CN103158858A - Shell of aircraft wing - Google Patents
Shell of aircraft wing Download PDFInfo
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- CN103158858A CN103158858A CN2013100668047A CN201310066804A CN103158858A CN 103158858 A CN103158858 A CN 103158858A CN 2013100668047 A CN2013100668047 A CN 2013100668047A CN 201310066804 A CN201310066804 A CN 201310066804A CN 103158858 A CN103158858 A CN 103158858A
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Abstract
The invention provides a shell of an aircraft wing. The shell of the aircraft wing comprises a sandwich structure and is made of metal, fiber and ceramic laminar composite. The shell of the aircraft wing is provided with at least one sandwich structure which is formed by a metal layer, a fiber layer and a ceramic layer. The shell of the aircraft wing is characterized in that the metal layer is made of aluminum or magnesium or titanium or corresponding alloy material, the fiber layer is made of glass fiber or Kevlar fiber or carbon fiber or silicon nitride fiber or silicon carbide fiber or zirconium dioxide fiber, and the ceramic layer comprises zirconium oxide, magnesium oxide, calcium oxide, yttrium oxide and cerium oxide. The shell of the aircraft wing is high in rigidity, good in toughness and light in mass and has excellent shock resistance.
Description
Technical field
The present invention relates to a kind of aircraft wing shell, relate in particular to a kind of wing shell with sandwich structure.
Background technology
Current, the large scale business jet airplane has all adopted high thrust turbofan aero-engine usually, the turbofan aero-engine of the type has all used large-sized fan blade, maximum fan blade diameter can reach 3m, during work, the tangential speed at fan blade tip place surpasses 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 subjected to the impact of foreign object strike damage or high-frequency vibration fatigue etc., inevitably the leaf destruction fault can occur.Broken blade has very high energy, if blade punctures engine nacelle, may produce infringement near the wing shell the driving engine installation site, and then jeopardize birdman's safety.Current aircraft wing shell adopts light-weight metal magnalium titanium or their alloy to make usually, also some aircraft adopts composite material, but current wing shell still is difficult to keep out the broken blade that has as the aforementioned heavy impulse very or is other shock.
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, has the sandwich structure that at least one metal level/fibrage/ceramic layer consists of, it is characterized in that metal level adopts aluminium, magnesium, titanium or corresponding alloy material, fibrage adopts glass fibre, the kevlar fiber, carbon fiber, silicon nitride, carborundum or zirconia fiber, described ceramic layer comprises the zirconia of weight ratio 100:6:4:2:1 or 100:8:3:4:1, magnesium oxide, calcium oxide, yttria and cerium oxide.
Preferably, described zirconia ceramics material adopts zirconia, magnesium oxide, calcium oxide, yttria and the cerium oxide of weight ratio 100:6:4:2:1, add the distilled water heavy with aforementioned Multiple components gross weight etc., ball milling is 5 hours in ball grinding mill, then drying, granulation, moulding, sintering is 1.8 hours at the temperature of 1600-1750 degree centigrade, and total temperature rise time is 8 hours; Be cooled to 1200 degrees centigrade 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 centigrade of heat treatments 1.6 hours, then again naturally cool to room temperature and get final product.
Preferably, described zirconia ceramics material adopts zirconia, magnesium oxide, calcium oxide, yttria and the cerium oxide of weight ratio 100:8:3:4:1, add the distilled water heavy with aforementioned Multiple components gross weight etc., ball milling is 5.5 hours in ball grinding mill, then drying, granulation, moulding, sintering is 2.0 hours at the temperature of 1600-1700 degree centigrade, and total temperature rise time is 9 hours; Be cooled to 1250 degrees centigrade of heat treatments 4.0 hours with 230 degrees centigrade of speed hourly again, then naturally cool to room temperature, then sample is warming up to 1480 degrees centigrade of heat treatments 1.5 hours, then again naturally cool to room temperature and get final product.
Preferably, described wing shell is followed successively by metal level, fibrage, ceramic layer from inside to outside, lamination coating can be that winding of single layer can be also 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, the wing shell is followed successively by metal level, fibrage, ceramic layer, fibrage, metal level from inside to outside, lamination coating can be that winding of single layer can be also multiple wraps, if multiple wraps, preferably between multilayer, machine direction is crisscross arranged, thickness 1.5mm～the 2mm of inner layer metal layer, the thickness 3mm～6mm of ceramic layer, the thickness 1.5mm～3.0mm of outer layer metal layer.
Preferably, the wing shell is followed successively by metal level, fibrage, ceramic layer, fibrage, ceramic layer from inside to outside, lamination coating can be that winding of single layer can be also 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, the Polymer resin materials such as described sandwich structure employing epoxy resin or polyimide are processed by curing as adhesive agent metal level, fibrage and ceramic layer are bondd.
Owing to having adopted high tenacity, porous zirconia stupalith in the present invention, wing shell according to the present invention has very excellent shock resistance, has simultaneously lower density.
The specific embodiment
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 consists of.Metal level wherein for example adopts aluminium, magnesium, titanium or corresponding alloy material, fibrage adopts glass fibre, kevlar fiber, carbon fiber, silicon nitride, carborundum or zirconia fiber, and described stupalith is a kind of zirconia ceramics of high tenacity porous.
Described zirconia ceramics material adopts zirconia, magnesium oxide, calcium oxide, yttria and the cerium oxide of weight ratio 100:6:4:2:1, add the distilled water heavy with aforementioned Multiple components gross weight etc., ball milling is 5 hours in ball grinding mill, then drying, granulation, moulding, sintering is 1.8 hours at the temperature of 1600-1750 degree centigrade, and total temperature rise time is 8 hours; Be cooled to 1200 degrees centigrade 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 centigrade of heat treatments 1.6 hours, then again naturally cool to room temperature and get final product.
In another embodiment, described zirconia ceramics material adopts zirconia, magnesium oxide, calcium oxide, yttria and the cerium oxide of weight ratio 100:8:3:4:1, add the distilled water heavy with aforementioned Multiple components gross weight etc., ball milling is 5.5 hours in ball grinding mill, then drying, granulation, moulding, sintering is 2.0 hours at the temperature of 1600-1700 degree centigrade, and total temperature rise time is 9 hours; Be cooled to 1250 degrees centigrade of heat treatments 4.0 hours with 230 degrees centigrade of speed hourly again, then naturally cool to room temperature, then sample is warming up to 1480 degrees centigrade of heat treatments 1.5 hours, then again naturally cool to room temperature and get final product.
Described sandwich structure adopts the Polymer resin materials such as epoxy resin or polyimide to process by curing as adhesive agent metal level, fibrage and ceramic layer is bondd.
In one embodiment, a kind of dull and stereotyped layered composite structure wing shell of manufacturing, be followed successively by from inside to outside metal level, fibrage, ceramic layer, lamination coating can be that winding of single layer can be also 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, a kind of dull and stereotyped layered composite structure wing shell of manufacturing, be followed successively by from inside to outside metal level, fibrage, ceramic layer, fibrage, metal level, lamination coating can be that winding of single layer can be also multiple wraps, if multiple wraps, preferably between multilayer, machine direction is crisscross arranged, the thickness 1.5mm～2mm of inner layer metal layer, thickness 3mm～the 6mm of ceramic layer, the thickness 1.5mm～3.0mm of outer layer metal layer.
In another embodiment, a kind of dull and stereotyped layered composite structure wing shell of manufacturing, be followed successively by from inside to outside metal level, fibrage, ceramic layer, fibrage, ceramic layer, lamination coating can be that winding of single layer can be also 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.
Aforementioned different embodiment and above-mentioned three specific embodiments about the wing shell about zirconia ceramics can make up.And those skilled in the art can make replacement or modification to content of the present invention according to content disclosed by the invention and the art technology of grasping; but these replacements or modification should not be considered as breaking away from the present invention's design, and these replacements or modification are all in the claimed interest field of the present invention.
Claims (7)
1. wing shell that is used for aircraft, comprise sandwich structure, it uses metal, fiber and ceramic laminar composite material to make, has the sandwich structure that at least one metal level/fibrage/ceramic layer consists of, 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, magnesium oxide, calcium oxide, yttria and the cerium oxide of weight ratio 100:6:4:2:1 or 100:8:3:4:1.
2. wing shell according to claim 1, it is characterized in that described zirconia ceramics material adopts zirconia, magnesium oxide, calcium oxide, yttria and the cerium oxide of weight ratio 100:6:4:2:1, add the distilled water heavy with aforementioned Multiple components gross weight etc., ball milling is 5 hours in ball grinding mill, then drying, granulation, moulding, sintering is 1.8 hours at the temperature of 1600-1750 degree centigrade, and total temperature rise time is 8 hours; Be cooled to 1200 degrees centigrade 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 centigrade of heat treatments 1.6 hours, then again naturally cool to room temperature and get final product.
3. wing shell according to claim 1, it is characterized in that described zirconia ceramics material adopts zirconia, magnesium oxide, calcium oxide, yttria and the cerium oxide of weight ratio 100:8:3:4:1, add the distilled water heavy with aforementioned Multiple components gross weight etc., ball milling is 5.5 hours in ball grinding mill, then drying, granulation, moulding, sintering is 2.0 hours at the temperature of 1600-1700 degree centigrade, and total temperature rise time is 9 hours; Be cooled to 1250 degrees centigrade of heat treatments 4.0 hours with 230 degrees centigrade of speed hourly again, then naturally cool to room temperature, then sample is warming up to 1480 degrees centigrade of heat treatments 1.5 hours, then again naturally cool to room temperature and get final product.
4. according to claim 1-3 described wing shells, it is characterized in that described wing shell is followed successively by metal level, fibrage, ceramic layer from inside to outside, lamination coating can be that winding of single layer can be also 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.
5. according to claim 1-3 described wing shells, it is characterized in that the wing shell is followed successively by metal level, fibrage, ceramic layer, fibrage, metal level from inside to outside, lamination coating can be that winding of single layer can be also multiple wraps, if multiple wraps, preferably between multilayer, machine direction is crisscross arranged, thickness 1.5mm～the 2mm of inner layer metal layer, the thickness 3mm～6mm of ceramic layer, the thickness 1.5mm～3.0mm of outer layer metal layer.
6. according to claim 1-3 described wing shells, it is characterized in that the wing shell is followed successively by metal level, fibrage, ceramic layer, fibrage, ceramic layer from inside to outside, lamination coating can be that winding of single layer can be also 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.
7. wing shell according to claim 1, is characterized in that described sandwich structure adopts the Polymer resin materials such as epoxy resin or polyimide to process by curing as adhesive agent metal level, fibrage and ceramic layer are bondd.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310066804.7A CN103158858B (en) | 2013-03-01 | 2013-03-01 | A kind of aircraft wing shell |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310066804.7A CN103158858B (en) | 2013-03-01 | 2013-03-01 | A kind of aircraft wing shell |
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| Publication Number | Publication Date |
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| CN103158858A true CN103158858A (en) | 2013-06-19 |
| CN103158858B CN103158858B (en) | 2015-11-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310066804.7A Active CN103158858B (en) | 2013-03-01 | 2013-03-01 | A kind of aircraft wing shell |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4759971A (en) * | 1985-10-07 | 1988-07-26 | Occidental Research Corporation | Multilayered structure |
| CN1052733A (en) * | 1989-12-21 | 1991-07-03 | 施宁 | The light compound material board shell of anti-springing and anti-striking |
| CN2406216Y (en) * | 1999-09-03 | 2000-11-15 | 北京航空航天大学 | Advanced composite-material anti-bullet board |
| CN1477081A (en) * | 2003-07-11 | 2004-02-25 | 清华大学 | High-toughness Al2O3/Ti3SiC2 laminate ceramic composite material and its hot-pressing preparation method |
| US6838162B1 (en) * | 1999-09-16 | 2005-01-04 | Sgl Technik Gmbh | Fiber-bundle-reinforced composite material having a ceramic matrix, method for manufacturing a composite material and method for manufacturing elements formed of a composite material |
| CN1708396A (en) * | 2002-10-30 | 2005-12-14 | 戈尔企业控股股份有限公司 | Porous polymeric membrane toughened composites |
-
2013
- 2013-03-01 CN CN201310066804.7A patent/CN103158858B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4759971A (en) * | 1985-10-07 | 1988-07-26 | Occidental Research Corporation | Multilayered structure |
| CN1052733A (en) * | 1989-12-21 | 1991-07-03 | 施宁 | The light compound material board shell of anti-springing and anti-striking |
| CN2406216Y (en) * | 1999-09-03 | 2000-11-15 | 北京航空航天大学 | Advanced composite-material anti-bullet board |
| US6838162B1 (en) * | 1999-09-16 | 2005-01-04 | Sgl Technik Gmbh | Fiber-bundle-reinforced composite material having a ceramic matrix, method for manufacturing a composite material and method for manufacturing elements formed of a composite material |
| CN1708396A (en) * | 2002-10-30 | 2005-12-14 | 戈尔企业控股股份有限公司 | Porous polymeric membrane toughened composites |
| CN1477081A (en) * | 2003-07-11 | 2004-02-25 | 清华大学 | High-toughness Al2O3/Ti3SiC2 laminate ceramic composite material and its hot-pressing preparation method |
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| CN103158858B (en) | 2015-11-25 |
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