ImageVerifierCode 换一换
格式:PDF , 页数:6 ,大小:157.79KB ,
资源ID:420171      下载积分:5000 积分
快捷下载
登录下载
邮箱/手机:
温馨提示:
如需开发票,请勿充值!快捷下载时,用户名和密码都是您填写的邮箱或者手机号,方便查询和重复下载(系统自动生成)。
如填写123,账号就是123,密码也是123。
特别说明:
请自助下载,系统不会自动发送文件的哦; 如果您已付费,想二次下载,请登录后访问:我的下载记录
支付方式: 支付宝扫码支付 微信扫码支付   
注意:如需开发票,请勿充值!
验证码:   换一换

加入VIP,免费下载
 

温馨提示:由于个人手机设置不同,如果发现不能下载,请复制以下地址【http://www.mydoc123.com/d-420171.html】到电脑端继续下载(重复下载不扣费)。

已注册用户请登录:
账号:
密码:
验证码:   换一换
  忘记密码?
三方登录: 微信登录  

下载须知

1: 本站所有资源如无特殊说明,都需要本地电脑安装OFFICE2007和PDF阅读器。
2: 试题试卷类文档,如果标题没有明确说明有答案则都视为没有答案,请知晓。
3: 文件的所有权益归上传用户所有。
4. 未经权益所有人同意不得将文件中的内容挪作商业或盈利用途。
5. 本站仅提供交流平台,并不能对任何下载内容负责。
6. 下载文件中如有侵权或不适当内容,请与我们联系,我们立即纠正。
7. 本站不保证下载资源的准确性、安全性和完整性, 同时也不承担用户因使用这些下载资源对自己和他人造成任何形式的伤害或损失。

版权提示 | 免责声明

本文(AECMA PREN 3342-2003 Aerospace Series Aluminium Alloy AL-P6061-T4 or T42 Drawn or Extruded Bar and Section a or D Less Than or Equal to 150 mm Edition P 3《航空航天系列.铝合金AL-P6061-T4 或 T.pdf)为本站会员(李朗)主动上传,麦多课文库仅提供信息存储空间,仅对用户上传内容的表现方式做保护处理,对上载内容本身不做任何修改或编辑。 若此文所含内容侵犯了您的版权或隐私,请立即通知麦多课文库(发送邮件至master@mydoc123.com或直接QQ联系客服),我们立即给予删除!

AECMA PREN 3342-2003 Aerospace Series Aluminium Alloy AL-P6061-T4 or T42 Drawn or Extruded Bar and Section a or D Less Than or Equal to 150 mm Edition P 3《航空航天系列.铝合金AL-P6061-T4 或 T.pdf

1、AECMA STANDARD NORME AECMA AECMA NORM prEN 3342 Edition P 3 November 2003 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES - STANDARDIZATION b Gulledelle 94 - 8-1200 Brussels -Tel. 32 2 775 81 10 - Fax. 32 2 775 811 1 - www.aecma-stan.org ICs: Descriptors: ENGLISH VERSION Aerospace se r

2、ies Aluminium alloy AL-P6061- T4 or T42 Drawn or extruded bar and section a or D I 150 mm Supersedes edition P 2 Decem ber 1998 Srie arospatiale Alliage daluminium AL-P6061- T4 ou T42 Barres et profils tirs ou fils aou DI 150 mm Luft- und Raumfahrt Aluminiumlegierung AL-P6061- T4 oder T42 Gezogene o

3、der Stranggeprete Stangen und Profile a oder D I 150 mm This “Aerospace Series“ Prestandard has been drawn up under the responsibility of AECMA-STAN (The European Association of Aerospace Industries - Standardization). It is published for the needs of the European Aerospace Industry. It has been tec

4、hnically approved by the experts of the concerned Domain following member comments. Subsequent to the publication of this Prestandard, the technical content shall not be changed to an extent that interchangeability is afiected, physically or functionally, without re-identification of the standard. A

5、fter examination and review by users and formal agreement of AECMA-STAN, it will be submitted as a draft European Standard (prEN) to CEN (European Committee for Standardization) for formal vote and transformation to full European Standard (EN). The CEN national members have then to implement the EN

6、at national level by giving the EN the status of a national standard and by withdrawing any national standards conflicting with the EN. Edition approved for publication 15 November 2003 Comments should be sent within six months after the date of publication to AECMA-STAN Metallic Material Domain Cop

7、yright 2003 O by AECMA-STA! 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-,-,-Page 2 prEN 3342:2003 Foreword This standard was reviewed by the Domain Tec

8、hnical Coordinator of AECMA-STANS Metallic Material Domain. After inquiries and votes carried out in accordance with the rules of AECMA-STAN defined in AECMA- STANS General Process Manual, this standard has received approval for Publication. Copyright Association Europeene des Constructeurs de Mater

9、iel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 3 prEN 3342:2003 O Introduction This standard is part of the series of EN metallic material standards for aerospace applications. The general organization o

10、f 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-P6061- T4 or T42 Drawn or extruded bar and section a or D 5 150 mm for aerospace application. The order shall state wh

11、ether the extruded or drawn condition is required. 2 Normative references 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 da

12、ted references, subsequent amendments to or revisions of any of these 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 -

13、 General organization of standardization - Links between types of EN standards and their use EN 4400-3, Aerospace series - Aluminium and aluminium alloy wrought products - Technical specification - Part 3: Bar and section EN 4500-2 Aerospace series - Metallic materials - Rules for drafting and prese

14、ntation of material standards - Part 2: Specific rules for aluminium, aluminium alloys and magnesium alloys 1) Published as AECMA Prestandard at the date of publication of this standard Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA

15、Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 4 prEN 3342:2003 Delivery condition Heat treatment Delivery condition code Use condition Heat treatment Method of melting I F O T4 520 “C 2 82 540 “C I WQ 82 40 “C + 8= ambient It t 5d - - F A U T42 T4 Delivery c

16、ondition + 520 “C 2 82 540 “CI WQ 82 40 “C + 8= ambient It t 5d Delivery condition Form Bar and section Method of production Limit dimension(s) mm a or D 2 150 Drawn or Extruded Technical specification EN 4400-3 Heat treatment Dimensions concerned mm - 3.1 - 3.2 7 - - - 3.1 3.2 3.3 9 10 11 12 13 14

17、15 16 17 18 19 20 21 22 23 24 25 26 27 - - - - - - - - - - - - - - - - - - - - - - Use condition aorD2150 Thickness of cladding on each face Characteristics % - Test sample(s) I See EN 4400-3. Proof stress T Strength Test piece(s) I See EN 4400-3. RPO,Z MPa t 110 R, MPa t 210 Reduction ofarea Z % -

18、L I Direction of test piece Hardness Shear strength & MPa Bending k- ITemperature I 8 I “C I Ambient - - - “ Elongation Rupture stress I Elongation I A I % I A or &omm t 14 a% - OR MPa - Elongation at rupture Impact strength I A % - I Time Ihl Notes (see line 98) - Copyright Association Europeene de

19、s Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ixternal defects - nternal defects 3atch uniformity See EN 4400-3. ixtrusion back-end defect - - Marking inspection Iimensional inspectio

20、n See EN 4400-3. See EN 4400-3. Votes 7 - rypical use 60 (Typical value) Hardness HB 6 2 16 per product A 2 24 per batch See EN 4400-3. - - See EN 4400-3. See EN 4400-3. 51 T4 -I -I Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot

21、for ResaleNo reproduction or networking permitted without license from IHS-,-,-100 Page 6 prEN 3342:2003 - Product qualification 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-,-,-

copyright@ 2008-2019 麦多课文库(www.mydoc123.com)网站版权所有
备案/许可证编号:苏ICP备17064731号-1