1、CEN PREN83441 93 m 3404589 0044650 35% m AECMA STANDARD NORME AECMA AECMA NORM prEN 3441 Edition P 2 April 1993 UDC : EDITE PAR LASSOCIATION EUROPEENNE DES CONSTRUCTEURS DE MATERIEL AEROSPATIAL Technopolis - 175, rue Jean-Jacques Rousseau - F-92138 Issy-les-Moulineaux Cedex - Tl. (1 ) 47.36.98.76 Su
2、persedes Issue P 1 March 1988 Descriptors : ENGLISH VERSION Aerospace series Titanium TI-P99001 Annealed Sheet and strip, hot rolled aI6mm 290 MPa I Rm I420 MPa Srie arospatiale Titane TI-P99001 Recuit Tles et bandes, lamines chaud aI6mm 290 MPa I R, I 420 MPa Luft- und Raumfahrt Titan TI-P9900 1 Ge
3、glht Bleche und Bnder, warmgewalzt al6mm 290 MPa I R, I420 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 INPSI 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 ICCY-LEC-MOULINEAUX CEDEX I C5 Chairman I Edition approved for publication I COmmentS should be sent within six months after the date of oublication to 1993-04-26 AECMA Technopolis - 175, rue Jean-Jacques Roussea
7、u 921 38 Issy-les-Moulineaux Cedex - FRANCE M. ODORICO 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 PRENb3441i 93 3404589 0044b5L 298
8、 prEN 3441 Page 3 0 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, 290 MPa I R, I420 MPa in titanium TI-P99001 for aerospace applications. 2 References
9、EN 2338 Sheets, titanium and titanium alloys - Hot rolled - Thickness 0,8 mm I a I 5 mm - O Dimensions - Aerospace series EN 2500-4 Aerospace series - Instructions for the drafting and use of metallic material standards - Part 4 - Specific requirements for titanium and titanium alloys *) EN 2600 Aer
10、ospace series - Designstion of metallic semi-finished products - Rules 2, EN 3544-1 Aerospace series - Titanium and titanium alloys - Wrought products - Technical specification - Part 1 - General requirements 3, EN 3544-2 Aerospace series - Titanium and titanium alloys - Wrought products - Technical
11、 specification - Part 2 - Plate, sheet and strip 3, I) 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 Copyright
12、 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 PREN+3441 93 = 3404589 0044652 324 = Chemical Element composition min. % ma. 2 prEN 3441 Page 4 o2 N2 H2 Fe
13、C Othen Ti Each Totai 0,20 0,05 0,0125 0,20 0,08 0,lO 0,601) Base 3 4 Method of melting See EN 3544-1 Form Sheet and strip I Method of production Limit dimensions (mm) I I Hot rolled as6 5.1 Technical specification 5.2 Dimensional standards EN 3544-2 EN 2338 5 6.1 Delivery condition and heat treatme
14、nt 6.2 Delivery condition code Use condition and heat treatment Annealed 600 “C 5 8 5 840 “C I t 2 1 min I AC or inert atmosphere U Delivery condition 8 Sample Test piece 9 10 11 12 13 14 15 - - - - l6 I Heat treatment Use condition Dimensions concerned mm a52 2eas5 5as6 each face Direction of test
15、piece Thickness of cladding on % See EN 3544-2 T I Temperature e OC Ambient 1 Proof stress I Rp0,2 I MPa . 2 200 Elongation Reduction of Strength R, MPa 290 5 R, 5 420 I I I A% 8 A5rnm224 Z % 18 19 area I I I I Shear strength R, MPa Bending k 1,O;a =105 I 1,5 ; a = 105“ I 20 Impact strength 21 Tempe
16、rature e C - 22 Time h 23 Stress o, MPa - - 24 C Elongation a % - 25 Rupturestress OR MPa 26 Elongation at A% 27 Notes (see line 98) 1) - rupture Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or network
17、ing permitted without license from IHS-,-,-CEN PREN*3441 93 3404589 0044653 Ob0 6 prEN 3441 Page 5 See EN 3544-2 5 mm a26 mm ixternal defects - ;utface contamination I) Determination not required for routine acceptance Designation Notes Typical use -I See EN 3544-2 -I See EN 2600 -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-,-,-
