formpiston (5), this cross section that adds die parts (2) is a T shape, end near formpiston is a small end, its shape is identical with the profile of products made thereby, and its other end is taper.
5. curing mold according to claim 3 is characterized in that described patrix has the bulge loop of the opposite planar that protrudes from upper and lower mould (1,5), and its counterdie has and the corresponding groove of the bulge loop of patrix, and the opposite face of bulge loop and groove has tapering.
6. curing mold according to claim 3, it is characterized in that described formpiston is divided into a plurality of segmentations according to the outer surface of the section bar of made, outer surface volume in each segmentation is spread the employed material of section bar of required making, fits together then, forms the formpiston of required form.
7. curing mold according to claim 3, the two ends that it is characterized in that described formpiston have shoulder hole, its aperture is a screwed hole, be provided with spring in the macropore, the bolt that is set with taper sheath passes spring and is connected with screw, be slidingly connected by feather key (10) between described pre-gland (11) and the formpiston (4), also have two clips (12) that internal taper hole is arranged.
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| Application Number | Priority Date | Filing Date | Title |
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| CNB2004100738089A CN100402278C (en) | 2004-09-01 | 2004-09-01 | Composite section bar of fiber, pure titanium and gold foil, method for producing the same and solidifying mould thereof |
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| CNB2004100738089A CN100402278C (en) | 2004-09-01 | 2004-09-01 | Composite section bar of fiber, pure titanium and gold foil, method for producing the same and solidifying mould thereof |
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| CN100402278C true CN100402278C (en) | 2008-07-16 |
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| CN106965505A (en) * | 2017-05-19 | 2017-07-21 | 南京航空航天大学 | Enhanced Fiber Reinforced Metal Laminates of superhigh molecular weight polyethylene fibers and preparation method thereof |
| CN111618940B (en) * | 2020-06-05 | 2022-02-08 | 浙江万丰飞机制造有限公司 | Novel civil aircraft wing maintenance cover hole drilling tool manufacturing process |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1080590A (en) * | 1992-07-03 | 1994-01-12 | 中国科学院金属研究所 | Vinylon strengthened aluminium alloy laminated composited material and preparation method |
| JP2001073103A (en) * | 1999-09-02 | 2001-03-21 | Ishikawajima Harima Heavy Ind Co Ltd | Manufacture of parts made of titanium matrix composite and furnace for manufacturing the same |
| US6730412B2 (en) * | 2001-10-29 | 2004-05-04 | Mitsubishi Heavy Industries, Ltd. | Metal matrix composite |
-
2004
- 2004-09-01 CN CNB2004100738089A patent/CN100402278C/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1080590A (en) * | 1992-07-03 | 1994-01-12 | 中国科学院金属研究所 | Vinylon strengthened aluminium alloy laminated composited material and preparation method |
| JP2001073103A (en) * | 1999-09-02 | 2001-03-21 | Ishikawajima Harima Heavy Ind Co Ltd | Manufacture of parts made of titanium matrix composite and furnace for manufacturing the same |
| US6730412B2 (en) * | 2001-10-29 | 2004-05-04 | Mitsubishi Heavy Industries, Ltd. | Metal matrix composite |
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| CN1733470A (en) | 2006-02-15 |
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