ASD-STAN PREN 2511-2003 Aerospace Series Aluminium Alloy AL-P7075-T7351 Plate 6 mm Less Than a Less Than or Equal to 100 mm (Edition P 2)《航空航天系列 6mm≤a≤100mm的AL-P7075-T7351铝合金厚板材 第P.pdf

1、AECMA STANDARD NORME AECMA AECMA NORM Edition approved for publication 15 May 2003 prEN 2511 Edition P 2 May 2003 Comments should be sent within six months after the date of publication to AECMA-STAN ICs: Descriptors: ENGLISH VERSION Supersedes edition P 1 October 1998 Aerospace series Al um i ni um

2、 alloy AL-P7075- T7351 Plate 6 mm a 100 mm Srie arospatiale Alliage daluminium AL-P7075- T7351 Tles paisses 6 mm ai 100 mm Luft- und Raumfahrt Aluminiumlegierung AL-P7075- T7351 Platten 6 mm ai 100 mm This “Aerospace Series“ Prestandard has been drawn up under the responsibility of AECMA-STAN (The E

3、uropean Association of Aerospace Industries - Standardization). It is published on green paper for the needs of the European Aerospace Industry. It has been technically approved by the experts of the concerned Domain following member comments. Subsequent to the publication of this Prestandard, the t

4、echnical content shall not be changed to an extent that interchangeability is affected, physically or functionally, without re-identification of the standard. After examination and review by users and formal agreement of AECMA-STAN it will be submitted as a draft European Standard to CEN (European C

5、ommittee for Standardization) for formal vote. Metallic Material Domain I I Copyright 2003 O by AECMA-STA1 Page 2 prEN 251 1 : 2003 Foreword This standard was reviewed by the Domain Technical Coordinator of AECMA-STANS Metallic Material Domain. After inquiries and votes carried out in accordance wit

6、h the rules of AECMA-STAN defined in AECMA- STANS General Process Manual, this standard has received approval for Publication. Page 3 prEN 251 1: 2003 O Introduction This standard is part of the series of EN metallic material standards for aerospace applications. The general organization of this ser

7、ies is described in EN 4258. This standard has been prepared in accordance with EN 4500-2. 1 Scope This standard specifies the requirements relating to: Aluminium alloy AL-P7075- T7351 Plate 6 mm a 100 mm for aerospace application. 2 Normative references This European Standard incorporates by dated

8、or undated refere ce provisia s from other publicatic S. These normative references are cited at the appropriate places in the text and the publications are listed hereafter. For dated references, subsequent amendments to or revisions of any of these publications apply to this European Standard only

9、 when incorporated in it by amendment or revision. For undated references the latest edition of the publication referred to applies. EN 4258, Aerospace series - Metallic materials - General organization of standardization - Links between types of EN standards and their use EN 4400-1, Aerospace serie

10、s - Aluminium and aluminium alloy wrought products - Technical specification - Part I: Plate 1) EN 4500-2, Aerospace series - Metallic materials - Rules for drafting and presentation of material standards - Part 2: Specific rules for aluminium, aluminium alloys and magnesium alloys 1) 1) Published a

11、s AECMA Prestandard at the date of publication of this standard Page 4 prEN 251 1: 2003 5 4.2 I Method of production I Rolled Technical specification EN 4400-1 4.3 I Limit dimension(s) I mm I 6a100 6.1 Delivery condition W51 T7351 Heat treatment 460 OC e 500 OC I WQ e 40 OC 460 OC e 500 OC I WQ e 40

12、 OC + 1,5 % controlled stretched 3 % + 1,5 % controlled stretched 3 % + 100 “C 6% 135 “C I3 h t 24 h a + 155 “C 6% 175 “C I8 h t 30 h a 6.2 7 Delivery condition code W U Use condition T7351 T7351 Heat treatment Delivery condition + 100 “C 6% 135 “C I3 h t 24 h a + 155 “C 6% 175 “C I8 h t 30 h a Deli

13、very condition 8.1 8.2 Test sample(s) See EN 4400-1. Test piece(s) See EN 4400-1. I12 I ITemperature I 0 I “C I Ambient I Ambient I Ambient I 8.3 9 11 Il I Heat treatment Use condition. 123 a 25 Dimensions concerned mm 6 a 12,5 each face Direction of test piece L LT L LT L LT I ST 25 a 40 Thickness

14、of cladding on % - - - Proof stress Elongation Il I I I I I I I I I I Rp0,2 MPa 2 390 2 390 2 390 2 390 2390 2390 2360 R, MPa 2 480 2 480 2 480 2 480 2470 2470 2440 A % Ammm27 Ammm 2 7 27 27 26 26 233 I I 16 I I Reductionofarea I Z I % I - 9 11 Dimensions concerned mm 40 a 60 60 a 80 80 a 100 each f

15、ace Direction of test piece L I LT I ST LI LT I ST LI LT I ST Thickness of cladding on % - - - I12 I ITemperature I 0 I “C I Ambient I Ambient I Ambient I 14 15 16 17 - - 113 I I Proofstress I Rp,2 I MPal 2370 I 2370 I 2340 I 2350 I 2350 I 2330 I 2340 I 2340 I 2320 I T Strength R, MPa 2460 2460 2430

16、 2440 2440 2420 2430 2430 2410 Elongation A % 26 26 233 26 26 233 26 26 233 Reduction ofarea Z % - Hardness - Il I 19 20 21 Bending k- - Impact strength - I Temperature I eloc - I I 18 I Shear strength I R, I MPa I - :;:;stress Elongation at OR MPa - A % - Il I I I I I22 I ITime Ihl Il I I I I a, b

17、I 27 I Notes see line 98) I Page 5 prEN 251 1 : 2003 - ilectrical conductivity See EN 4400-1. Stress corrosion 7 ixternal defects y 2 23,O MSlm Acceptable Acceptable if Rw:2 LT Rp0,2 min. LT + 85 MPa (see line 13) or if stress corrosion test results (see line 39) are acceptable. 22,O MSlm y 23,O MSl

18、m nternal defects - 3atch uniformity y 22,O MSlm Not acceptable See EN 4400-1. Marking inspection 7 - Iimensional inspection Votes t220d See EN 4400-1. rypical use - a Artificial ageing may be carried out using the following alternative single stage method: heating to a temperature of 155 “C I 81 17

19、5 “C at a rate not exceeding 20 “C I h and soaking at this temperature for 8 h I t I30 h. Or hD 2 4 if required by the purchaser. 61 O = 75 % Rp0,2 min. LT -I See EN 4400-1. -I See EN 4400-1. See EN 4400-1. -I -I See EN 4400-1. -I 100 See EN 4400-1. Qualification programme to be agreed between manufacturer and purchaser. Page 6 prEN 251 1: 2003 - Product qualification