CN103144764B - A kind of Wing panel with sandwich structure - Google Patents
A kind of Wing panel with sandwich structure Download PDFInfo
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- CN103144764B CN103144764B CN201310067208.0A CN201310067208A CN103144764B CN 103144764 B CN103144764 B CN 103144764B CN 201310067208 A CN201310067208 A CN 201310067208A CN 103144764 B CN103144764 B CN 103144764B
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Abstract
The invention provides a kind of wing shell for aircraft, comprise sandwich structure, it uses metal, fiber and ceramic laminar composite material to make, there is the sandwich structure that at least one metal level/fibrage/ceramic layer is formed, it is characterized in that metal level adopts aluminium, magnesium, titanium or corresponding alloy material, fibrage adopts glass fibre, kevlar fiber, carbon fiber, silicon nitride, carborundum or zirconia fiber, and described ceramic layer comprises zirconia and niobium/toughness reinforcing phase of titanium/nickel.Wing shell hardness of the present invention is high, good toughness, quality light, has good shock resistance.
Description
Technical field
The present invention relates to a kind of Wing panel with sandwich structure, particularly relate to a kind of wing shell with sandwich structure.
Background technology
Current, large scale business jet airplane all have employed high thrust turbofan aero-engine usually, the turbofan aero-engine of the type all employ large-sized fan blade, maximum fan blade diameter can reach 3m, during work, the tangential speed at fan blade tip place is more than 450m/s, the development of following turbofan aero-engine, the tangential speed of turbofan blade tip can be higher.The blade of high-speed operation is subject to the impact of foreign object strike damage or high-frequency vibration fatigue etc., inevitably leaf destruction fault.Broken blade has very high energy, if blade punctures engine nacelle, then may produce infringement to the wing shell near engine mounting positions, and then jeopardize birdman's safety.Current aircraft wing shell adopts light-weight metal magnalium titanium or their alloy to manufacture usually, also some aircraft then adopts composite material, but current wing shell is still difficult to keep out the broken blade as the aforementioned with very heavy impulse or the shock being other.
Summary of the invention
In order to overcome above-mentioned shortcoming and drawback, the invention provides a kind of wing shell for aircraft, comprise sandwich structure, it uses metal, fiber and ceramic laminar composite material are made, there is the sandwich structure that at least one metal level/fibrage/ceramic layer is formed, it is characterized in that metal level adopts aluminium, magnesium, titanium or corresponding alloy material, fibrage adopts glass fibre, kevlar fiber, carbon fiber, silicon nitride, carborundum or zirconia fiber, described ceramic material layer mixes niobium powder by zirconia base with the ratio according to weight ratio 4:3:2 or 5:4:3, what titanium valve and nickel powder were made is toughness reinforcingly formed mutually, wherein zirconia base is 2:1 or 3:1 with the volume ratio of toughness reinforcing phase.
Preferably, niobium powder, titanium valve and the nickel powder of selecting purity to be greater than 99.5% mix according to the ratio of weight ratio 4:3:2, carry out ball milling 100 hours under nitrogen protection, obtain toughness reinforcing phase powder; Then, get Zirconium powder and mix according to the ratio of volume ratio 2:1 with toughness reinforcing phase powder, ball milling 5 hours in ball grinding mill, then drying, granulation, shaping, at the temperature of 1600-1750 degree Celsius, sinter 1.8 hours, total temperature rise time is 8 hours; Be cooled to 1200 degrees Celsius of heat treatments 3.5 hours with 220 comfort level speed hourly again, then naturally cool to room temperature, then sample is warming up to 1460 degrees Celsius of heat treatments 1.6 hours, then again naturally cool to room temperature and can obtain described stupalith.
Preferably, described niobium powder, titanium valve and nickel powder are the ratio mixing of 5:4:3 according to weight ratio, carry out ball milling 90 hours under nitrogen protection, obtain toughness reinforcing phase powder; Then, get Zirconium powder and mix according to the ratio of volume ratio 3:1 with toughness reinforcing phase powder, ball milling 5.5 hours in ball grinding mill, then drying, granulation, shaping, at the temperature of 1600-1700 degree Celsius, sinter 2.0 hours, total temperature rise time is 9 hours; Be cooled to 1250 degrees Celsius of heat treatments 4.0 hours with 230 degrees Celsius of speed hourly again, then naturally cool to room temperature, then sample is warming up to 1480 degrees Celsius of heat treatments 1.5 hours, then again naturally cool to room temperature and can obtain described stupalith.
Preferably, described wing shell is followed successively by metal level, fibrage, ceramic layer from inside to outside, lamination coating can be winding of single layer also can be multiple wraps, if multiple wraps, preferably between multilayer, machine direction is crisscross arranged, thickness 1.5mm ~ the 3mm of metal level, the thickness 5mm ~ 8mm of ceramic layer.
Preferably, wing shell is followed successively by metal level, fibrage, ceramic layer, fibrage, metal level from inside to outside, lamination coating can be winding of single layer also can be multiple wraps, if multiple wraps, preferably between multilayer, machine direction is crisscross arranged, thickness 1.5mm ~ the 2mm of interior metal layer, the thickness 3mm ~ 6mm of ceramic layer, the thickness 1.5mm ~ 3.0mm of outer layer metal layer.
Preferably, wing shell is followed successively by metal level, fibrage, ceramic layer, fibrage, ceramic layer from inside to outside, lamination coating can be winding of single layer also can be multiple wraps, if multiple wraps, preferably between multilayer, machine direction is crisscross arranged, thickness 1.5mm ~ the 3mm of metal level, the thickness 3mm ~ 5mm of internal layer ceramic layer, the thickness 4mm ~ 6mm of outer pottery.
Preferably, described sandwich structure adopts the macromolecule resin material such as epoxy resin or polyimide metal level, fibrage and ceramic layer bonding to be got up by solidification process as adhesive agent.
Owing to have employed high tenacity, porous zirconia stupalith in the present invention, wing shell according to the present invention has very excellent shock resistance, has lower density simultaneously.
Detailed description of the invention
Aircraft wing shell in the present invention has sandwich structure, and it uses metal, fiber and ceramic laminar composite material to make, and has the sandwich structure that at least one metal level/fibrage/ceramic layer is formed.Metal layer is wherein as adopted aluminium, magnesium, titanium or corresponding alloy material, and fibrage adopts glass fibre, kevlar fiber, carbon fiber, silicon nitride, carborundum or zirconia fiber, and described stupalith is a kind of high tenacity zirconia ceramics.
Described zirconia ceramics material take zirconia as matrix, adopts niobium/titanium/nickel as toughness reinforcing phase.Particularly, niobium powder, titanium valve and the nickel powder of first selecting purity to be greater than 99.5% mix according to the ratio of weight ratio 4:3:2, carry out ball milling 100 hours under nitrogen protection, obtain toughness reinforcing phase powder; Then, get Zirconium powder and mix according to the ratio of volume ratio 2:1 with toughness reinforcing phase powder, ball milling 5 hours in ball grinding mill, then drying, granulation, shaping, at the temperature of 1600-1750 degree Celsius, sinter 1.8 hours, total temperature rise time is 8 hours; Be cooled to 1200 degrees Celsius of heat treatments 3.5 hours with 220 comfort level speed hourly again, then naturally cool to room temperature, then sample is warming up to 1460 degrees Celsius of heat treatments 1.6 hours, then again naturally cool to room temperature.
In another embodiment, described niobium powder, titanium valve and nickel powder are the ratio mixing of 5:4:3 according to weight ratio, carry out ball milling 90 hours under nitrogen protection, obtain toughness reinforcing phase powder; Then, get Zirconium powder and mix according to the ratio of volume ratio 3:1 with toughness reinforcing phase powder, ball milling 5.5 hours in ball grinding mill, then drying, granulation, shaping, at the temperature of 1600-1700 degree Celsius, sinter 2.0 hours, total temperature rise time is 9 hours; Be cooled to 1250 degrees Celsius of heat treatments 4.0 hours with 230 degrees Celsius of speed hourly again, then naturally cool to room temperature, then sample is warming up to 1480 degrees Celsius of heat treatments 1.5 hours, then again naturally cool to room temperature.
Described sandwich structure adopts the macromolecule resin material such as epoxy resin or polyimide metal level, fibrage and ceramic layer bonding to be got up by solidification process as adhesive agent.
In one embodiment, manufactured one dull and stereotyped layered composite structure wing shell, be followed successively by metal level, fibrage, ceramic layer from inside to outside, lamination coating can be winding of single layer also can be multiple wraps, if multiple wraps, preferably between multilayer, machine direction is crisscross arranged, the thickness 1.5mm ~ 3mm of metal level, the thickness 5mm ~ 8mm of ceramic layer.
In another embodiment, manufactured one dull and stereotyped layered composite structure wing shell, be followed successively by metal level, fibrage, ceramic layer, fibrage, metal level from inside to outside, lamination coating can be winding of single layer also can be multiple wraps, if multiple wraps, preferably between multilayer, machine direction is crisscross arranged, the thickness 1.5mm ~ 2mm of interior metal layer, thickness 3mm ~ the 6mm of ceramic layer, the thickness 1.5mm ~ 3.0mm of outer layer metal layer.
In another embodiment, manufactured one dull and stereotyped layered composite structure wing shell, be followed successively by metal level, fibrage, ceramic layer, fibrage, ceramic layer from inside to outside, lamination coating can be winding of single layer also can be multiple wraps, if multiple wraps, preferably between multilayer, machine direction is crisscross arranged, thickness 1.5mm ~ the 3mm of metal level, the thickness 3mm ~ 5mm of internal layer ceramic layer, the thickness 4mm ~ 6mm of outer pottery.
Certainly, the wing shell in the present invention also can only be applied to partly near aero-engine installation site near zone.
The aforementioned different embodiment about zirconia ceramics and above-mentioned three specific embodiments about wing shell can combine.And those skilled in the art can make replacement or modification according to content disclosed by the invention and the art technology grasped to content of the present invention; but these replacements or modification should not be considered as disengaging the present invention design, and these replacements or modification are all in the interest field of application claims protection.
Claims (1)
1. the wing shell for close aero-engine installation site near zone, comprise sandwich structure, it uses metal, fiber and ceramic laminar composite material are made, there is the sandwich structure that at least one metal level and fibrage and ceramic layer are formed, metal level adopts aluminium, magnesium or titanium, fibrage adopts glass fibre, kevlar fiber, carbon fiber, silicon nitride, carborundum or zirconia fiber, ceramic layer mixes niobium powder by zirconia base with the ratio according to weight ratio 4:3:2, what titanium valve and nickel powder were made is toughness reinforcingly formed mutually, wherein zirconia base is 2:1 with the volume ratio of toughness reinforcing phase, it is characterized in that the niobium powder selecting purity to be greater than 99.5%, titanium valve and nickel powder mix according to the ratio of weight ratio 4:3:2, carry out ball milling 100 hours under nitrogen protection, obtain toughness reinforcing phase powder, then, get Zirconium powder and mix according to the ratio of volume ratio 2:1 with toughness reinforcing phase powder, ball milling 5 hours in ball grinding mill, then drying, granulation, shaping, at the temperature of 1600-1750 degree Celsius, sinter 1.8 hours, total temperature rise time is 8 hours, be cooled to 1200 degrees Celsius of heat treatments 3.5 hours with 220 degrees Celsius of speed hourly again, then naturally cool to room temperature, then sample is warming up to 1460 degrees Celsius of heat treatments 1.6 hours, then again naturally cool to room temperature and can obtain stupalith, wing shell is followed successively by metal level, fibrage, ceramic layer, fibrage, ceramic layer from inside to outside, the thickness 1.5mm ~ 3mm of metal level, the thickness 3mm ~ 5mm of internal layer ceramic layer, the thickness 4mm ~ 6mm of outer pottery.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310067208.0A CN103144764B (en) | 2013-03-01 | 2013-03-01 | A kind of Wing panel with sandwich structure |
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| CN201310067208.0A CN103144764B (en) | 2013-03-01 | 2013-03-01 | A kind of Wing panel with sandwich structure |
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| CN103144764A CN103144764A (en) | 2013-06-12 |
| CN103144764B true CN103144764B (en) | 2015-12-23 |
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Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4126738A1 (en) * | 1990-12-11 | 1992-06-17 | Claussen Nils | ZR0 (DOWN ARROW) 2 (DOWN ARROW) CERAMIC MOLDED BODY |
| CN1246256C (en) * | 2004-10-13 | 2006-03-22 | 天津大学 | Method for preparing high tenacity stable zirconia ceramics with partial porous network structure |
| CN100497089C (en) * | 2006-09-27 | 2009-06-10 | 北京航空航天大学 | Fibre-reinforced metal/ceramic sheet-like composite container casing and its manufacture method |
| CN100575304C (en) * | 2007-05-25 | 2009-12-30 | 山东大学 | A kind of intermetallic Ni-Al compound/Zirconium oxide ceramic composite material and preparation method thereof |
| CN101565306B (en) * | 2009-05-21 | 2011-12-14 | 济南大学 | Zirconia ceramic matrix composite and preparation method thereof |
| DE102011008574B4 (en) * | 2010-10-12 | 2014-05-15 | Ec Technik Gmbh | A composite panel for an aircraft, assembly and aircraft having such a composite panel, and use and method of making such a composite panel |
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