CN110181905B - Aircraft floor made of fiber/metal laminate composite material and manufacturing method - Google Patents

Aircraft floor made of fiber/metal laminate composite material and manufacturing method Download PDF

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Publication number
CN110181905B
CN110181905B CN201910482184.2A CN201910482184A CN110181905B CN 110181905 B CN110181905 B CN 110181905B CN 201910482184 A CN201910482184 A CN 201910482184A CN 110181905 B CN110181905 B CN 110181905B
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China
Prior art keywords
fiber
metal panel
layer
manufacturing
panel layer
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CN110181905A (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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Lingyun Yichang Aviation Equipment Engineering Co ltd
Lingyun Science and Technology Group Co Ltd
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Priority to CN201910482184.2A priority Critical patent/CN110181905B/en
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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 invention provides an aircraft floor made of fiber/metal laminated board composite materials and a manufacturing method thereof. The aircraft floor manufactured by the material has the advantages of high strength ratio, high rigidity ratio, good designability and the like of the resin matrix composite material, meanwhile, good shock resistance and bending performance of the metal material are reserved, and the anti-skid performance of the aircraft floor is improved.

Description

Aircraft floor made of fiber/metal laminate composite material and manufacturing method
Technical Field
The invention relates to the technical field of aircraft floors, in particular to an aircraft floor with a fiber/metal laminated plate composite material and a manufacturing method thereof, and more particularly relates to a manufacturing method for replacing an original aircraft floor with a fiber/metal laminated plate.
Background
Only two types of metal materials and fiber resin-based laminated board composite materials are currently used for aircraft floor materials. The metal material used as the traditional material has the advantages of good shock resistance, isotropy, good bending property and the like, and has the defects of low specific strength, specific rigidity, poor designability and the like, and as the aircraft floor material, the metal material can not meet the urgent requirements of the aircraft on the light high-strength material. The fiber resin-based laminated board composite material is used as an advanced composite material, has the advantages of high specific strength, specific rigidity, designability and the like, has the defects of poor shock resistance, anisotropy, poor bending property and the like, and can not meet the requirement of the floor on the anti-shock property as a floor material.
Disclosure of Invention
In order to solve the technical problems, the invention provides the aircraft floor made of the fiber/metal laminated plate composite material and the manufacturing method thereof, and the aircraft floor made of the fiber/metal laminated plate composite material has the advantages of high strength ratio, high rigidity ratio, good designability and the like of a resin-based composite material, simultaneously keeps good impact resistance and bending performance of a metal material, and improves the anti-skid performance of the aircraft floor.
In order to achieve the technical characteristics, the aim of the invention is realized in the following way: the utility model provides an aircraft floor of fibre/metal laminate combined material, it includes the metal panel layer, the punching press is provided with the stud nest of equipartition on the metal panel layer, the inside resin fiber mixture layer that fills of stud nest, the lower terminal surface on resin fiber mixture layer and the metal panel layer of going up is pasted and is had the fiber fabric layer, the lower terminal surface on fiber fabric layer is pasted and is had the metal panel layer down.
The fiber fabric layer is soaked with pure resin.
The resin fiber mixture layer is formed by stirring and mixing epoxy resin and short fibers.
The fiber fabric layer adopts a glass fiber fabric layer or a carbon fiber fabric layer.
The fiber fabric layer adopts plain weave or twill weave.
And the upper metal panel layer and the fiber fabric layer are bonded and cured by adopting an adhesive film.
A method of making an aircraft floor of a fiber/metal laminate composite comprising the steps of:
step one, manufacturing a stamping die;
step two, manufacturing an anti-skid nail nest;
step three, surface treatment;
step four, preparing a cementing mold;
step five, paving;
and step six, solidifying and forming.
The die in the first step comprises a stamping die and a stamping needle; the stamping die is made of 45# steel, and stress relief annealing treatment is carried out after rough milling; the punching needle is made of Cr12 die steel, and is subjected to quenching and tempering treatment after turning, wherein the hardness is HRC 48-52;
the specific operation of manufacturing the anti-skid nail nest in the second step is as follows: selecting a TA2 titanium alloy plate as an upper metal panel layer, and adopting laser blanking according to the floor size; selecting a TA2 titanium alloy plate as a lower metal panel layer; the upper metal panel layer is placed on a press to manufacture the cleat pockets using a stamping die.
The specific operation of surface treatment in the step three: sulfuric acid anodizing the upper metal panel layer and the lower metal panel layer; it must be transferred to a clean room within 2 hours after anodization,spraying corrosion inhibition primer on the cementing surface of the part within 8 hours, wherein the spraying primer amount is 200g/m 2 ~250g/m 2 ；
The concrete operation of the cementing mold preparation in the step four is as follows: firstly cleaning oil stain, dust and sundries on the surfaces of a plane die and a non-skid nail die, wiping the surfaces of the die with acetone, and uniformly coating a release agent;
the specific operation of paving in the fifth step is as follows: in the clean room, the adhesive film is flatly paved on the upper metal panel layer and the lower metal panel layer; the cementing surface of the plate is used for paving the upper metal panel layer on a plate workbench, and the anti-skid nail nest faces downwards; adding chopped carbon fibers into epoxy resin, uniformly stirring, and filling into the anti-skid nail nest; the fiber fabric layer is flatly attached to the bonding surface of the upper metal panel layer, and the bonding surface of the lower metal panel layer is attached to the fiber fabric layer.
The specific operation of curing and forming in the step six is as follows: after the paving is finished, a plane mould, a separation film, a stop block, a paving blank, the separation film, a glue absorbing material, a mould, an air felt, a vacuum bag and a pressure sensitive adhesive tape are sequentially arranged; the thermocouples are attached to the edges of two ends of the part in the length direction, air tightness detection is carried out after encapsulation, the vacuum degree in the vacuum bag is smaller than-0.092 Mpa after vacuum is closed, the vacuum degree is reduced by not more than 0.01Mpa within 5min, and otherwise, the pressure-sensitive adhesive tapes are rolled one by one to be tightly pressed; performing air tightness retest before curing, closing vacuum, wherein the vacuum degree in the vacuum bag is less than-0.092 Mpa, and the vacuum degree is reduced by not more than 0.01Mpa within 5min, otherwise, rolling the sealing adhesive tapes one by one to be tightly pressed; heating to 80deg.C at a rate of 1.0deg.C/min, maintaining the temperature for 30min, pressurizing to 0.5Mpa, heating to 130+ -5deg.C at a rate of 1.0deg.C/min, maintaining the temperature for 120min, cooling to 40deg.C at a rate of 1.0deg.C/min, relieving pressure, and opening the tank.
The invention has the following beneficial effects:
the aircraft floor made of the fiber/metal laminated board composite material is a composite material formed by layering a metal material and a fiber resin matrix composite material and curing the metal material and the fiber resin matrix composite material through an autoclave, integrates the advantages of the metal material and the fiber matrix composite material, and has high specific strength and specific rigidity; but also has better shock resistance; higher damage tolerance, good fatigue performance, etc. Therefore, the composite material is incomparable with the composite material of the fiber resin-based laminated board in the aspects of safety and reliability, weight reduction effect, designability of anti-skid performance and the like.
Drawings
The invention is further described below with reference to the drawings and examples.
FIG. 1 is a schematic cross-sectional view of an aircraft floor of the fiber/metal laminate composite of the present invention.
FIG. 2 is a view of an apparatus for curing and molding an aircraft floor made of the fiber/metal laminate composite of the present invention.
FIG. 3 is a flow chart of the aircraft floor manufacturing process of the fiber/metal laminate composite of the present invention.
FIG. 4 is a cross-sectional view of an aircraft floor manufacturing process of the fiber/metal laminate composite of the present invention.
In the figure: an upper metal panel layer 1, a resin fiber mixture layer 2, a fiber fabric layer 3, a lower metal panel layer 4, a glue absorbing material 5, a vacuum bag 6, a paving blank 7, a separation film 8, an airfelt 9, a pressure sensitive adhesive tape 10, a mold 11, a plane mold 12 and a stop 13.
Detailed Description
Embodiments of the present invention will be further described with reference to the accompanying drawings.
Example 1:
referring to fig. 1, the aircraft floor made of the fiber/metal laminate composite material comprises an upper metal panel layer 1, wherein uniformly distributed stud pockets are punched on the upper metal panel layer 1, a resin fiber mixture layer 2 is filled in the stud pockets, a fiber fabric layer 3 is adhered to the lower end surfaces of the resin fiber mixture layer 2 and the upper metal panel layer 1, and a lower metal panel layer 4 is adhered to the lower end surface of the fiber fabric layer 3. The aircraft floor adopting the structure adopts the composite material formed by the fiber layer and the metal layer through curing in the autoclave after being paved, integrates the advantages of the metal material and the fiber-based composite material, and has high specific strength and specific rigidity; but also has better shock resistance; higher damage tolerance, good fatigue performance, etc. All performance characteristics required by the aircraft floor are further achieved, the safety of the aircraft floor is greatly improved, and the weight reduction and anti-skid effects are achieved.
Further, the fiber fabric layer 3 is impregnated with pure resin. The bonding capability between the metal layer and the limiting layer is ensured through the resin additive, so that the bonding reliability between layers is ensured.
Further, the resin fiber mixture layer 2 is formed by stirring and mixing epoxy resin and short fibers. The resin fiber mixture layer 2 can be used for filling the anti-skid stud pits on one hand, so that the shock resistance is improved, the bonding surface area between the upper metal panel layer 1 and the fiber fabric layer 3 is increased on the other hand, and the interlayer bonding strength is ensured.
Further, the fiber fabric layer 3 is a glass fiber fabric layer or a carbon fiber fabric layer. The fiber fabric layer 3 has high specific strength, specific rigidity and designability, so that the defects existing in the single metal layer are well overcome.
Further, the fiber fabric layer 3 adopts plain weave or twill weave.
Further, the upper metal panel layer 1 and the fiber fabric layer 3 and the lower metal panel layer 4 are bonded and cured by adopting adhesive films.
Further, the thickness of the upper metal panel layer 1 is preferably 0.5mm.
Further, the thickness of the lower metal panel layer 4 is preferably 0.3. 0.3 mm.
Further, the preferred fibrous fabric layer 3 is a + -45 DEG warp knit fabric.
Example 2:
referring to fig. 2-4, a method of manufacturing an aircraft floor of a fiber/metal laminate composite, comprising the steps of:
step one, manufacturing a stamping die: the die comprises a stamping die and a stamping needle; the stamping die is made of 45# steel, and stress relief annealing treatment is carried out after rough milling; the punching needle is made of Cr12 die steel, and is subjected to quenching and tempering treatment after turning, wherein the hardness is HRC 48-52; the mold is mainly used for punching the upper metal panel layer 1 to form the anti-skid nail nest, so that the upper surface of the floor has a good protection effect;
step two, manufacturing an anti-skid nail nest: selecting a TA2 titanium alloy plate as an upper metal panel layer 1, and adopting laser blanking according to the floor size; selecting a TA2 titanium alloy plate as a lower metal panel layer 4; placing the upper metal panel layer 1 on a press to manufacture an anti-skid nail nest by using the stamping die in the first step;
step three, surface treatment: sulfuric acid anodizing both the upper metal panel layer 1 and the lower metal panel layer 4; transferring to a cleaning room within 2 hours after anodizing, spraying SY-D9 corrosion inhibition primer on the part bonding surface within 8 hours, wherein the spraying primer amount is 200g/m 2 ~250g/m 2 The method comprises the steps of carrying out a first treatment on the surface of the The anodizing treatment is mainly used for increasing the surface cementing property of the metal panel, so that the metal panel is well cemented with the adhesive film, and the cementing reliability is ensured.
Step four, preparing a cementing mold: firstly cleaning the surface of the plane mould 12 and the anti-skid nail mould 11 with oil stain, dust and sundries, wiping the surface of the mould with acetone, and uniformly coating a release agent; the reliability of subsequent bonding is ensured through the cleaning procedure.
Step five, paving: in a clean room, a SY-24C adhesive film is flatly paved on an upper metal panel layer 1 and a lower metal panel layer 4; the upper metal panel layer 1 is paved on a flat worktable by the cementing surface of the plate, and the anti-skid nail nest faces downwards; adding chopped carbon fibers into epoxy resin, uniformly stirring, and filling into the anti-skid nail nest; the fiber fabric layer 3 is flatly attached to the adhesive bonding surface of the upper metal panel layer 1, and the adhesive bonding surface of the lower metal panel layer 4 is attached to the fiber fabric layer 3;
step six, curing and forming: after the paving is finished, a plane die 12, a separation film 8, a stop block 13, a paving blank 7, the separation film 8, a glue absorbing material 5, a die 11, an airfelt 9, a vacuum bag 6 and a pressure-sensitive adhesive tape 10 are sequentially arranged; the thermocouples are attached to the edges of two ends of the part in the length direction, air tightness detection is carried out after encapsulation, the vacuum degree in the vacuum bag 6 is smaller than-0.092 Mpa after vacuum is closed, the vacuum degree is reduced by not more than 0.01Mpa within 5min, and otherwise, the pressure-sensitive adhesive tapes 10 are rolled one by one to be tightly pressed; performing air tightness retest before curing, closing vacuum, wherein the vacuum degree in the vacuum bag 6 is less than-0.092 Mpa, and the vacuum degree is reduced by not more than 0.01Mpa within 5min, otherwise, rolling the sealing adhesive tapes one by one and compacting; heating to 80deg.C at a rate of 1.0deg.C/min, maintaining the temperature for 30min, pressurizing to 0.5Mpa, heating to 130+ -5deg.C at a rate of 1.0deg.C/min, maintaining the temperature for 120min, cooling to 40deg.C at a rate of 1.0deg.C/min, relieving pressure, and opening the tank.
The above-mentioned adhesive material 5, vacuum bag 6, paving blank 7, isolating film 8, air felt 9, pressure sensitive adhesive tape 10, mould 11, plane mould 12 and stop 13 together form a vacuum-pumping structure, so that it can ensure that the upper metal panel layer 1, resin fiber mixture layer 2, fiber fabric layer 3 and lower metal panel layer 4 are completely bonded, solidified and formed. The method mainly adopts the principle of vacuumizing negative pressure to realize the gluing molding of the plastic.

Claims (8)

1. The manufacturing method of the aircraft floor made of the fiber/metal laminated board composite material comprises the steps that an upper metal panel layer (1) is arranged on the upper metal panel layer (1) in a punching mode, a uniformly distributed anti-skid nail nest is filled in the anti-skid nail nest, a resin fiber mixture layer (2) is filled in the anti-skid nail nest, a fiber fabric layer (3) is adhered to the lower end faces of the resin fiber mixture layer (2) and the upper metal panel layer (1), and a lower metal panel layer (4) is adhered to the lower end face of the fiber fabric layer (3);
the manufacturing method is characterized by comprising the following steps:
step one, manufacturing a stamping die;
step two, manufacturing an anti-skid nail nest;
step three, surface treatment;
step four, preparing a cementing mold;
step five, paving;
step six, solidifying and forming;
the specific operation of surface treatment in the step three: sulfuric acid anodizing the upper metal panel layer (1) and the lower metal panel layer (4); within 2 hours after anodisingThe parts are transferred to a cleaning room, corrosion inhibition primer is sprayed on the cementing surface of the parts within 8 hours, and the sprayed primer amount is 200g/m 2 ~250g/m 2 ；
The concrete operation of the cementing mold preparation in the step four is as follows: firstly cleaning oil stain, dust and sundries on the surfaces of a plane die (12) and a stud die (11), wiping the surfaces of the die with acetone, and uniformly coating a release agent;
the specific operation of paving in the fifth step is as follows: in the clean room, the adhesive film is flatly paved on the upper metal panel layer (1) and the lower metal panel layer (4); the upper metal panel layer (1) is paved on a plate workbench by the cementing surface of the plate, and the anti-skid nail nest faces downwards; adding chopped carbon fibers into epoxy resin, uniformly stirring, and filling into the anti-skid nail nest; the fiber fabric layer (3) is flatly attached to the bonding surface of the upper metal panel layer (1), and the bonding surface of the lower metal panel layer (4) is attached to the fiber fabric layer (3).
2. The method of manufacturing an aircraft floor of fiber/metal laminate composite of claim 1, wherein: the fiber fabric layer (3) is internally soaked with pure resin.
3. The method of manufacturing an aircraft floor of fiber/metal laminate composite of claim 1, wherein: the resin fiber mixture layer (2) is formed by stirring and mixing epoxy resin and short fibers.
4. The method of manufacturing an aircraft floor of fiber/metal laminate composite of claim 1, wherein: the fiber fabric layer (3) adopts a glass fiber fabric layer or a carbon fiber fabric layer.
5. A method of manufacturing an aircraft floor of fiber/metal laminate composite according to claim 1 or 2 or 3, characterized by: the fiber fabric layer (3) adopts plain weave or twill weave.
6. The method of manufacturing an aircraft floor of fiber/metal laminate composite of claim 1, wherein: and the upper metal panel layer (1) and the fiber fabric layer (3) are bonded and solidified by adopting an adhesive film, and the fiber fabric layer (3) and the lower metal panel layer (4) are bonded and solidified by adopting an adhesive film.
7. The method of manufacturing an aircraft floor made of a fiber/metal laminate composite according to claim 1, wherein the die in the first step comprises two parts, namely a stamping die and a punch pin; the stamping die is made of 45# steel, and stress relief annealing treatment is carried out after rough milling; the punching needle is made of Cr12 die steel, and is subjected to quenching and tempering treatment after turning, wherein the hardness is HRC 48-52;
the specific operation of manufacturing the anti-skid nail nest in the second step is as follows: selecting a TA2 titanium alloy plate as an upper metal panel layer (1), and adopting laser blanking according to the floor size; selecting a TA2 titanium alloy plate as a lower metal panel layer (4); the upper metal panel layer (1) is placed on a press and the cleat pockets are manufactured using a stamping die.
8. The method for manufacturing an aircraft floor made of a fiber/metal laminate composite according to claim 1, wherein the specific operation of curing and molding in the sixth step is as follows: after the paving is finished, a plane mould (12), an isolating film (8), a stop block (13), a paving blank (7), the isolating film (8), a glue absorbing material (5), a mould (11), an air felt (9), a vacuum bag (6) and a pressure-sensitive adhesive tape (10) are sequentially arranged; the thermocouples are attached to the edges of two ends of the part in the length direction, air tightness detection is carried out after encapsulation, the vacuum degree in the vacuum bag (6) is smaller than-0.092 Mpa after vacuum is closed, the vacuum degree is reduced by not more than 0.01Mpa within 5min, and otherwise, the pressure-sensitive adhesive tapes (10) are rolled and tightly pressed one by one; performing air tightness retest before curing, closing vacuum, wherein the vacuum degree in the vacuum bag (6) is less than-0.092 Mpa, and the vacuum degree is reduced by not more than 0.01Mpa within 5min, otherwise, rolling the sealing adhesive tapes one by one to compact; heating to 80deg.C at a rate of 1.0deg.C/min, maintaining the temperature for 30min, pressurizing to 0.5Mpa, heating to 130+ -5deg.C at a rate of 1.0deg.C/min, maintaining the temperature for 120min, cooling to 40deg.C at a rate of 1.0deg.C/min, relieving pressure, and opening the tank.
CN201910482184.2A 2019-06-04 2019-06-04 Aircraft floor made of fiber/metal laminate composite material and manufacturing method Active CN110181905B (en)

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CN112537103A (en) * 2020-04-13 2021-03-23 廊坊市飞泽复合材料科技有限公司 Composite material structure of automobile covering part and forming method thereof
CN111421861A (en) * 2020-05-08 2020-07-17 上海瓴荣材料科技有限公司 Aluminum alloy and resin composite material integrated structure and preparation method thereof

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