1、 _I AECMA PREN2128 85 10123LL 0002208 I W A.E.C.M.A. STANDARD prEN2128 NORME A.E.C.M.A. Edition 2 A,E.C.M.A. NORM May 1985 Supersedes edition i October 1980 Approved by COMIT DE NORMALISATION of A.E.C.M.A. 1984-11-23 ENGLISH VERSION The equivalent versions in French and German languages can be suppl
2、ied by B.N.A.E., 8, rue Moreau-Vauthier 92100 BOULOGNE-BILLANCOURT - FRANCE. Aerospace series Aluminium alloy 7075-T7351 drawn bar a 75 mm Srie arospatiale Alliage daluminium 7075-T7351 barres tires a 75 mm Luft- und Raumfahrt Aluminium-legierung 7075-T7351 gezogene Stangen a G 75 mm This industrial
3、 standard for the aerospace sector has been drawn up under the responsibility of AECMA (Associa tion Europenne des Constructeurs de Matriel Arospatial), It is published on yellow paper in three equivalent versions (English, French, German). It will be submitted to CEN (European Committee for Standar
4、dization) 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 PREN2L28 85 /0123LL 0002209 3 prEN21-8 Page 3 Previous pa
5、ge is blank Aluminium alloy 7075-T7351 drawn bar a 75 mm 0.40 0.50 2.0 0.30 2.9 - Cr O,? 8 0.28 - - - Element Others Each I Total Ti TifZr. Ai C hem Ica1 Composition % min. -!-I- Rem. 0,20 0.25 0,05 1 0,15 max. 1 lethod of melting Ear Drawn a 6 75 mm orm 1 et hod of production .mit dimensions 1-1 Je
6、chnical specifycations .2 Dimeniional standards EN207C-1 and EN207C-3 ER2044, EN2045 and EN2046 I I Solution treated 465 5 50C / Water quench + 1,5 E controlled stretched S 3% T651 I T7351. Solution treated 465 ,+ 50C/Water quench - 400c + artificially aged 110 2 5C / 6 t 1,5 3 controlled stretched
7、s 3% . t artificially aged 120 2 5OC/20 6 t S 30 h + artificially aged 177 2 5OC / 5 400c 4 t $24 h t 12 h I I T7351 I T7351 :ondition ind ieat treatment )ellvery :ondition ind ieat treatment J se I Delivery condition I Delivery condition + artificially aged 177 2 5OC / 5 6 td12 h , rest piece i eat
8、 treatm ent jampling . T7351 1 75 Iimensions :oncerned % rhickneis of :ladding on each face 3irection of sample L Temperature e g: Room temperature - . Proof Stress 9 385 b 470 Strength Rm Elongation A % t 11 or Aso mm r, 10 % - - MPa *I Reduction of area 135 (for information) - Hardness Shear Stren
9、gth Bending k Impact K J e oc Temperature Tlme Strcss W f u Elongation h MPa 1 % - - Rupture Stress Elongation at rupture *i 1 MPa = 1 N/rnm* I), see 1 - Notes Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduct
10、ion or networking permitted without license from IHS-,-,- - l_l_ - AECMA PREN2LZB 85 U LOL23LL 0002210 T U prEN2128 Page 4 ilectrical :onductivity 1 Itress :orrosion iC/a Notei Typical use EM204-1 21 r, 23 1 Acceptable Acceptable if : 1) Rp0,2 6 Rp0,2 3, + 85 MPa and 2) if- Y shows a decrease of at
11、least 3,5 MS/m compared tri the original value when measured within 15 minutes of re-solution treatment and quenching. 22s y 23 I EFi2004-4 L, . ST direction 75% Rp0,2 3) - 1) Ag mm for thicknesses a s 10 mrn 2) In preparation 3) Minimum values indicated in line 13. 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-,-,-
