1、CEN PRENU3443 93 = 3404589 O044658 642 AECMA STANDARD NORME AECMA AECMA NORM prEN 3443 Edition P 2 April 1993 UDC : EDITE PAR LASSOCIATION EUROPEENNE DES CONSTRUCTEURS DE MATERIEL AtROSPATIAL Technopolis - 175, rue Jean-Jacques Rousseau - F-92138 Issy-les-Moulineaux Cedex - Tl. (1) 47.36.98.76 Super
2、sedes Issue P 1 March 1988 Descriptors : ENGLISH VERSION Aerospace series Titanium TI-P99003 Annealed Sheet and strip, hot rolled a16mm 570 MPa I Rm I 730 MPa Srie arospatiale Titane TI-P99003 Recuit Tles et bandes, lamines chaud a16mm 570 MPa I R, I 730 MPa Luft- und Raumfahrt Titan TI-P99003 Geglh
3、t Bleche und Bnder, warmgewalzt a26mm 570 MPa I R, I 730 MPa This “Aerospace Series“ Prestandard has been drawn up under the responsibility of AECMA (Association Europenne des Constructeurs de Matriel Arospatial). It is published on green paper for the needs of AECMA-Members. It has been technically
4、 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 functionally, without re-identificati
5、on of the standard. After examination and signature of the AECMA Standard Checking Centre (NPS) and formal agreement of the Official Services of the Member countries it will be submitted as a draft European Standard to CEN (European Committee for Standardization) for formal vote. Nota - Extra copies
6、 can be supplied by B.N.A.E. - Technopolis 54 - 199, rue Jean-Jacques Rousseau - 921 38 ISSY-LES-MOULINEAUX CEDEX I Comments should be sent within six months after the date of publication to I Edition approved for publication I AECMA 1993-04-26 1 TechnoDolis - 175. rue Jean-Jacaues Rousseau C5 Chair
7、man M. ODORICO I I 921 38 Issy-les-Moulineaux Cedex - FRANCE aecma 1993 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-,-,-CEN PRENm3443 93 H 3404589 0044
8、659 589 9 prEN 3443 Page 3 O Introduction For the use of this standard, see EN 2500-4. 1 Scope and field of application This standard specifies the requirements relating to sheet and strip, hot rolled, a I 6 mm, annealed, 570 MPa I R, I730 MPa in titanium TLP99003 for aerospace applications. 2 Refer
9、ences EN 2338 EN 2500-4 EN 2600 EN 3544-1 EN 3544-2 Sheets, titanium and titanium alloys - Hot rolled - Thickness 0,8 mm I a I 5 mm - Dimensions - Aerospace series Aerospace series - Instructions for the drafting and use of metallic material standards - Part 4 - Specific requirements for titanium an
10、d titanium alloys z, Aerospace series - Designation of metallic semi-finished products - Rules 2, Aerospace series - Titanium and titanium alloys - Wrought products - Technical specification - Part 1 - General requirements 3, Aerospace series - Titanium and titanium alloys - Wrought products - Techn
11、ical specification - Part 2 - Plate, sheet and strip 3, 1) Published as AECMA standard at the date of publication of this standard 2) Published as AECMA pre-standard at the date of publication of this standard 3) In preparation at the date of publication of this standard Previous page is blank Copyr
12、ight Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CEN PRENt3443 93 m 3404589 0044660 2TO m 2 prEN 3443 Page 4 Fe C Others Ti o2 N2 H2 Chemical Element Each To
13、tal composition min. Base % max. 0,40 0,05 0,0125 0,35 0,08 0,101) 0,60 1 I Material designation I Tltanium TI - P99003 4 FoM Sheet and strip I See EN 3544-1 3 I Method of meltina I 5 EN 3544-2 5.1 Technical specification 5.2 Dimensional standards EN 2338 Method of production Limit dimensions (mm) 6
14、 6.1 Delivery condition and heat treatment 6.2 Delivery condition de 7 Use condition and heat treatment Hot rolled a16 Annealed 600 “C 1 0 5 840 “C I t 2 1 min I AC or inert atmosphere U Delivery condition 8 Sample Test piece Heat treatment 9 Dimensions concerned mm 10 Thickness of cladding on % Use
15、 condition a12 2a15 5a16 II Dii :h face I Pction of test piece Temperature 0 “C Proof stress Rp0,2 MPa Strength R, MPa Elongation A% Reduction of 2% See EN 3544-2 Ambient 2 460 570 1 R, 5 730 A 50 mm 216 17 18 19 27 NI I area I I Hardness Shear strength R, MPa Bending k 2,5 ; a = 105“ 3 ; a = 105“ ,
16、act strength Temperature 0 “C Time h stress ua MPa Elongation a % Rupturestress UR MPa Elongation at A% rupture :es (see line 98) 1) Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted
17、 without license from IHS-,-,-CEN PRENr3443 93 m 3404589 00Yqbbl 137 m prEN 3443 Page 5 6 External defects Surface contamination 5 mrn a 5 6 mrn Iesignation Votes - - rypical use See EN 2600 1) Determination not required for routine acceptance I See EN 3544-2 -I See EN 3544-2 -I 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-,-,-
