CA2182058A1 - Aircraft structural element, particularly for a supersonic aircraft, made of aluminium alloy with long life, good tolerance to damage and good resistance to stress corrosion - Google Patents

Aircraft structural element, particularly for a supersonic aircraft, made of aluminium alloy with long life, good tolerance to damage and good resistance to stress corrosion

Info

Publication number
CA2182058A1
CA2182058A1 CA 2182058 CA2182058A CA2182058A1 CA 2182058 A1 CA2182058 A1 CA 2182058A1 CA 2182058 CA2182058 CA 2182058 CA 2182058 A CA2182058 A CA 2182058A CA 2182058 A1 CA2182058 A1 CA 2182058A1
Authority
CA
Canada
Prior art keywords
aircraft
aluminium alloy
structural element
good
damage
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CA 2182058
Other languages
French (fr)
Other versions
CA2182058C (en
Inventor
Gilles Pons
Yann Philippe Barbaux
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Group SAS
Original Assignee
Airbus Group SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Group SAS filed Critical Airbus Group SAS
Publication of CA2182058A1 publication Critical patent/CA2182058A1/en
Application granted granted Critical
Publication of CA2182058C publication Critical patent/CA2182058C/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C22C21/16—Alloys based on aluminium with copper as the next major constituent with magnesium

Abstract

An aircraft structural element, such as a supersonic aircraft fuselage skin or wing, or a frame or reinforcement in contact with this skin is made from an aluminium alloy that contains between 2.00 and 3.00%
by weight of copper, between 1.40 and 1.90% of magnesium, between 0.20 and 0.70% of manganese, between 0 and 0.30% of iron, between 0 and 0.30% of nickel, between 0 and 0.15% of titanium, at least 0.05% of silicon and between 0 and 1.10% of silver.
Furthermore, the silicon content T(Si), the silver content T(Ag) and the magnesium content T(Mg) satisfy the following relations:

0.40 <= T(Si) + 0.4 T(Ag) <= 0.6 and (1) T(Si) + T(Ag) + 1.1 T(Mg) <= 2.6 (2) The life under stress (250 MPa) and at high temperature (150°C) is thus very much longer (E1, E3) than the life of conventional alloys (Ref.).
CA 2182058 1995-07-28 1996-07-25 Aircraft structural element, particularly for a supersonic aircraft, made of aluminium alloy with long life, good tolerance to damage and good resistance to stress corrosion Expired - Fee Related CA2182058C (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9509246A FR2737224B1 (en) 1995-07-28 1995-07-28 ELEMENT OF STRUCTURE OF AIRCRAFT, AND PARTICULARLY OF SUPERSONIC AIRCRAFT, IN ALUMINUM ALLOY HAVING A LONG SERVICE LIFE, A GOOD TOLERANCE TO DAMAGES AND A GOOD RESISTANCE TO CORROSION UNDER STRESS
FR9509246 1995-07-28

Publications (2)

Publication Number Publication Date
CA2182058A1 true CA2182058A1 (en) 1997-01-29
CA2182058C CA2182058C (en) 2008-12-09

Family

ID=9481516

Family Applications (1)

Application Number Title Priority Date Filing Date
CA 2182058 Expired - Fee Related CA2182058C (en) 1995-07-28 1996-07-25 Aircraft structural element, particularly for a supersonic aircraft, made of aluminium alloy with long life, good tolerance to damage and good resistance to stress corrosion

Country Status (7)

Country Link
EP (1) EP0756016B1 (en)
JP (1) JP3791972B2 (en)
AU (1) AU703162B2 (en)
CA (1) CA2182058C (en)
DE (1) DE69608506T2 (en)
ES (1) ES2148699T3 (en)
FR (1) FR2737224B1 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5879181B2 (en) * 2011-06-10 2016-03-08 株式会社神戸製鋼所 Aluminum alloy with excellent high temperature characteristics

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE735314C (en) * 1937-06-29 1943-05-12 Ernst Heinkel Flugzeugwerke G Use of aluminum alloys as a material for rivets
FR2087439A5 (en) * 1970-05-20 1971-12-31 British Aluminium Co Ltd Aluminium alloys suitable for eloxation - for decorative applications
US4000007A (en) * 1973-02-13 1976-12-28 Cegedur Societe De Transformation De L'aluminium Pechiney Method of making drawn and hemmed aluminum sheet metal and articles made thereby
FR2279852B1 (en) * 1974-07-23 1977-01-07 Cegedur Transf Aumin Pechiney ALUMINUM ALLOY WITH GOOD CREEP RESISTANCE AND IMPROVED CRICK PROPAGATION RESISTANCE
US4062704A (en) * 1976-07-09 1977-12-13 Swiss Aluminium Ltd. Aluminum alloys possessing improved resistance weldability
CH668269A5 (en) 1985-10-31 1988-12-15 Bbc Brown Boveri & Cie AL/CU/MG TYPE ALUMINUM ALLOY WITH HIGH STRENGTH IN THE TEMPERATURE RANGE BETWEEN 0 AND 250 C.
US5376192A (en) * 1992-08-28 1994-12-27 Reynolds Metals Company High strength, high toughness aluminum-copper-magnesium-type aluminum alloy

Also Published As

Publication number Publication date
AU703162B2 (en) 1999-03-18
EP0756016A1 (en) 1997-01-29
JPH09104941A (en) 1997-04-22
FR2737224B1 (en) 1997-10-17
FR2737224A1 (en) 1997-01-31
ES2148699T3 (en) 2000-10-16
JP3791972B2 (en) 2006-06-28
AU6075496A (en) 1997-02-06
DE69608506T2 (en) 2001-01-18
EP0756016B1 (en) 2000-05-24
DE69608506D1 (en) 2000-06-29
CA2182058C (en) 2008-12-09

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Legal Events

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