1、AECMA PREN2704 85 10123LL 0004003 4 Approved by COMIT DE NORMALISATION of A.E.C.M.A. 1984-1 - 1-23 I The equivalent versions in French and German languages can be supplied by B.N.A.E., 8, rue Moreau-Vauthier 92100 BOULOGNE-BILLANCOURT - FRANCE. A.E.C.M.A. STANDARD NORME A.E.C.M.A. prEN2704 Edition I
2、 A.E.C.M.A. NORM May 1985 E W. I CO J -5 3 a W 2 2 W u 2 ENGLISH VERSION Aerospace series Aluminium alloy 2024-7351 I drawn bar a 75 mm Srie arospatiale Alliage daluminium 2024-T351 I barres tires a 75 mm Luft- und Raumfahrt Aluminium-legierung 2024-T35 1 1 gezogene Stangen a 75 mm This industrial s
3、tandard for the aerospace sector has been drawn up under the responsibility of AECMA (Association Europenne des Constructeurs de Matrier Arospatial). It is published on yellow paper in three equivalent versions (English, French, German). It will be submitted to CEN- (European Committee for Standardi
4、zation) as a draft European Standard. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,- AECMA PREN270Y 85 9 LOL23LL O004004 b Previous page is blank - p
5、rEN2704 Page 3 Aluminium alloy 2024-T3511 drawn bar a 75 mm Si I Fe I Cu I Mn 1 Mg I Cr 1 Ni 1 Zn 1 Ti Ti+Zri Al each - - - - - - - 3,8 0,30 1,2 - Rem. 0,9 1,8 I 0,lO I - 0.25 0,15 0,20 0,05 0,15 Element C hem Ica1 Com position max. 1 2 Method of melting Bar . Drawn a 4 75 mm Form Method of producti
6、on Limit dimensions 5.1 Technical sp.ecificationc EN2070-1 and EN2070-3 5.2 Dimensional standards EN2044 to EN2046 T3511 Condition and Solution treated 495 2 5OC / Water quench C , 40C + lI5 $ controlled stretched 6 3% + minor straightening permitted + naturally aged t 3 5 d Heat treatment Delivery
7、Condition T3511 Delivery condition and Heat treatment U se Test piece Heat treatm ent Sampling Dimensions concerned Thickness of cladding on each face T3511 z 75 L Room temperature tion of sample Temperature b 315 Proof Stress 3 440 Strength , MPa - Elongation A % Reduction 76 of area - _- b 13 1) -
8、 i20 (for information) Hardness I 4 - Shear Strength R, MPa * Bending k Impact KJ - - - a a w w u - - Temperature 6 % Time th - Stress Elongation Rupture Stress Elongation at rupture - A ) 1 MPa = 1 N/mm2 L) , see line 98 t. Notes Copyright Association Europeene des Constructeurs de Materiel Aerospa
9、tial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-prEN2704 Page 4 -AECMA PREN2704 45 - LOL23LL OOOLi005 8 m 1 Electrical Votes 2 EN2004-1 2, 175 Y$ 20 : acceptable 1) A50 mm 2) In preparation. 12% for thicknesses a & 10 mm. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
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