CN110181905A - Fiber/metal laminate composite material airplane floor and manufacturing method - Google Patents

Fiber/metal laminate composite material airplane floor and manufacturing method Download PDF

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Publication number
CN110181905A
CN110181905A CN201910482184.2A CN201910482184A CN110181905A CN 110181905 A CN110181905 A CN 110181905A CN 201910482184 A CN201910482184 A CN 201910482184A CN 110181905 A CN110181905 A CN 110181905A
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China
Prior art keywords
layer
fiber
metal decking
composite material
laminate composite
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CN201910482184.2A
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Chinese (zh)
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CN110181905B (en
Inventor
万绍钦
鲁光涛
赖建政
李强宣
李芳宇
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Lingyun Yichang Aviation Equipment Engineering Co ltd
Lingyun Science and Technology Group Co Ltd
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No571 Plant Of Pla
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    • 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
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/14—Layered products comprising a layer of metal next to a 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
    • B32B17/00—Layered products essentially comprising sheet glass, or glass, slag, or like fibres
    • B32B17/06—Layered products essentially comprising sheet glass, or glass, slag, or like fibres comprising glass as the main or only constituent of a layer, next to another layer of a specific material
    • B32B17/061—Layered products essentially comprising sheet glass, or glass, slag, or like fibres comprising glass as the main or only constituent of a layer, next to another layer of a specific material of metal
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form
    • B32B3/02—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by features of form at particular places, e.g. in edge regions
    • B32B3/08—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
    • 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
    • B32B33/00—Layered products characterised by particular properties or particular surface features, e.g. particular surface coatings; Layered products designed for particular purposes not covered by another single class
    • 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
    • B32B37/10—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure
    • B32B37/1018—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure using only vacuum
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/12—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B38/00—Ancillary operations in connection with laminating processes
    • 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
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B32B5/024—Woven fabric
    • 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
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B32B5/026—Knitted fabric
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
    • B32B7/04—Interconnection of layers
    • B32B7/12—Interconnection of layers using interposed adhesives or interposed materials with bonding properties
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
    • B32B9/04—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B9/041—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material of metal
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/18—Floors
    • 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
    • B32B2038/0052—Other operations not otherwise provided for
    • B32B2038/0076—Curing, vulcanising, cross-linking
    • 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
    • B32B2038/042—Punching
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/02—Composition of the impregnated, bonded or embedded layer
    • B32B2260/021—Fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/04—Impregnation, embedding, or binder material
    • B32B2260/046—Synthetic resin
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/101—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
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/106—Carbon fibres, e.g. graphite fibres
    • 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
    • B32B2307/50—Properties of the layers or laminate having particular mechanical properties
    • B32B2307/552—Fatigue strength
    • 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
    • B32B2307/50—Properties of the layers or laminate having particular mechanical properties
    • B32B2307/558—Impact strength, toughness
    • 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
    • B32B2307/744—Non-slip, anti-slip
    • 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
    • B32B2605/18—Aircraft

Abstract

The present invention provides fiber/metal laminate composite material airplane floors and manufacturing method, it includes upper metal decking layer, punching press is provided with uniformly distributed anti-skid stud nest on the upper metal decking layer, resin fibre mixture layer is filled with inside the anti-skid stud nest, the lower end surface of the resin fibre mixture layer and upper metal decking layer is pasted with fiber fabric layer, and the lower end surface of the fiber fabric layer is pasted with lower metal decking layer.Using the airplane floor that this kind of material manufactures not only have many advantages, such as polymer matrix composites it is high-intensitive than, when designability is good for rigidity, while also retaining metal material excellent impact resistance energy and bending property, improve the non-skid property of airplane floor.

Description

Fiber/metal laminate composite material airplane floor and manufacturing method
Technical field
The present invention relates to airplane floor technical fields, and in particular to a kind of with fiber/metal laminate composite material Airplane floor and manufacturing method more particularly relate to the manufacture that former airplane floor is substituted with fiber/metal composite layer plywood Method.
Background technique
There was only metal material and two kinds of fiber resin matrix Test of Laminate Composites currently used for airplane floor material.Metal material Material is used as traditional material, its advantage is that shock resistance is good, isotropism, good bending property etc., the disadvantage is that low specific strength, Specific stiffness, designability difference etc., as airplane floor material, metal material is not able to satisfy aircraft to the urgent of light-weight high-strength material Demand.Fiber resin matrix Test of Laminate Composites as advanced composite material, its advantage is that have high specific strength, specific stiffness and Designability etc., the disadvantage is that shock resistance is poor, anisotropy, bending property difference etc., as flooring material, fiber resin matrix Test of Laminate Composites cannot meet the requirement that performance is hit in floor confrontation.
Summary of the invention
In order to solve the above technical problems, the present invention provides fiber/metal laminate composite material airplane floor and manufacture Method using the airplane floor that this kind of material manufactures not only there is the high-intensitive ratio of polymer matrix composites, rigidity can when set The advantages that meter property is good, while also retaining metal material excellent impact resistance energy and bending property, improve the anti-skidding of airplane floor Performance.
In order to realize above-mentioned technical characteristic, the object of the present invention is achieved like this: fiber/metal laminate composite wood The airplane floor of material, it includes upper metal decking layer, and punching press is provided with uniformly distributed anti-skid stud nest, institute on the upper metal decking layer It states inside anti-skid stud nest filled with resin fibre mixture layer, the lower end of the resin fibre mixture layer and upper metal decking layer Face is pasted with fiber fabric layer, and the lower end surface of the fiber fabric layer is pasted with lower metal decking layer.
Pure resin is impregnated in the fiber fabric layer.
The resin fibre mixture layer is stirred using epoxy resin and staple fiber.
The fiber fabric layer uses glass fabric layer or carbon fiber fabric plies.
The fiber fabric layer uses plain cloth or twills.
Glue is all used between the upper metal decking layer and fiber fabric layer and fiber fabric layer and lower metal decking layer Film adhesive solidification.
The manufacturing method of fiber/metal laminate composite material airplane floor, it the following steps are included:
Step 1, stamping die manufacture；
Step 2, the manufacture of anti-skid stud nest；
Step 3, surface treatment；
Step 4 is glued mold and is prepared；
Step 5, paving；
Step 6, curing molding.
Mold in the step 1 includes stamping die and red needle two parts；The stamping die selects 45# steel, rough mills Afterwards, stress relief annealing process is done；The red needle selects Cr12 mould steel, handles after Vehicle Processing through quenching+tempering, hardness is HRC48~52；
The concrete operations of anti-skid stud nest manufacture in the step 2: select TA2 titanium alloy sheet as upper metal decking layer, foundation Ground board size uses laser blanking；Select TA2 titanium alloy sheet as lower metal decking layer；Upper metal decking layer is placed on press Anti-skid stud nest is manufactured using stamping die.
The concrete operations being surface-treated in the step 3: upper metal decking layer and lower metal decking layer are all subjected to sulfuric acid Anodization；Broom closet must be gone to after anodization in 2 hours, inhibition primer, spray must be sprayed in part glue joint face in 8h Linging glue amount is 200g/m2~250g/m2；
It is glued the concrete operations that mold prepares in the step 4: by plane mould and anti-skidding mould for nail first by its surface grease stain Dust debris are cleaned out, and wipe die surface with acetone, and be uniformly coated with release agent；
The concrete operations of paving in the step 5: in clean room, by the smooth paving of glue film in upper metal decking layer and lower gold Belong on panel layer；The splicing face of plate spreads upper metal decking layer on flat bench, and anti-skid stud nest is downward；Using epoxy resin plus Enter and is inserted in anti-skid stud nest after chopped carbon fiber is mixed thoroughly；Fiber fabric layer is smooth on upper metal decking layer splicing face, lower metal Panel layer is glued face paste on fiber fabric layer.
The concrete operations of curing molding in the step 6: after the completion of paving, plane mould, isolation film, gear are successively put Block, isolation film, inhales glue material, mold, airfelt, vacuum bag and pressure sensitive adhesive tape at paving blank；Thermocouple is affixed on part length side To two ends edge, air-leakage test is done after encapsulation, close after vacuum vacuum degree in vacuum bag and be less than -0.092Mpa, and Vacuum degree decline is no more than 0.01Mpa in 5min, on the contrary then pressure sensitive adhesive tape is rolled to real compression one by one；It is multiple that air-tightness is done before solidification It surveys, vacuum degree is less than -0.092Mpa in vacuum bag after closing vacuum, and vacuum degree decline is no more than 0.01Mpa in 5min, instead Sealant tape is then rolled to real compression one by one；80 DEG C are warming up to the rate of 1.0 DEG C/min, 30min is kept the temperature, is forced into 0.5Mpa is warming up to 130 ± 5 DEG C with the rate of 1.0 DEG C/min, and heat-insulation pressure keeping 120min is cooled to the rate of 1.0 DEG C/min 40 DEG C of releases, can openings.
The method have the advantages that:
Fiber of the present invention/metal laminate composite material airplane floor is compound by metal material and fiber resin matrix By the molding composite material of solidification of hot-press tank after material laying, the excellent of metal material and fiber-base composite materials is combined Point not only has high specific strength, specific stiffness；And there are also preferable shock resistances；Higher damage tolerance and good Fatigue behaviour etc..Therefore consider to be metal material from security reliability, weight loss effect, the designability of non-skid property etc. It is incomparable with fiber resin matrix Test of Laminate Composites.
Detailed description of the invention
Present invention will be further explained below with reference to the attached drawings and examples.
Fig. 1 is fiber of the present invention/metal laminate composite material airplane floor schematic cross-section.
Device figure when Fig. 2 is fiber of the present invention/metal laminate composite material airplane floor curing molding.
Fig. 3 is fiber of the present invention/metal laminate composite material airplane floor manufacturing process flow diagram.
Fig. 4 is fiber of the present invention/metal laminate composite material airplane floor manufacturing process sectional view.
In figure: upper metal decking layer 1, fiber fabric layer 3, lower metal decking layer 4, inhales glue material at resin fibre mixture layer 2 Expect 5, vacuum bag 6, paving blank 7, isolation film 8, airfelt 9, pressure sensitive adhesive tape 10, mold 11, plane mould 12, block 13.
Specific embodiment
Embodiments of the present invention are described further with reference to the accompanying drawing.
Embodiment 1:
Referring to Fig. 1, fiber/metal laminate composite material airplane floor, it includes upper metal decking layer 1, the upper metal Punching press is provided with uniformly distributed anti-skid stud nest on panel layer 1, is filled with resin fibre mixture layer 2, institute inside the anti-skid stud nest The lower end surface for stating resin fibre mixture layer 2 and upper metal decking layer 1 is pasted with fiber fabric layer 3, the fiber fabric layer 3 Lower end surface is pasted with lower metal decking layer 4.By using the airplane floor of above structure, use fibrous layer and metal layer compound By the molding composite material of solidification of hot-press tank after material laying, the excellent of metal material and fiber-base composite materials is combined Point not only has high specific strength, specific stiffness；And there are also preferable shock resistances；Higher damage tolerance and good Fatigue behaviour etc..And then reach all properties feature required for airplane floor, and then greatly improve the peace of airplane floor Quan Xing reaches loss of weight, antiskid effect.
Further, pure resin is impregnated in the fiber fabric layer 3.It ensure that metal by above-mentioned resin additive Bonding capacity between layer and limit layer, and then ensure that the reliability of Coating combination.
Further, the resin fibre mixture layer 2 is stirred using epoxy resin and staple fiber.By upper Resin fibre mixture layer 2 its one side stated can be filled anti-skid stud nest, and then improve its shock resistance, separately On the one hand the faying face area between metal decking layer 1 and fiber fabric layer 3 is also increased, ensure that interfacial bonding strength.
Further, the fiber fabric layer 3 uses glass fabric layer or carbon fiber fabric plies.Pass through above-mentioned fibre Tie up tissue layer 3 its with high specific strength, specific stiffness and designability, and then compensate for deposited using single metal layer well Defect.
Further, the fiber fabric layer 3 uses plain cloth or twills.
Further, the upper metal decking layer 1 and fiber fabric layer 3 and fiber fabric layer 3 and lower metal decking layer 4 Between all use glue film adhesive solidification.
Further, the thickness of the preferred upper metal decking layer 1 uses 0.5mm.
Further, the preferred lower metal decking layer 4 with a thickness of 0.3 mm.
Further, preferred fiber fabric layer 3 is ± 45 ° of knitted fabrics.
Embodiment 2:
Referring to fig. 2-4, the manufacturing method of fiber/metal laminate composite material airplane floor, it the following steps are included:
Step 1, stamping die manufacture: the mold includes stamping die and red needle two parts；The stamping die selects 45# steel, After rough milling, stress relief annealing process is done；The red needle selects Cr12 mould steel, handles after Vehicle Processing through quenching+tempering, hardness is HRC48~52；It is mainly used for being stamped and formed out anti-skid stud nest on upper metal decking layer 1 using above-mentioned mold, so that floor Upper surface play good protective action；
Step 2, the manufacture of anti-skid stud nest: selecting TA2 titanium alloy sheet as upper metal decking layer 1, uses laser according to ground board size Blanking；Select TA2 titanium alloy sheet as lower metal decking layer 4；Upper metal decking layer 1 is placed on press using in step 1 Stamping die manufactures anti-skid stud nest；
Surface treatment: upper metal decking layer 1 and lower metal decking layer 4 are all carried out sulfur acid anodizing processing by step 3；Anodization Broom closet must be gone in 2 hours afterwards, SY-D9 inhibition primer must be sprayed in part glue joint face in 8h, spraying primer amount is 200g/m2~250g/m2；Using anodization primarily to increasing metal decking surface cementing property, and then make it well It is glued with glue film, ensure that the reliability of splicing.
Step 4 is glued mold and is prepared: plane mould 12 and anti-skidding mould for nail 11 is miscellaneous by its surface grease stain dust first Object is cleaned out, and wipes die surface with acetone, and be uniformly coated with release agent；It ensure that by above-mentioned cleaning process subsequent The reliability of splicing.
Step 5, paving: in clean room, by the smooth paving of SY-24C glue film in upper metal decking layer 1 and lower metal covering On plate layer 4；The splicing face of plate spreads upper metal decking layer 1 on flat bench, and anti-skid stud nest is downward；It is added using epoxy resin Chopped carbon fiber is inserted in anti-skid stud nest after mixing thoroughly；Fiber fabric layer 3 is smooth on upper 1 splicing face of metal decking layer, lower metal Panel layer 4 is glued face paste on fiber fabric layer 3；
Step 6, curing molding: after the completion of paving, successively put plane mould 12, isolation film 8, block 13, paving blank 7, every From film 8, inhale glue material 5, mold 11, airfelt 9, vacuum bag 6 and pressure sensitive adhesive tape 10；Thermocouple is affixed on part length direction both ends At head edge, air-leakage test is done after encapsulation, vacuum degree is less than -0.092Mpa in vacuum bag 6 after closing vacuum, and in 5min Vacuum degree decline is no more than 0.01Mpa, on the contrary then pressure sensitive adhesive tape 10 is rolled real compression one by one；Air-tightness repetition measurement is done before solidification, is closed Close after vacuum that vacuum degree is less than -0.092Mpa in vacuum bag 6, and vacuum degree decline is no more than 0.01Mpa in 5min, it is on the contrary then Sealant tape is rolled to real compression one by one；80 DEG C are warming up to the rate of 1.0 DEG C/min, 30min is kept the temperature, is forced into 0.5Mpa, with The rate of 1.0 DEG C/min is warming up to 130 ± 5 DEG C, heat-insulation pressure keeping 120min, is cooled to 40 DEG C with the rate of 1.0 DEG C/min and unloads Pressure, can opening.
Wherein above-mentioned suction glue material 5, vacuum bag 6, paving blank 7, isolation film 8, airfelt 9, pressure sensitive adhesive tape 10, mold 11, plane mould 12, block 13 collectively form Vacuuming structure, and then ensure that metal decking layer 1, resin fibre mixture Complete solidification by cement molding between layer 2, fiber fabric layer 3 and lower metal decking layer 4.It is mainly using the original for vacuumizing negative pressure Reason forms to realize that it is glued.

Claims (10)

1. fiber/metal laminate composite material airplane floor, it is characterised in that: it includes upper metal decking layer (1), described Punching press is provided with uniformly distributed anti-skid stud nest on upper metal decking layer (1), mixes inside the anti-skid stud nest filled with resin fibre The lower end surface of nitride layer (2), the resin fibre mixture layer (2) and upper metal decking layer (1) is pasted with fiber fabric layer (3), The lower end surface of the fiber fabric layer (3) is pasted with lower metal decking layer (4).
2. fiber/metal laminate composite material airplane floor according to claim 1, it is characterised in that: the fiber Pure resin is impregnated in tissue layer (3).
3. fiber/metal laminate composite material airplane floor according to claim 1, it is characterised in that: the resin Fibre blend layer (2) is stirred using epoxy resin and staple fiber.
4. fiber/metal laminate composite material airplane floor according to claim 1, it is characterised in that: the fiber Tissue layer (3) uses glass fabric layer or carbon fiber fabric plies.
5. according to claim 1 or 2 or 3 fibers/metal laminate composite material airplane floor, it is characterised in that: institute Fiber fabric layer (3) are stated using plain cloth or twills.
6. fiber/metal laminate composite material airplane floor according to claim 1, it is characterised in that: the upper gold Belong to all viscous using glue film between panel layer (1) and fiber fabric layer (3) and fiber fabric layer (3) and lower metal decking layer (4) Knot solidification.
7. the manufacturing method of fiber described in claim 1-6 any one/metal laminate composite material airplane floor, special Sign be it the following steps are included:
Step 1, stamping die manufacture；
Step 2, the manufacture of anti-skid stud nest；
Step 3, surface treatment；
Step 4 is glued mold and is prepared；
Step 5, paving；
Step 6, curing molding.
8. the manufacturing method of fiber/metal laminate composite material airplane floor, feature exist according to claim 7 In the mold in the step 1 includes stamping die and red needle two parts；The stamping die selects 45# steel, after rough milling, does Stress relief annealing process；The red needle selects Cr12 mould steel, handles after Vehicle Processing through quenching+tempering, and hardness is HRC48 ~ 52；
The concrete operations of anti-skid stud nest manufacture in the step 2: selecting TA2 titanium alloy sheet as upper metal decking layer (1), Laser blanking is used according to ground board size；Select TA2 titanium alloy sheet as lower metal decking layer (4)；By upper metal decking layer (1) It is placed on press and manufactures anti-skid stud nest using stamping die.
9. the manufacturing method of fiber/metal laminate composite material airplane floor, feature exist according to claim 7 In the concrete operations being surface-treated in the step 3: upper metal decking layer (1) and lower metal decking layer (4) are all carried out sulphur Sour anodization；Broom closet must be gone to after anodization in 2 hours, inhibition primer must be sprayed in part glue joint face in 8h, Spraying primer amount is 200g/m2~250g/m2；
It is glued the concrete operations that mold prepares in the step 4: by plane mould (12) and anti-skidding mould for nail (11) first by it Surface grease stain dust debris are cleaned out, and wipe die surface with acetone, and be uniformly coated with release agent；
The concrete operations of paving in the step 5: in clean room, by the smooth paving of glue film in upper metal decking layer (1) and under On metal decking layer (4)；The splicing face of plate spreads upper metal decking layer (1) on flat bench, and anti-skid stud nest is downward；Use ring Oxygen resin is added after chopped carbon fiber is mixed thoroughly and inserts in anti-skid stud nest；Fiber fabric layer (3) is smooth in upper metal decking layer (1) glue In junction, lower metal decking layer (4) is glued face paste on fiber fabric layer (3).
10. the manufacturing method of fiber/metal laminate composite material airplane floor, feature exist according to claim 7 In the concrete operations of curing molding in the step 6: after the completion of paving, successively put plane mould (12), isolation film (8), Block (13), isolation film (8), inhales glue material (5), mold (11), airfelt (9), vacuum bag (6) and pressure-sensitive at paving blank (7) Adhesive tape (10)；Thermocouple is affixed on part length direction two ends edge, and air-leakage test is done after encapsulation, closes vacuum after vacuum Bag (6) interior vacuum degree is less than -0.092Mpa, and vacuum degree decline is no more than 0.01Mpa in 5min, it is on the contrary then by pressure sensitive adhesive tape (10) real compression is rolled one by one；Air-tightness repetition measurement is done before solidification, vacuum bag (6) interior vacuum degree is less than -0.092Mpa after closing vacuum, And vacuum degree decline is no more than 0.01Mpa in 5min, it is on the contrary then sealant tape is rolled to real compression one by one；With 1.0 DEG C/min's Rate is warming up to 80 DEG C, keeps the temperature 30min, is forced into 0.5Mpa, is warming up to 130 ± 5 DEG C with the rate of 1.0 DEG C/min, heat preservation is protected 120min is pressed, 40 DEG C of releases, can openings are cooled to the rate of 1.0 DEG C/min.
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