CN103612431A - Novel composite aircraft skin material with characteristics of light weight, high strength and high temperature resistance - Google Patents
Novel composite aircraft skin material with characteristics of light weight, high strength and high temperature resistance Download PDFInfo
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- CN103612431A CN103612431A CN201310424561.XA CN201310424561A CN103612431A CN 103612431 A CN103612431 A CN 103612431A CN 201310424561 A CN201310424561 A CN 201310424561A CN 103612431 A CN103612431 A CN 103612431A
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Abstract
The present invention discloses a novel composite aircraft skin material with characteristics of light weight, high strength and high temperature resistance. The composite material comprises three layers such as a titanium alloy layer, an aluminum alloy layer and a titanium alloy layer, wherein the material trademark of the titanium alloy is Ti-6Al-4V, the titanium alloy comprises 5.5-6.75% of aluminum, 3.5-4.5% of vanadium, and the balance of titanium, the material of the aluminum alloy is 2024, the thickness is 8 mm, and the chemical components of 2024 comprise 0.5% of silicon, 0.5% of iron, 3.8-4.9% of copper, 0.3-0.9% of manganese, 1.2-1.8% of magnesium, 0.10% of chromium, 0.25% of zinc, 0.15% of titanium, and the balance of aluminum. According to the present invention, the binding rate of the composite material achieves 100%, the strength of the bonding interface achieves the aluminum alloy yield strength, and the novel composite aircraft skin material is the novel composite aircraft skin material with characteristics of light weight, high strength and high temperature resistance.
Description
Technical field
The present invention is a kind of novel light, high-strength, high temperature resistant compound aircraft skin material, belongs to field of compound material.
Background technology
Aircraft skin is to maintain aircraft configuration, makes it to have one deck structural material of good aerodynamic characteristics.Covering bears after aerodynamic effect force transmission to connected fuselage wing skeleton, and stressed complexity, and directly contacting with the external world not only requires that skin material intensity is high, plasticity good, also requires smooth surface, has higher resistance to corrosion.Conventional aircraft skin material has aluminium alloy, steel alloy, carbon fiber load material and titanium alloy.Its density of aluminium alloy is little, intensity is higher, apply wider, but its poor heat resistance, in the time of 150 ℃, specific strength obviously declines, operating temperature is below 200 ℃.High heat when high strength alloy steel can bear hypersonic flight, but the density of steel alloy is too large, will greatly increase aircraft flight load.Also there is part aircraft skin to use carbon fibre material and titanium alloy, but the impact resistance of carbon fiber is not good enough, and non-refractory, titanium alloy has the feature of low-density and high specific strength, can effectively alleviate aircraft weight, its durable temperature is high, the high heat condition in the time of adapting to high-speed flight, but pure titanium alloy material is expensive, be difficult to promote.
As can be seen here, aircraft of new generation needs a kind of novel light, high-strength, high temperature resistant skin material, thereby meet, aircraft flight speed is more and more faster, serviceability temperature is more and more higher and the requirement of loss of weight.
Summary of the invention
Goal of the invention: for the deficiencies in the prior art, the object of this invention is to provide a kind of lightweight, high-strength, high temperature resistant compound aircraft skin material, it is 100% in conjunction with rate, and its bond strength meets the law of force of bimetallic solid phase metallurgical binding.
Technical scheme: in order to realize foregoing invention object, the technical solution used in the present invention is:
(1) this lightweight, high-strength, high temperature resistant compound aircraft skin material are comprised of three-layer metal material: upper and lower two-layer titanium alloy layer and middle aluminium alloy layer.Ablation that titanium alloy is high temperature resistant, elevated temperature strength is high, can at high temperature use for a long time; Titanium alloy layer can play support structure effect, has the advantages that lightweight and specific strength are high.
(2) with emery wheel and polishing machine, the surface finish of three-ply metal is polished to surface roughness Ra < 6nm.
(3) three-ply metal is positioned on ground successively, it is sequentially titanium alloy sheet, aluminium alloy plate and titanium alloy sheet, centre is put separation material each layer is supported, the Bing the superiors lay explosive, the upper detonator of inserting, lights detonator, and ignition charge produces detonation wave, promote each layer and clash into successively, make three-ply metal be combined into clad metal sheet.
(4) detonation wave impacts the stress staying to metallic plate when eliminating explosive welding, and preferably suitable annealing temperature, puts into heat-treatment furnace by this clad metal sheet and anneal.
(5) this metallic composite offseted, rolls thin and anneal for the second time.
(6), by this composite metal plate deburring, school shape, pickling and polishing, can make lightweight, high-strength, high temperature resistant compound aircraft skin material.
Beneficial effect of the present invention: the feature of maximum of the present invention is three-layer sandwich structure, the heat-resisting difference of original aluminium alloy and the expensive shortcoming of titanium alloy have been solved, greatly improved the resistance to elevated temperatures of composite and reduced cost, can be used for, in the covering manufacture of airborne vehicle, being beneficial to the loss of weight of airborne vehicle and the raising of flying speed.
Accompanying drawing explanation
Fig. 1 is lightweight, high-strength, high temperature resistant compound aircraft skin material structure schematic diagram.
Fig. 2 is lightweight, high-strength, high temperature resistant compound aircraft skin material preparation facilities schematic diagram.
The specific embodiment
Embodiment 1:
The material trademark of titanium alloy is Ti-6Al-4V, and thickness is 2mm, its chemical composition: aluminium: 5.5%-6.75%, and vanadium: 3.5%-4.5%, surplus is titanium.The material of aluminium alloy is 2024, and thickness is 8mm, 2024 chemical compositions: silicon: 0.5%, iron: 0.5%, copper: 3.8-4.9, manganese: 0.3-0.9, magnesium: 1.2-1.8, chromium: 0.10, zinc: 0.25, titanium: 0.15, surplus is aluminium.The shot elevation of explosive is 25mm, and gap is 4mm.
Titanium alloy Ti-6Al-4V wherein, has good corrosion resistance, little density, high specific strength and the series of advantages such as toughness and weldability preferably.And the main alloy element of aluminium alloy 2024 is Cu, Mg, Mn, it has higher plasticity, fatigue life, fracture toughness and fatigue crack scalability, but corrosion resistance is poor.
Concrete steps:
(1) this lightweight, high-strength, high temperature resistant compound aircraft skin material are comprised of three-layer metal material: upper and lower two-layer titanium alloy layer (2), (5) and middle aluminium alloy layer (4).Titanium alloy layer (2), (5) are high temperature resistant ablation, elevated temperature strength is high, can at high temperature use for a long time; Aluminium alloy layer (4) can play support structure effect, has the advantages that lightweight and specific strength are high.
(2) with emery wheel and polishing machine, the surface finish of three-ply metal is polished to surface roughness Ra < 6nm.
(3) three-ply metal is positioned on ground successively, it is sequentially titanium alloy sheet (2), aluminium alloy plate (4) and titanium alloy sheet (5), centre is put separation material (3) each layer is supported, the Bing the superiors lay explosive (6), the upper detonator (7) of inserting, lights detonator (7), and ignition charge (6) produces detonation wave, promote each layer and clash into successively, make three-ply metal be combined into clad metal sheet.
(4) detonation wave impacts the stress staying to metallic plate when eliminating explosive welding, and preferably annealing temperature is 350 ℃, this clad metal sheet is put into heat-treatment furnace and anneal.
(5) this metallic composite offseted, rolls thin and anneal for the second time, annealing temperature is 350 ℃.
(6), by this composite metal plate deburring, school shape, pickling and polishing, can make lightweight, high-strength, high temperature resistant compound aircraft skin material.
Through check, the seam rate of this compound aircraft skin is 100%, bimetallic has reached 396MPa in conjunction with intensity, while standing failure by shear, destroying does not occur on combination interface, completely can bear in processing and be out of shape, this material bond strength is high, density is low, high temperature resistant, is a kind of good aircraft skin material.
Claims (2)
1. novel light, high-strength, a high temperature resistant compound aircraft skin material, is characterized in that this lightweight, high-strength, high temperature resistant compound aircraft skin material are comprised of three-layer metal material: upper and lower two-layer titanium alloy layer and middle aluminium alloy layer.Ablation that titanium alloy is high temperature resistant, elevated temperature strength is high, can at high temperature use for a long time; Titanium alloy layer can play support structure effect, has the advantages that lightweight and specific strength are high.
2. a kind of novel light according to claim 1, high-strength, high temperature resistant compound aircraft skin material, is characterized in that its preparation method comprises following content:
(1) with emery wheel and polishing machine, the surface finish of three-ply metal is polished to surface roughness Ra < 6nm.
(2) three-ply metal is positioned on ground successively, it is sequentially titanium alloy sheet, aluminium alloy plate and titanium alloy sheet, centre is put separation material each layer is supported, the Bing the superiors lay explosive, the upper detonator of inserting, lights detonator, and ignition charge produces detonation wave, promote each layer and clash into successively, make three-ply metal be combined into clad metal sheet.
(3) detonation wave impacts the stress staying to metallic plate when eliminating explosive welding, and preferably suitable annealing temperature, puts into heat-treatment furnace by this clad metal sheet and anneal.
(4) this metallic composite offseted, rolls thin and anneal for the second time.
(5), by this composite metal plate deburring, school shape, pickling and polishing, can make lightweight, high-strength, high temperature resistant compound aircraft skin material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201310424561.XA CN103612431A (en) | 2013-09-18 | 2013-09-18 | Novel composite aircraft skin material with characteristics of light weight, high strength and high temperature resistance |
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| CN201310424561.XA CN103612431A (en) | 2013-09-18 | 2013-09-18 | Novel composite aircraft skin material with characteristics of light weight, high strength and high temperature resistance |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106944736A (en) * | 2017-05-22 | 2017-07-14 | 史少杰 | The double vertical explosive welding 3-layer composite materials of the high corrosion resistant titanium/aluminium/titanium of light-high-strength |
| CN109398676A (en) * | 2017-08-16 | 2019-03-01 | 张跃 | A kind of transatmospheric vehicle structure |
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| CN101010190A (en) * | 2004-08-26 | 2007-08-01 | 克拉德许可股份公司 | Multilayer, plate-shaped composite material used for the production of cooking utensils suitable for induction stovetops by means of shaping |
| CN101319333A (en) * | 2008-07-14 | 2008-12-10 | 昆明理工大学 | Titanium/aluminum composite board and production method thereof |
| CN202639757U (en) * | 2011-08-31 | 2013-01-02 | 南京三邦金属复合材料有限公司 | Large-sized non-ferrous metal explosive cladding steel plate |
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| CN101010190A (en) * | 2004-08-26 | 2007-08-01 | 克拉德许可股份公司 | Multilayer, plate-shaped composite material used for the production of cooking utensils suitable for induction stovetops by means of shaping |
| CN101319333A (en) * | 2008-07-14 | 2008-12-10 | 昆明理工大学 | Titanium/aluminum composite board and production method thereof |
| CN202639757U (en) * | 2011-08-31 | 2013-01-02 | 南京三邦金属复合材料有限公司 | Large-sized non-ferrous metal explosive cladding steel plate |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106944736A (en) * | 2017-05-22 | 2017-07-14 | 史少杰 | The double vertical explosive welding 3-layer composite materials of the high corrosion resistant titanium/aluminium/titanium of light-high-strength |
| CN106944736B (en) * | 2017-05-22 | 2019-02-12 | 史少杰 | The double vertical explosive welding 3-layer composite materials of the high corrosion resistant titanium/aluminium/titanium of light-high-strength |
| CN109398676A (en) * | 2017-08-16 | 2019-03-01 | 张跃 | A kind of transatmospheric vehicle structure |
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Application publication date: 20140305 |