ASD-STAN PREN 4457-1999 Aerospace Series Aluminium Alloy AL-P7475-T7351 Plate 6 mm Less Than a Less than or Equal to 100 mm (Edition P 1)《航空航天系列 6mm≤a≤100mm的AL-P7475-T7351铝合金厚板材 第P.pdf

1、STD*AECMA PREN 4Y57-ENGL 1999 .I lOL231L 0036039 53L D Edition approved for publication 199942-26 AECMA STANDARD NORME AECMA AECMA NORM Cb Chairman Mr Evetts Comments should be sent within six months after the date of publication to AECMA Gulledelle 94 BI200 BRUXELLES prEN 4457 Edition P 1 February

2、1999 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES (AECMA) Gulledelle 94 - 8-1200 BRUXELLES - Tel. (+32) 2 775 81 10 - Fax. (+32) 2 775 81 1 I ICs: ENGLISH VERSION Aerospace series Aluminium alloy AL-P7475- T7351 Plate 6 mm a I 100 mm Srie arospatiale Alliage daluminium AL-P7475- Ti3

3、51 Tles paisses 6 mm a I 100 mm Luft- und Raumfahrt Aluminiumlegierung AL-P7475- i7351 Platten 6 mm as 100 mm This “Aerospace Series” Prestandard has been drawn up under the responsibility of AECMA (The European Association of Aerospace Industries). It is published on green paper for the needs of AE

4、CMA-Members. It has been technically approved by the experts of the concerned Technical Committee following comment by the Member countries. Subsequent to the publication of this Prestandard, the technical content shall not be changed to an extent that interchangeability is affected, physically or f

5、unctionally, without re-identification of the standard. After examination and signature of the AECMA Standard Checking Centre (NPS) and formal agreement of the Oficial Setvices of the Member countries it will be submitted as a draft European Standard to CEN (European Committee for Standardization) f

6、or formal vote. COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling ServicesSTD-AECMA PREN 4457-ENGL 1999 LOL231L 00Lb040 253 Page 3 prEN 4457: 1999 O Introduction This standard is part of the series of EN metallic material standards for aerospace

7、applications. The general organization of this series 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-P7475- T7351 Plate 6 mm ar 100 mm for aerospace applications. 2 Normative refe

8、rences This European Standard incorporates by dated or undated reference provisions from other publications. 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 the

9、se publications apply to this European Standard only 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

10、 standards and their use EN 4400-1 Aerospace series - Aluminium and aluminium alloy wrought products - Technical Specification - Part 1: Plate 1) EN 4500-2 Aerospace series - Metallic materials - Rules for drafting and presentation of material standards - Part 2: Specific rules for aluminium, alumin

11、ium alloys and magnesium alloys 1) 1) Published as AECMA Prestandard at the date of publication of this standard Previous page is blank COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling ServicesSTD.AECMA PREN 4457-ENGL 1999 1012311 001bO41 19T I

12、Page 4 prEN 4457: 1999 1 I I Material designation I Aluminium alloy AL-P7475- Element min. max. 2 AI Others Each Total si Fe Cu Mn Mg Cr Zn Ti - - 12 - 1,9 0,18 5,2 - - - Base 0,lO 0,12 1,9 0,06 2,6 0,25 6.2 0,06 0,05 0,151 Chemical composition % 3 4.1 Method of melting - Form Plate 4.2 4.3 5 Method

13、 of production Rolled Limit dimension(s) mm 6as100 Technical sDecification EN 4400-1 16.1 I Delivery condition I T7351 I 6.2 7 Il I Delivery condition code U Use condition T7351 Heat treatment 8.3 9 - 460 OC s es 500 OC I WQ es 40 oc + 1,5 % I controlled stretched I 3 % + 100 “C I e 135 “C I 3 h I t

14、 I 24 h 1 + 155 C I 6% 175 “C I 8 h I t I 30 h Heat treatment Use condition Dimensions concerned I mm 6 a II 12.5 I 12,5a125 I 25 a 140 11 12 II I I Thickness of cladding % - - - on each face Direction of test piece L LT L LT L LT ST I Temperature I eloc Ambient Ambient Ambient Proof stress Elongati

15、on Reductionofarea 18.2 I Test piece(s) I See EN 4400-1 I Rw, MPa 2 390 2 390 2390 2390 2390 2 390 2 365 R, MPa 2 480 2480 2480 2480 2470 2 470 2 440 A % A50mm28 A50mm 2 8 28 28 28 28 2 33 2) Z % - 10 Thickness of cladding % - - - on each face I I I1 12 Direction of test piece LI LT I ST LI LT I ST

16、LI LT I ST I Temperature I eloc Ambient Ambient Ambient (continued) I Proofstress Elongation Reductionofarea 60 a I 80 r 80as100 I 9 I Dimensions concerned I mm I 40 a 2 60 I Rp0,2 MPa 2370 2370 2340 2350 2350 2330 2340 2340 2320 Rm MPa 2460 2460 2430 2440 2440 2420 2430 2430 2410 A % 28 28 23,!j2)

17、28 28 23,52) 27 27 2 3,521 2 % - 17 18 Hardness - Shear strength I R, IMPa - I I I 19 20 Bending k- - Impact strength - 21 Temperature 1 e OC - 23 Stress I MPa - - 22 Time h - - 24 C M Elongation a% - Rupture stress oR MPa - COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLice

18、nsed by Information Handling ServicesSTDoAECMA PREN 4457-ENGL 1999 30123L1 001b042 02b I See EN 4400-1 Page 5 prEN 4457: 1999 y 2 23,O MSlm I Acceptable I ilectrical conductivity I 22,O MS/m 5 y 23,O MS/m Acceptable if Rp0,2LT 5 Rp0,2 min. LT + 85 MPa or if stress I corrosion test is acceptable. y 2

19、2,O MS/m Not acceptable See EN 4400-1 T = 75 % Rp0,2min. LT t 2 20d See EN 4400-1 The “capability clause“ applies ;tress corrosion 1) Artificial ageing may be carried out using the following alternative single stage method heating to a temperature of 155 “C 5 8s 175 “C at a rate not exceeding 20 Clh

20、 anc soaking at this temperature for 8 h t s 30 h. 2) Or AD 2 4 if required by the purchaser. :racture toughness 25 a s 50 50as 75 75a 100 KIC) 2 41 2 36 - t 40 2 35 2 27 L 39 2 34 2 27 External defects qotchlyield ratio 3elR0.2 nternal defects 3atch uniformity Marking inspection Dimensional inspect

21、ion Notes Typical use -I Dimensions L-T T-L s-L (mm) I MPah 1 MPah I MPah See EN 4400-1 See EN 4400-1 See EN 4400-1 See EN 4400-1 -I See EN 4400-1 -I COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling ServicesSTD.AECMA PREN 4457-ENGL 1999 1012311 O036043 Tb2 Page 6 prEN 4457: 1999 Product qualification See EN 4400-1 Qualification programme to be agreed between manufacturer and purchaser. COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling Services