CN104015917A - Fiber aluminum lithium alloy laminated board used as airplane wall board and production method of laminated board - Google Patents
Fiber aluminum lithium alloy laminated board used as airplane wall board and production method of laminated board Download PDFInfo
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- CN104015917A CN104015917A CN201410264847.0A CN201410264847A CN104015917A CN 104015917 A CN104015917 A CN 104015917A CN 201410264847 A CN201410264847 A CN 201410264847A CN 104015917 A CN104015917 A CN 104015917A
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Abstract
The invention provides a fiber aluminum lithium alloy laminated board used as an airplane wall board. The fiber aluminum lithium alloy laminated board is produced by sequentially and alternatively paving an aluminum lithium alloy board, fiber prepreg and an aluminum lithium alloy board and gluing through bottom glue, or is produced by sequentially and alternatively paving the aluminum lithium alloy board, the fiber prepreg, the aluminum lithium alloy board and the aluminum lithium alloy board and gluing through the bottom glue. The fiber aluminum lithium alloy laminated board is produced by adopting the aluminum lithium alloy board (2060 or 2198) as a raw material, and has the advantages of high strength, high anti-damage tolerance, high static strength and the like when being used as the airplane wall board; the structure weight of an aircraft is obviously reduced and the thrust-weight ratio of the aircraft is increased. According to the fiber aluminum lithium alloy laminated board, a novel phosphoric acid or sulfuric acid anodizing process is adopted so that the preparation of the laminated board is very environment-friendly. The preparation method is simple and feasible, is suitable for industrial production and has a great application value.
Description
Technical field
The present invention relates to composite material, be specifically related to fiber aluminum lithium alloy laminate, relate in particular to a kind of fiber aluminum lithium alloy laminate as aircraft target ship and preparation method thereof.
Background technology
Structure weight reduce and improve the Important Problems that the aircraft utilization life-span is current large-scale High Performance commercial passenger aircraft development, therefore, how developing density material little and that have a high damage tolerance has important meaning.
Aircraft target ship is one of important structure part of aircraft, and the metallic material that aircraft target ship adopts is the earliest 2024 and 7075 aluminum alloys, and it is little that they have density, good processability and low-cost feature, and still, fatigue life is poor and damage tolerance performance is poor.For overcoming the shortcoming of described aluminum alloy, in succession developed the new material that is applicable to covering.The first kind is that Air Passenger A350 and Pang Badi series aircraft are by the third generation aluminum lithium alloy (2198 or 2060) adopting, this serial aluminum lithium alloy is with respect to aluminum alloy (2024 or 7075), have that density is little, strength-to-density ratio is high, stiffness-to-density ratio is high, damage tolerance is good, the advantages such as withstanding corrosion.Adopt with aluminum lithium alloy (2198 or 2060), can make architecture quality alleviate 15%, rigidity improves 30%, can significantly reduce the structural weight of aircraft, increases the thrust-weight ratio of aircraft, and then significantly improves load carrying behaviour and the maneuvering performance of aircraft.Equations of The Second Kind is to adopt resin matrix composite, and this type of material, with respect to aluminum alloy materials, has density little, fatigue life advantages of higher, but the impact resistance of resin matrix composite is poor, processing characteristics is poor and expensive.The 3rd class is the fiber aramid aluminiumlaminates that adopts aluminium alloy sheet (2024 or 7075 aluminum alloy) and fiber composite materials prepreg to prepare.This laminate possesses the advantage of resin matrix composite and aluminum alloy simultaneously, compares with traditional aluminum alloy materials, and Structure weight reduce reaches 25%-30%, improves 10-20 fatigue life doubly, and the type at Boeing and Air Passenger is applied.Therefore, research adopts aluminum lithium alloy (2060 or 2198) substitute the aluminum alloy (2024 or 7075) in above-mentioned fine aluminum alloy fiber laminate and further optimize laminate preparation technology, the aluminum lithium alloy fibre laminates that design a kind of novel high-strength high anti-damage tolerance limit, have great significance.
Summary of the invention
Technical matters to be solved by this invention is to overcome above-mentioned weak point, fiber aluminum lithium alloy laminate and the preparation method of the high strength high damage tolerance of a kind of optimization as aircraft target ship of research and design.
The invention provides a kind of fiber aluminum lithium alloy laminate as aircraft target ship, described fiber aluminum lithium alloy laminate is by aluminum lithium alloy plate-fiber prepreg material-aluminum lithium alloy plate (2/1 structure, 2 layers of aluminum lithium alloy plate and 1 layer of fiber prepreg material form) alternately laying is bonded by primer mutually, or alternately laying is bonded by primer mutually by aluminum lithium alloy plate-fiber prepreg material-aluminum lithium alloy plate-fiber prepreg material-aluminum lithium alloy plate (3/2 structure, 3 layers of aluminum lithium alloy plate and 2 layers of fiber prepreg material form).
Described in fiber aluminum lithium alloy laminate of the present invention, aluminum lithium alloy plate is selected from 2198 or 2060 aluminum lithium alloy plates, and thickness is 0.2 ~ 0.5mm.
Described in fiber aluminum lithium alloy laminate of the present invention, fiber prepreg material is comprised of fiber and resin matrix, and described fiber is selected from carbon fiber, glass fibre or aramid fiber prepreg, preferred glass fibers; Resin matrix is epoxy resin.The content of described fiber in prepreg is 40%-70%V/V.Can buy by commercially available.
Fiber in described fiber prepreg material is individual layer or bilayer, and the thickness of described single layer fibre is 0.2 ~ 0.5mm.
Direction between described double-deck fiber is 0 °, 45 ° or 90 ° of angles.
Another object of the present invention has been to provide a kind of preparation method of the fiber aluminum lithium alloy laminate as aircraft target ship, and the method comprises the following steps:
(1) aluminum lithium alloy plate is processed:
(1) aluminum lithium alloy plate carries out phosphoric acid or sulfur acid anodizing processing:
Described aluminum lithium alloy plate carries out phosphoric acid (H
3pO
4) anodizing: in anodizing tank liquor, phosphoric acid quality percentum is 100 ~ 160g/L, and anodic oxydation treatment temperature is 15-35 ℃, and anodic oxydation treatment vdc is 10-20V, and the anodic oxydation treatment time is 15-30min; Or
Described aluminum lithium alloy plate carries out sulfuric acid H
3sO4 anodizing: in anodizing tank liquor, sulfuric acid mass percent is 35 ~ 65g/L, and anodic oxydation treatment temperature is 15-35 ℃, and anodic oxydation treatment vdc is 10-20V, and the anodic oxydation treatment time is 15-30min;
(2) aluminum lithium alloy plate carries out, after sour anodizing, rinsing 5-10min in water, in the baking oven of 50 ~ 70 ℃, toasts 15min;
(3) through the even brushing one deck of side surface primer of anodized aluminum lithium alloy plate, dry; Described primer is epoxy resin, and the use amount of primer is 100 ~ 300g/ aluminum lithium alloy plate m
2, bake out temperature is 80 ~ 100 ℃, drying time is 4 ~ 8 hours;
(2) prepare fiber aluminum lithium alloy laminate
(1) the aluminum lithium alloy plate of step () being processed and commercially available buy prepreg laying alternate with each other successively, by primer epoxy resin bonding, make fiber aluminum lithium alloy laminate, be stored in vacuum bag that (vacuum pressure reduction is 0.095-0.100MPa, and the use amount of described primer is 100 ~ 300g/ fiber aluminum lithium alloy laminate m
2;
(2) bonding good fiber aluminum lithium alloy laminate carries out heat-pressure curing: the vacuum bag of above-mentioned preservation fiber aluminum lithium alloy laminate is at the uniform velocity warmed up to 20 ℃ of-40 ℃ of temperature, and be incubated 10-20min, be forced into again 0.6-1MPa, be warmed up to 160-200 ℃ of temperature and be incubated 1-3 hour, solidify and finish rear cool to room temperature, remove vacuum bag, make fiber aluminum lithium alloy laminate.
Before step described in the inventive method () aluminum lithium alloy plate carries out phosphoric acid or sulfur acid anodizing processing, aluminum lithium alloy plate carries out degreasing and deoxidation treatment according to a conventional method, then carries out phosphoric acid or sulfur acid anodizing and processes.
The present invention has following positive effect:
(1) fiber aluminum lithium alloy laminate of the present invention adopts the little 10-15% of density of the density ratio aluminum alloy (2024 or 7075) of aluminum lithium alloy (2060 or 2198), can further reduce the density of fiber aramid aluminiumlaminates, thereby further improve the strength-to-density ratio of this type of laminate.
(2) decay resistance of aluminum lithium alloy (2060 or 2198) is than the corrosion resistance and good of aluminum alloy (2024 or 7075), further the decay resistance of fortifying fibre aluminum lithium alloy laminate.
(3) the anti-damage tolerance performance of aluminum lithium alloy (2060 or 2198) is higher than the anti-damage tolerance performance of aluminum alloy (2024 or 7075), can further improve the anti-damage tolerance performance of fiber aluminum lithium alloy laminate.
(4) static strength of aluminum lithium alloy (2060 or 2198) is higher than the static strength of aluminum alloy (2024 or 7075), adopts aluminum lithium alloy (2060 or 2198) can further improve the static strength of fiber aluminum lithium alloy laminate.
(5) the alternative existing aluminium alloy plate of fiber aluminum lithium alloy laminate provided by the invention has the advantages such as high strength high anti-damage tolerance limit as aircraft target ship.
(6) fiber aluminum lithium alloy laminate provided by the invention substitutes existing aluminium alloy plate as aircraft target ship, can significantly reduce the structural weight of aircraft, increases the thrust-weight ratio of aircraft, is conducive to flight.
(7) the present invention adopts phosphoric acid or the sulfur acid anodizing aluminum lithium alloy plate treatment process of novel environment friendly, makes preparation technology's environmental protection more of laminate.
Fiber aluminum lithium alloy laminate provided by the invention has the advantages such as high strength high anti-damage tolerance limit as aircraft target ship, significantly reduces the structural weight of aircraft, increases the thrust-weight ratio of aircraft.Preparation method of the present invention is simple, is suitable for suitability for industrialized production, has larger using value.
The specific embodiment
By specific embodiment, technical scheme of the present invention is described in detail below.
Embodiment 2198 aluminum lithium alloy plates used are by commercially available buying (Alcoa) below.
The 2198 aluminum lithium alloy plates of buying all need to process according to a conventional method: first with acetone, wash away greasy dirt, then use three sour deoxidations (three acid, for nitric acid, chromic acid and hydroflouric acid, are that 3:1:2 joins three acid solutions according to mass ratio)
embodiment 1
Material: 2198 aluminum lithium alloy laminates, thickness 0.2mm
Glass fibre prepreg consists of glass fibre (commercially available, Zhuhai glass) and epoxy resin (commercially available, Shanghai loyal Kanggong department), and fiber volume fraction is 50%, and the bed thickness of glass fibre prepreg is 0.3mm.
Preparation: the first step: aluminum lithium alloy plate 500 * 1000mm (science popularization reaches board) in anodic oxydation treatment groove is carried out to phosphoric acid processing: H
3pO
4mass percent is 130g/L, and anodic oxydation treatment temperature is 25 ℃, and anodic oxydation treatment vdc is 15V, and the anodic oxydation treatment time is 20min.After anodizing, with water purification, rinse aluminum lithium alloy plate 8min, then toast 15min in the baking oven of 60 ℃.
Second step: the even brushing one deck of side surface epoxy resin primer of 2198 aluminum lithium alloy laminates after anodizing, the use amount of primer is 200g/m
2, the bake out temperature that scribbles the aluminum lithium alloy plate of primer is 90 ℃, baking time is 6 hours.The aluminum lithium alloy laminate that afterwards painting is brushed with to primer mutually replaces laying with prepreg and becomes as a whole, and utilizes vacuum bag that fiber aluminium alloy layer intralamellar part is formed to a vacuum system (vacuum pressure reduction 0.095MPa).
The 3rd step: heat-pressure curing: the vacuum bag that fiber aramid aluminiumlaminates is housed is at the uniform velocity warmed up to than 140 ℃ of the solidification temperatures of primer, and be incubated 15min, be forced into again 0.8MPa, finally be warmed up to 170 ℃ and be incubated 2 hours, solidify and finish rear cool to room temperature (25 ℃), remove vacuum bag, make fiber aramid aluminiumlaminates.
embodiment 2
Material: 2060 aluminum lithium alloy laminates, thickness 0.2mm;
Glass fibre prepreg, consists of glass fibre and epoxy resin, and fiber volume fraction is 50%, and the bed thickness of glass fibre prepreg is 0.3mm.
Equipment is with embodiment 1.
Preparation: the first step: aluminum lithium alloy laminate is carried out to phosphoric acid processing: H
3pO
4mass percent is 135g/L, and anodic oxydation treatment temperature is 25 ℃, and anodic oxydation treatment vdc is 15V, and the anodic oxydation treatment time is 20min.After anodizing, aluminum lithium alloy rinses 8min with water purification, in the baking oven of 60 ℃, toasts 15min.
Second step: the even brushing one deck of the 2060 aluminum lithium alloy laminate one side surface epoxy resin primer after anodizing, the use amount of primer is 200g/m
2, the bake out temperature that scribbles primer resume alloy sheets is 90 ℃, baking time is 6 hours.The aluminum lithium alloy plate that afterwards painting is brushed with to primer contacts with prepreg and mutually replaces laying and becomes as a whole, and utilizes vacuum bag by the inner vacuum system (vacuum pressure reduction 0.095MPa) that forms of the laminate of completing.
The 3rd step: heat-pressure curing: the vacuum bag that fiber aramid aluminiumlaminates is housed is at the uniform velocity warmed up to than 140 ℃ of the solidification temperatures of primer, and be incubated 15min, be forced into again 0.8MPa, be finally warmed up to 170 ℃ and be incubated 2 hours, solidify finish after cool to room temperature (25 ℃).Remove vacuum bag, make fiber aramid aluminiumlaminates.
embodiment 3
Material: 2198 aluminum lithium alloy laminates, thickness 0.2mm;
Glass fibre prepreg, consists of glass fibre and epoxy resin, and fiber volume fraction is 50%, and the bed thickness of glass fibre prepreg is 0.3mm.
Preparation: the first step: the aluminum lithium alloy laminate of lower honest material is carried out to sulfur acid anodizing processing: H
3sO4 mass percent is 50g/L, and anodic oxydation treatment temperature is 25 ℃, and anodic oxydation treatment vdc is 15V, and the anodic oxydation treatment time is 20min.After anodizing, aluminum lithium alloy laminate rinses 8min with clean water, in the baking oven of 60 ℃, toasts 15min.
Second step: the even brushing one deck of the 2198 aluminum lithium alloy laminate one side surface epoxy resin primer after anodizing, the use amount of primer is 200g/m
2, the bake out temperature of primer is 90 ℃, baking time is 6 hours.The aluminum lithium alloy laminate that afterwards painting is brushed with to primer mutually replaces laying with prepreg and becomes as a whole, and utilizes vacuum bag by the inner vacuum system (vacuum pressure reduction 0.095MPa) that forms of the laminate of completing.
The 3rd step: heat-pressure curing: the vacuum bag that fiber aramid aluminiumlaminates is housed is at the uniform velocity warmed up to than 140 ℃ of the solidification temperatures of primer, and be incubated 15min, be forced into again 0.8MPa, be finally warmed up to 170 ℃ and be incubated 2 hours, solidify finish after with stove cool to room temperature (25 ℃).Remove vacuum bag, make fiber aramid aluminiumlaminates.
Embodiment 4
Material: 2060 aluminum lithium alloy laminates, thickness 0.2mm;
Glass fibre prepreg, consists of glass fibre and epoxy resin, and fiber volume fraction is 50%, and the bed thickness of glass fibre prepreg is 0.3mm.
Preparation: the first step: aluminum lithium alloy laminate is carried out to sulfur acid anodizing processing, and anodic process is: H
3sO4 mass percent is 55g/L, and anodic oxydation treatment temperature is 25 ℃, and anodic oxydation treatment vdc is 15V, and the anodic oxydation treatment time is 20min.After anodizing, aluminum lithium alloy rinses 8min with water purification, in the baking oven of 60 ℃, toasts 15min.
Second step: the even brushing one deck of the 2060 aluminum lithium alloy sheet material one side surface epoxy resin primer after anodizing, the use amount of primer is 200g/m
2, the bake out temperature of primer is 90 ℃, baking time is 6 hours.The aluminum lithium alloy plate that afterwards painting is brushed with to primer mutually replaces laying with prepreg and becomes as a whole, and utilizes vacuum bag by the inner vacuum system (vacuum pressure reduction 0.095MPa) that forms of the laminate of completing.
The 3rd step: heat-pressure curing: the vacuum bag that fiber aramid aluminiumlaminates is housed is at the uniform velocity warmed up to than 140 ℃ of the solidification temperatures of primer, and be incubated 15min, be forced into again 0.8MPa, be finally warmed up to 170 ℃ and be incubated 2 hours, solidify finish after with stove cool to room temperature (25 ℃).Remove vacuum bag, make fiber aramid aluminiumlaminates.
Claims (6)
1. as a fiber aluminum lithium alloy laminate for aircraft target ship, it is characterized in that, described fiber aluminum lithium alloy laminate is made by primer is bonding by aluminum lithium alloy plate-fiber prepreg material-aluminum lithium alloy plate successively laying alternate with each other.
2. the fiber aluminum lithium alloy laminate as aircraft target ship, it is characterized in that, described fiber aluminum lithium alloy laminate is bonded by primer by aluminum lithium alloy plate-fiber prepreg material-aluminum lithium alloy plate-fiber prepreg material-aluminum lithium alloy plate structure successively laying alternate with each other.
3. a kind of fiber aluminum lithium alloy laminate as aircraft target ship according to claim 1 and 2, is characterized in that, described aluminum lithium alloy plate is selected from 2198 or 2060 aluminum lithium alloy plates, and thickness is 0.2 ~ 0.5mm.
4. a kind of fiber aluminum lithium alloy laminate as aircraft target ship according to claim 1 and 2, is characterized in that, described fiber prepreg material is made by fiber and resin matrix; Described fiber is selected from carbon fiber, glass fibre or aramid fiber prepreg; The content of described fiber in prepreg is 50%; Described resin matrix is epoxy resin.
5. a kind of fiber aluminum lithium alloy laminate as aircraft target ship according to claim 1 and 2, is characterized in that, described fiber prepreg material is individual layer, bilayer or three layers, and the thickness of described single layer fibre prepreg is 0.2 ~ 0.5mm; Machine direction between described double-deck prepreg is 0 °, direction, 45 ° or 90 ° of angles.
6. be used as claimed in claim 1 a preparation method for the fiber aluminum lithium alloy laminate of aircraft target ship, it is characterized in that, the method comprises the following steps:
(1) aluminum lithium alloy laminate is processed:
(1) aluminum lithium alloy plate carries out sour anodizing:
Aluminum lithium alloy laminate is according to a conventional method: first with acetone, wash away greasy dirt, then use three sour deoxidation treatment, described three acid are nitric acid, chromic acid and hydroflouric acid, according to mass ratio, are that 3:1:2 joins three acid solutions, then carry out sour anodizing;
I, aluminum lithium alloy plate carry out phosphoric acid (H
3pO
4) anodizing: phosphoric acid quality percentum is 100 ~ 160g/L, and anodic oxydation treatment temperature is 15-35 ℃, and anodic oxydation treatment vdc is 10-20V, and the anodic oxydation treatment time is 15-30min; Or
II, aluminum lithium alloy plate carry out sulfuric acid H
3sO4 anodizing: sulfuric acid mass percent is 35 ~ 65g/L, anodic oxydation treatment temperature is 15-35 ℃, and anodic oxydation treatment vdc is 10-20V, and the anodic oxydation treatment time is 15-30min;
Aluminum lithium alloy plate carries out, after sour anodizing, rinsing 5-10min in water, in the baking oven of 50 ~ 70 ℃, toasts 15min;
(3) through the even brushing one deck of side surface primer of anodized aluminum lithium alloy plate, dry; Described primer is that the use amount of epoxy resin primer is 100 ~ 300g/m
2, bake out temperature is 80 ~ 100 ℃, drying time is 4 ~ 8 hours;
(2) fiber prepreg material preparation:
The fiber volume fraction of described fiber prepreg material is 50%, and the layer thickness of fiber prepreg material is 0.2 ~ 0.5mm;
(3) prepare fiber aluminum lithium alloy laminate
(1) prepreg prepared by the aluminum lithium alloy plate of step () being processed and step (two) is laying alternate with each other successively, by primer epoxy resin bonding, make fiber aluminum lithium alloy laminate, be stored in vacuum bag, vacuum pressure reduction is 0.095-0.100MPa, and the use amount of described primer is 100 ~ 300g/m
2;
(2) bonding good fiber aluminum lithium alloy laminate carries out heat-pressure curing: vacuum bag is at the uniform velocity warmed up to 20 ℃ of-40 ℃ of temperature, and be incubated 10-20min, be forced into again 0.6-1MPa, be warmed up to 120 ℃-140 ℃ and be incubated 1-3 hour, solidify and finish rear cool to room temperature, remove vacuum bag, make fiber aluminum lithium alloy laminate.
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| CN105538745A (en) * | 2015-12-14 | 2016-05-04 | 中国商用飞机有限责任公司 | Forming method of aluminum alloy fiber laminate structural part and laminate structural part thereof |
| CN106515188A (en) * | 2016-12-03 | 2017-03-22 | 上海海洋大学 | Stress releasing forming method of super-hybrid fiber magnesium alloy laminated plate |
| CN106739364A (en) * | 2016-11-28 | 2017-05-31 | 株洲时代新材料科技股份有限公司 | A kind of aramid fiber/Al alloy composite and its preparation method and application |
| CN107499495A (en) * | 2017-07-11 | 2017-12-22 | 中北大学 | A kind of composite wing skins front edges of interior pad sandwich core material and preparation method thereof |
| CN108284623A (en) * | 2018-01-29 | 2018-07-17 | 江苏金风科技有限公司 | The manufacturing process of blade part |
| CN109415836A (en) * | 2016-04-18 | 2019-03-01 | 福克航空结构公司 | The anode oxidation method of aluminium or its alloy product |
| CN113103620A (en) * | 2021-04-16 | 2021-07-13 | 武汉理工大学 | Method for manufacturing subway fan blade |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105538745A (en) * | 2015-12-14 | 2016-05-04 | 中国商用飞机有限责任公司 | Forming method of aluminum alloy fiber laminate structural part and laminate structural part thereof |
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| CN106515188A (en) * | 2016-12-03 | 2017-03-22 | 上海海洋大学 | Stress releasing forming method of super-hybrid fiber magnesium alloy laminated plate |
| CN107499495A (en) * | 2017-07-11 | 2017-12-22 | 中北大学 | A kind of composite wing skins front edges of interior pad sandwich core material and preparation method thereof |
| CN108284623A (en) * | 2018-01-29 | 2018-07-17 | 江苏金风科技有限公司 | The manufacturing process of blade part |
| CN113103620A (en) * | 2021-04-16 | 2021-07-13 | 武汉理工大学 | Method for manufacturing subway fan blade |
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