CN107336502A - A kind of preparation method of winged flying vehicle compartment board - Google Patents
A kind of preparation method of winged flying vehicle compartment board Download PDFInfo
- Publication number
- CN107336502A CN107336502A CN201710643826.3A CN201710643826A CN107336502A CN 107336502 A CN107336502 A CN 107336502A CN 201710643826 A CN201710643826 A CN 201710643826A CN 107336502 A CN107336502 A CN 107336502A
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- sheet material
- preparation
- vehicle compartment
- flying vehicle
- thermoplastic
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- 238000002360 preparation method Methods 0.000 title claims abstract description 18
- 239000000463 material Substances 0.000 claims abstract description 52
- 230000001413 cellular effect Effects 0.000 claims abstract description 18
- 150000001875 compounds Chemical class 0.000 claims abstract description 17
- 239000002131 composite material Substances 0.000 claims abstract description 14
- -1 polypropylene Polymers 0.000 claims abstract description 11
- 229920001169 thermoplastic Polymers 0.000 claims abstract description 11
- 239000004416 thermosoftening plastic Substances 0.000 claims abstract description 11
- 239000011199 continuous fiber reinforced thermoplastic Substances 0.000 claims abstract description 10
- 239000004743 Polypropylene Substances 0.000 claims abstract description 8
- 229920001155 polypropylene Polymers 0.000 claims abstract description 8
- 238000000034 method Methods 0.000 claims abstract description 4
- 238000007789 sealing Methods 0.000 claims abstract description 4
- 238000001816 cooling Methods 0.000 claims description 19
- 238000005452 bending Methods 0.000 claims description 16
- 239000000835 fiber Substances 0.000 claims description 15
- 239000005038 ethylene vinyl acetate Substances 0.000 claims description 12
- 239000003365 glass fiber Substances 0.000 claims description 12
- 229920001200 poly(ethylene-vinyl acetate) Polymers 0.000 claims description 12
- 239000012528 membrane Substances 0.000 claims description 10
- 229920005992 thermoplastic resin Polymers 0.000 claims description 7
- 229920000877 Melamine resin Polymers 0.000 claims description 6
- 229920001971 elastomer Polymers 0.000 claims description 6
- 239000000806 elastomer Substances 0.000 claims description 6
- JDSHMPZPIAZGSV-UHFFFAOYSA-N melamine Chemical compound NC1=NC(N)=NC(N)=N1 JDSHMPZPIAZGSV-UHFFFAOYSA-N 0.000 claims description 6
- 238000000465 moulding Methods 0.000 claims description 6
- 229920005989 resin Polymers 0.000 claims description 6
- 239000011347 resin Substances 0.000 claims description 6
- 238000004804 winding Methods 0.000 claims description 6
- 238000010438 heat treatment Methods 0.000 claims description 4
- 238000013329 compounding Methods 0.000 claims description 3
- FPYJFEHAWHCUMM-UHFFFAOYSA-N maleic anhydride Chemical compound O=C1OC(=O)C=C1 FPYJFEHAWHCUMM-UHFFFAOYSA-N 0.000 claims description 3
- 238000002844 melting Methods 0.000 claims description 3
- 230000008018 melting Effects 0.000 claims description 3
- 238000001125 extrusion Methods 0.000 claims 1
- 230000002787 reinforcement Effects 0.000 claims 1
- 230000008901 benefit Effects 0.000 abstract description 5
- 229910000831 Steel Inorganic materials 0.000 abstract description 4
- 238000005516 engineering process Methods 0.000 abstract description 4
- 239000010959 steel Substances 0.000 abstract description 4
- 239000002344 surface layer Substances 0.000 abstract description 3
- 238000005265 energy consumption Methods 0.000 abstract description 2
- 239000011152 fibreglass Substances 0.000 abstract description 2
- 238000009434 installation Methods 0.000 abstract description 2
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 239000002861 polymer material Substances 0.000 abstract description 2
- 239000011162 core material Substances 0.000 description 13
- 239000011521 glass Substances 0.000 description 5
- 239000010410 layer Substances 0.000 description 4
- 239000004925 Acrylic resin Substances 0.000 description 3
- 229920000178 Acrylic resin Polymers 0.000 description 3
- 238000007664 blowing Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000007493 shaping process Methods 0.000 description 3
- 241000256844 Apis mellifera Species 0.000 description 2
- 239000002313 adhesive film Substances 0.000 description 2
- 238000005520 cutting process Methods 0.000 description 2
- HDERJYVLTPVNRI-UHFFFAOYSA-N ethene;ethenyl acetate Chemical compound C=C.CC(=O)OC=C HDERJYVLTPVNRI-UHFFFAOYSA-N 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000032683 aging Effects 0.000 description 1
- 238000010924 continuous production Methods 0.000 description 1
- 229920001577 copolymer Polymers 0.000 description 1
- 230000008595 infiltration Effects 0.000 description 1
- 238000001764 infiltration Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229920000642 polymer Polymers 0.000 description 1
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
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/06—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the heating method
-
- 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
- B32B37/08—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the cooling method
-
- 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
- B32B37/1207—Heat-activated adhesive
-
- 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
- B32B38/00—Ancillary operations in connection with laminating processes
- B32B38/04—Punching, slitting or perforating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B62—LAND VEHICLES FOR TRAVELLING OTHERWISE THAN ON RAILS
- B62D—MOTOR VEHICLES; TRAILERS
- B62D33/00—Superstructures for load-carrying vehicles
- B62D33/04—Enclosed load compartments ; Frameworks for movable panels, tarpaulins or side curtains
-
- 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
- B32B37/1207—Heat-activated adhesive
- B32B2037/1215—Hot-melt adhesive
-
- 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
- B32B38/00—Ancillary operations in connection with laminating processes
- B32B38/04—Punching, slitting or perforating
- B32B2038/045—Slitting
-
- 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
- B32B2255/00—Coating on the layer surface
- B32B2255/02—Coating on the layer surface on 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
- B32B2255/00—Coating on the layer surface
- B32B2255/26—Polymeric coating
-
- 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
- B32B2262/101—Glass fibres
-
- 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
- B32B2307/00—Properties of the layers or laminate
- B32B2307/70—Other properties
- B32B2307/718—Weight, e.g. weight per square meter
-
- 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
- B32B2307/00—Properties of the layers or laminate
- B32B2307/70—Other properties
- B32B2307/72—Density
-
- 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
- B32B2307/00—Properties of the layers or laminate
- B32B2307/70—Other properties
- B32B2307/726—Permeability to liquids, absorption
- B32B2307/7265—Non-permeable
-
- 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
- B32B2323/00—Polyalkenes
- B32B2323/10—Polypropylene
-
- 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
- B32B2331/00—Polyvinylesters
- B32B2331/04—Polymers of vinyl acetate, e.g. PVA
-
- 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
- B32B2398/00—Unspecified macromolecular compounds
- B32B2398/20—Thermoplastics
-
- 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
- B32B2605/00—Vehicles
- B32B2605/08—Cars
Abstract
The invention belongs to compartment sheet material preparing technical field, is related to a kind of preparation method of compartment board high polymer material, more particularly to a kind of preparation method of winged flying vehicle compartment board；Its preparation technology specifically include prepare prepreg tape, prepare thermoplastic meet sheet material, prepare cellular board, fluting the step such as sealing and leveling pad pasting；Sheet material carries out compound, resulting materials intensity height in material selection using continuous fiber reinforced thermoplastic composite material with cellular board material, in performance fiberglass can be substituted to rivet steel plate completely, and the density of material is small, quality is lighter, and traveling is more fuel-efficient, and economic benefit is obvious.Sheet material uses polypropylene material surface layer, more plays waterproof action；Obtained sheet material institute technique is simple, and workable, continuity is good, efficiency high, by the way of heat joins, reduces the hardening time of tradition splicing, reduces the energy consumption during production, improve efficiency；Obtained sheet material uses integral structure, makes its installation simple, convenient.
Description
Technical field：
The invention belongs to compartment sheet material preparing technical field, is related to a kind of preparation method of compartment board high polymer material, special
It is not related to a kind of preparation method of winged flying vehicle compartment board.
Background technology：
Winged flying vehicle is the improvement of common van, manually device or hydraulic means, can open compartment wing plates on two sides
Special-purpose vehicle, because it has, handling speed is fast, efficiency high, can side access the advantages that, be modern resources-flow enterprises very
The means of transport of favor.Because in recent years, a large amount of lightweight new material applications are in span car series so that compartment deadweight reduces, and adds
Cabin design it is attractive in appearance, cargo transportation security is reliable, it is contemplated that will be occupied a tiny space in high-end logistics transportation market.The car two
Flank plate liftable, 90 ° are opened, both sides position is opened wide completely, greatly facilitate handling goods, double back doors can also open 270
Degree.The car entire vehicle design is unique, rational in infrastructure, good appearance.The both wings side plate material of winged flying vehicle uses surface glass mostly at present
Glass steel surface, inner layer steel plate, is fixed by rivet and section bar, is made, and especially in wing plate circular arc, connection is more, when long
Between after use, easily there is connection and crack, phenomena such as infiltration, long this can impact to the use in compartment, increase the use of car owner
Cost.Therefore, seeking to design a kind of preparation method of winged flying vehicle compartment board has good Social benefit and economic benefit.
The content of the invention：
It is an object of the invention to overcome above-mentioned the shortcomings of the prior art, there is provided a kind of high intensity, ageing-resistant, weight
Light suitable continuous production, the preparation method of winged flying vehicle compartment board made of the thermoplastic composite of efficiency high.
To achieve these goals, the preparation technology of winged flying vehicle compartment board of the present invention specifically includes following steps：
(1) prepreg tape is prepared
Glass fibre is exported by creel according to weight proportion and spread out to 150-350g/m2Surface density, so
It is coated afterwards with extruding the thermoplastic resin of melting by weight ratio, then winding is crimped after mould molding, is obtained
Thickness is 0.15-0.35mm, and simple tension intensity is 600-1000MPa continuous lod prepreg tape；Wherein glass fibre
Parts by weight with thermoplastic resin are：Glass fibre 50-70 parts, thermoplastic is as resin 30-50 parts；
(2) prepare thermoplastic and meet sheet material
Continuous lod prepreg tape made from (1) and Polar Crystal Slab are positioned on unwinding rack, the non-polar plane of Polar Crystal Slab
It is bonded with continuous lod prepreg tape, traction flattening-out is then carried out with 3-8m/min speed, then be by heating-up temperature
190-220 DEG C of baking oven heating, the number of plies that then Compound cooling is fixed to that thickness is 0.3-1.05mm is that the multilayer of 2-5 layers is continuous
Fiber reinforced thermolplastic composite material sheet material；
(3) cellular board is prepared
Obtained multilayer continuous fiber reinforced thermoplastic composite material sheet material in step (2) is cut, then with honeybee
Nest core is placed in compounding machine, and 180-220 DEG C of preheating is carried out under 1.5-3.5/min hauling speed, then carry out it is compound, it is cold
But the continuous lod cellular board that the thickness for obtaining being covered with polarity film surface afterwards is 20-40mm；
(4) fluting sealing
By continuous lod cellular board obtained in step (3), according to angle 0-90°, width 6-18mm opened
Groove, then glued membrane is put into groove, the sheet material after fluting is positioned on mould bases, after carrying out pressure bending, heat gun temperature is set
Spend and be heat-treated 30-60s for the gap of 130-160 DEG C of cross-notching, then with carrying out splicing processing at the split notch of thermosol gelgun,
Keep bending state under cooling until temperature be down to less than 35 DEG C, obtain bending sheets；
(5) leveling pad pasting
Vestige after bending sheets prepared by step (4) are handled thermosol gelgun with flatiron plates, finally on its surface
Pad pasting is carried out, is got product.
The present invention relates to the step of (1) in thermoplastic resin be selected from HOPP, one kind in COPP or
It is several.
The present invention relates to the step of (2) in Polar Crystal Slab be addition maleic anhydride inoculated polypropylene film, ethene-vinyl acetate is common
One kind in polymers (EVA) or elastomer (POE).
The present invention relates to the step of (2) in multilayer continuous fiber reinforced thermoplastic composite material sheet material structure laying be 0/
One or more in 90,0/90/0,90/0/90,0/90/0/90,0/90/90/0,0/90/0/90/0,90/0/90/0/90.
The present invention relates to the step of (3) in honeycomb core material be selected from polypropylene, the aperture of the honeycomb core is 6-12mm, institute
The grammes per square metre for stating honeycomb core is 60-120g/m2, the honeycomb core thickness is 20-40mm.
The present invention relates to the step of (4) in glued membrane in ethylene-vinyl acetate copolymer (EVA) or elastomer (POE)
One kind.
The present invention relates to the step of (4) in pad pasting be melamine film or phenolic aldehyde film.
The present invention compared with prior art, sheet material material selection on using continuous fiber reinforced thermoplastic composite material with
Cellular board material carries out compound, and resulting materials intensity is high, and fiberglass can be substituted to rivet steel plate in performance completely, and material
Density is small, and quality is lighter, and traveling is more fuel-efficient, and economic benefit is obvious.Sheet material uses polypropylene material surface layer, more plays waterproof work
With；Obtained sheet material institute technique is simple, and workable, continuity is good, efficiency high, by the way of heat joins, reduces
The hardening time that tradition is glued, the energy consumption during production is reduced, improves efficiency；Obtained sheet material uses integral type knot
Structure, make its installation simple, it is convenient.
Brief description of the drawings：
Fig. 1 is wing plate schematic diagram.
Fig. 2 is plate cutting fluting schematic diagram.
Fig. 3 is cutting groove on sheet angle and width indication figure.
Fig. 4 is sheet metal bending schematic diagram.
Embodiment：
The present invention will be further described by way of example and in conjunction with the accompanying drawings.
The preparation technology for the winged flying vehicle compartment board that the present embodiment is related to specifically includes following steps：
(1) prepreg tape is prepared
Glass fibre is exported by creel according to weight proportion and spread out to 150-350g/m2Surface density, so
It is coated afterwards with extruding the thermoplastic resin of melting by weight ratio, then winding is crimped after mould molding, is obtained
Thickness is 0.15-0.35mm, and simple tension intensity is 600-1000MPa continuous lod prepreg tape；Wherein glass fibre
Parts by weight with thermoplastic resin are：Glass fibre 50-70 parts, thermoplastic is as resin 30-50 parts；
(2) prepare thermoplastic and meet sheet material
Continuous lod prepreg tape made from (1) and Polar Crystal Slab are positioned on unwinding rack, the non-polar plane of Polar Crystal Slab
It is bonded with continuous lod prepreg tape, traction flattening-out is then carried out with 3-8m/min speed, then be by heating-up temperature
190-220 DEG C of baking oven heating, the number of plies that then Compound cooling is fixed to that thickness is 0.3-1.05mm is that the multilayer of 2-5 layers is continuous
Fiber reinforced thermolplastic composite material sheet material；
(3) cellular board is prepared
Obtained multilayer continuous fiber reinforced thermoplastic composite material sheet material in step (2) is cut, then with honeybee
Nest core is placed in compounding machine, and 180-220 DEG C of preheating is carried out under 1.5-3.5/min hauling speed, then carry out it is compound, it is cold
But the continuous lod cellular board that the thickness for obtaining being covered with polarity film surface afterwards is 20-40mm；
(4) fluting sealing
By continuous lod cellular board obtained in step (3), according to angle 0-90°, width 6-18mm opened
Groove, then glued membrane is put into groove, the sheet material after fluting is positioned on mould bases, after carrying out pressure bending, heat gun temperature is set
Spend and be heat-treated 30-60s for the gap of 130-160 DEG C of cross-notching, then with carrying out splicing processing at the split notch of thermosol gelgun,
Keep bending state under cooling until temperature be down to less than 35 DEG C, obtain bending sheets；
(5) leveling pad pasting
Vestige after bending sheets prepared by step (4) are handled thermosol gelgun with flatiron plates, finally on its surface
Pad pasting is carried out, is got product.
Thermoplastic resin in the step of the present embodiment is related to (1) is selected from HOPP, one kind in COPP
It is or several.
Polar Crystal Slab is to add maleic anhydride inoculated polypropylene film, ethene-vinyl acetate in the step of the present embodiment is related to (2)
One kind in copolymer (EVA) or elastomer (POE).
The structure laying of multilayer continuous fiber reinforced thermoplastic composite material sheet material is in the step of the present embodiment is related to (2)
One kind or several in 0/90,0/90/0,90/0/90,0/90/0/90,0/90/90/0,0/90/0/90/0,90/0/90/0/90
Kind.
Honeycomb core material is selected from polypropylene in the step of the present embodiment is related to (3), and the aperture of the honeycomb core is 6-12mm,
The grammes per square metre of the honeycomb core is 60-120g/m2, the honeycomb core thickness is 20-40mm.
Glued membrane in the step of the present embodiment is related to (4) is ethylene-vinyl acetate copolymer (EVA) or elastomer (POE)
In one kind.
Pad pasting in the step of the present embodiment is related to (4) is melamine film or phenolic aldehyde film.
Embodiment 2：
Continuous glass fibre is exported by creel, continuous fiber is deployed into the ㎡ of surface density 180/, is then melted with extruding
The acrylic resin melted is coated, and after mould molding, cooling, is crimped winding, it is pre- to obtain continuous lod
Band is soaked, continuous fiber belt glass mass fraction is 60%, and the thickness of continuous fiber belt is 0.2mm, tensile strength 650MPa,；
Obtained continuous lod prepreg tape and Polar Crystal Slab are positioned on unwinding rack, by the non-polar plane of Polar Crystal Slab with
Prepreg tape is bonded, with 7m/min speed drawing, flattening-out, then by 220 DEG C of baking oven after, compound, cooling and shaping, laying is made
0/90/0, thickness 0.6mm continuous fiber reinforced thermoplastic composite material sheet materials；
Obtained sheet material is cut, is then placed in thickness 20mm apertures 6mm grammes per square metre 80g/ ㎡ honeycomb core compound
In machine, compound by 180 DEG C of preheatings under 2m/min hauling speed, it is 25mm continuous lods that thickness is completed after cooling
Cellular board；
By cellular board, slot treatment is carried out according to 60 ° of angles and width 8mm, after EVA adhesive film is placed in groove, glued membrane is put
Postpone, the sheet material after fluting is positioned on mould bases, after carrying out pressure bending, with 130 DEG C of heat gun, preheating time, 40s was split
The gap blowing hot wind of groove is handled, and will will carry out splicing processing at the split notch of thermosol gelgun after processing；
After obtained sheet material cooling, intrados be surface-treated with flatiron it is smooth after, carry out pasting melamine film.
Embodiment 3：
Continuous glass fibre is exported by creel, continuous fiber is deployed into surface density 240g/ ㎡, is then melted with extruding
The acrylic resin melted is coated, and after mould molding, cooling, is crimped winding, it is pre- to obtain continuous lod
Band is soaked, continuous fiber belt glass mass fraction is 60%, and the thickness of continuous fiber belt is 0.3mm, tensile strength 850MPa,；
Obtained continuous lod prepreg tape and Polar Crystal Slab are positioned on unwinding rack, by the non-polar plane of Polar Crystal Slab with
Prepreg tape is bonded, with 5m/min speed drawing, flattening-out, then by 200 DEG C of baking oven after, compound, cooling and shaping, laying is made
0/90/0, thickness 0.9mm continuous fiber reinforced thermoplastic composite material sheet materials；
Obtained sheet material is cut, is then placed in thickness 25mm apertures 8mm grammes per square metre 80g/ ㎡ honeycomb core compound
In machine, compound by 200 DEG C of preheatings under 2m/min hauling speed, it is 25mm continuous lods that thickness is completed after cooling
Cellular board；
By cellular board, slot treatment is carried out according to 45° angle degree and width 8mm, after EVA adhesive film is placed in groove, glued membrane is put
Postpone, the sheet material after fluting is positioned on mould bases, after carrying out pressure bending, with 150 DEG C of heat gun, preheating time, 40s was split
The gap blowing hot wind of groove is handled, and will will carry out splicing processing at the split notch of thermosol gelgun after processing；Treat obtained sheet material
After cooling, intrados be surface-treated with flatiron it is smooth after, carry out pasting melamine film.
Embodiment 4：
Continuous glass fibre is exported by creel, continuous fiber is deployed into surface density 300g/ ㎡, is then melted with extruding
The acrylic resin melted is coated, and after mould molding, cooling, is crimped winding, it is pre- to obtain continuous lod
Band is soaked, continuous fiber belt glass mass fraction is 50%, and the thickness of continuous fiber belt is 0.35mm, tensile strength 650MPa,；
Obtained continuous lod prepreg tape and Polar Crystal Slab are positioned on unwinding rack, by the non-polar plane of Polar Crystal Slab with
Prepreg tape is bonded, with 3m/min speed drawing, flattening-out, then by 200 DEG C of baking oven after, compound, cooling and shaping, laying is made
0/90/0, thickness 1.05mm continuous fiber reinforced thermoplastic composite material sheet materials；
Obtained sheet material is cut, is then placed in thickness 35mm apertures 12mm grammes per square metre 80g/ ㎡ honeycomb core compound
In machine, compound by 220 DEG C of preheatings under 2m/min hauling speed, it is 35mm continuous lods that thickness is completed after cooling
Cellular board；
By cellular board, slot treatment is carried out according to 60 ° of angles and width 12mm, after POE glued membranes are placed in groove, glued membrane is put
Postpone, the sheet material after fluting is positioned on mould bases, after carrying out pressure bending, with 150 DEG C of heat gun, preheating time, 40s was split
The gap blowing hot wind of groove is handled, and will will carry out splicing processing at the split notch of thermosol gelgun after processing；
After obtained sheet material cooling, intrados be surface-treated with flatiron it is smooth after, carry out pasting melamine film.
The Thickness Strength of the surface layer of compartment board is relevant with carrying needed for selected vehicle in summary, the formula pair of different resins
The performance of material determines that reason is very big, also closely related with material cost, therefore in this patent, the thickness of continuous fiber layer with
And performance selection is not limited to this, but need flexibly to handle with specific environment, specific requirement.
The above-mentioned description to embodiment is understood that for ease of those skilled in the art and using invention.
Person skilled in the art obviously can easily make various modifications to these embodiments, and described herein general
Principle is applied in other embodiment without by performing creative labour.Therefore, the invention is not restricted to above-described embodiment, ability
Field technique personnel do not depart from improvement that scope made and modification all should be the present invention's according to the announcement of the present invention
Within protection domain.
Claims (7)
1. a kind of preparation method of winged flying vehicle compartment board, it is characterised in that its technique specifically includes following steps：
(1) prepreg tape is prepared
Glass fibre is exported by creel according to weight proportion and spread out to 150-350g/m2Surface density, then with by
The thermoplastic resin of weight proportion extrusion melting is coated, then winding is crimped after mould molding, and obtaining thickness is
0.15-0.35mm, simple tension intensity are 600-1000MPa continuous lod prepreg tape；Wherein glass fibre and thermoplastic
The parts by weight of property resin are：Glass fibre 50-70 parts, thermoplastic is as resin 30-50 parts；
(2) prepare thermoplastic and meet sheet material
Continuous lod prepreg tape made from (1) and Polar Crystal Slab are positioned on unwinding rack, the non-polar plane of Polar Crystal Slab and company
Continuous fiber reinforcement prepreg tape fitting, then carries out traction flattening-out with 3-8m/min speed, then by heating-up temperature is 190-220
DEG C baking oven heating, the number of plies that then Compound cooling is fixed to that thickness is 0.3-1.05mm be 2-5 layers multilayer continuous fiber increase
Strong Thermoplastic Laminates；
(3) cellular board is prepared
Obtained multilayer continuous fiber reinforced thermoplastic composite material sheet material in step (2) is cut, then with honeycomb core
Be placed in compounding machine, 180-220 DEG C of preheating carried out under 1.5-3.5/min hauling speed, then carry out it is compound, after cooling
The continuous lod cellular board that the thickness for obtaining being covered with polarity film surface is 20-40mm；
(4) fluting sealing
By continuous lod cellular board obtained in step (3), according to angle 0-90°, width 6-18mm slotted, so
Glued membrane is put into groove afterwards, the sheet material after fluting is positioned on mould bases, after carrying out pressure bending, setting heat gun temperature is
The gap heat treatment 30-60s of 130-160 DEG C of cross-notching, then with splicing processing is carried out at the split notch of thermosol gelgun, is keeping
Under bending state cooling until temperature be down to less than 35 DEG C, obtain bending sheets；
(5) leveling pad pasting
Vestige after bending sheets prepared by step (4) are handled thermosol gelgun with flatiron plates, and is finally carried out on its surface
Pad pasting, get product.
2. the preparation method of winged flying vehicle compartment board according to claim 1, it is characterised in that the thermoplastic in the step (1)
Property resin is selected from HOPP, the one or more in COPP.
3. the preparation method of winged flying vehicle compartment board according to claim 1, it is characterised in that Polar Crystal Slab in the step (2)
To add maleic anhydride inoculated polypropylene film, one kind in ethylene-vinyl acetate copolymer (EVA) or elastomer (POE).
4. the preparation method of winged flying vehicle compartment board according to claim 1, it is characterised in that multilayer connects in the step (2)
The structure laying of continuous fiber reinforced thermolplastic composite material sheet material is 0/90,0/90/0,90/0/90,0/90/0/90,0/90/
One or more in 90/0,0/90/0/90/0,90/0/90/0/90.
5. the preparation method of winged flying vehicle compartment board according to claim 1, it is characterised in that honeycomb core in the step (3)
Material is selected from polypropylene, and the aperture of the honeycomb core is 6-12mm, and the grammes per square metre of the honeycomb core is 60-120g/m2, the honeycomb
Core thickness is 20-40mm.
6. the preparation method of winged flying vehicle compartment board according to claim 1, it is characterised in that the glued membrane in the step (4)
For one kind in ethylene-vinyl acetate copolymer (EVA) or elastomer (POE).
7. the preparation method of winged flying vehicle compartment board according to claim 1, it is characterised in that the pad pasting in the step (4)
For melamine film or phenolic aldehyde film.
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|---|---|---|---|---|
| CN102218828A (en) * | 2011-05-27 | 2011-10-19 | 常州市宏发纵横新材料科技股份有限公司 | Method for preparing continuous fiber multiaxial fabric reinforced thermoplastic composite material |
| CN203297920U (en) * | 2013-05-30 | 2013-11-20 | 黄晓波 | Hard buckling board |
| CN103568396A (en) * | 2012-08-02 | 2014-02-12 | 上海杰事杰新材料(集团)股份有限公司 | Light-weight and high-strength thermoplastic composite material sandwich board and production method thereof |
| CN205504442U (en) * | 2016-04-18 | 2016-08-24 | 青岛志卓通力新材料有限公司 | Aluminium -plastic panel fluting structure of buckling |
| CN106182582A (en) * | 2016-07-27 | 2016-12-07 | 青岛集威新材料科技有限公司 | A kind of fiber reinforced thermolplastic composite material makes the method for highway guard plate |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102218828A (en) * | 2011-05-27 | 2011-10-19 | 常州市宏发纵横新材料科技股份有限公司 | Method for preparing continuous fiber multiaxial fabric reinforced thermoplastic composite material |
| CN103568396A (en) * | 2012-08-02 | 2014-02-12 | 上海杰事杰新材料(集团)股份有限公司 | Light-weight and high-strength thermoplastic composite material sandwich board and production method thereof |
| CN203297920U (en) * | 2013-05-30 | 2013-11-20 | 黄晓波 | Hard buckling board |
| CN205504442U (en) * | 2016-04-18 | 2016-08-24 | 青岛志卓通力新材料有限公司 | Aluminium -plastic panel fluting structure of buckling |
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Application publication date: 20171110 |