AECMA PREN 2735-1986 Aerospace Series Magnesium Alloy Mg-C91-T5 Sand Castings Issue P 1《航空和航天系列镁合金 Mg-C91-T5软铸造》.pdf

1、A. E.C. M .A. STAN DARD NOR ME A.E.C. M.A. A.E.C.M.A. NORM Edition approved for publication prEN 2735 Issue P 1 April 1986 C5 Chairman Comments should be sent within six months after the date of publication decision EDIT PAR LASSOCIATION EUROPEENNE DES CONSTRUCTEURS DE MATRIEL AROSPATIAL 88, bouleva

2、rd Malesherbes, 75008 PARIS -TL. 45-63-82-85 ENGLISH VERSION Aerospace series Magnesium alloy Mg-C91 -T5 sand castings Srie arospatiale Luft- und Raumfahrt pices de fonderie Gustcke moulage au sable Sandgu Alliage de magnsium Mg-C91-15 Magnesiumlegierung Mg491 -T5 This standard is initially publishe

3、d on green paper for the needs of AECMA-Members (Association Europenne des Constructeurs de Matriel Arospatial). It has been technically approved by the experts of the concerned AECMA Commission following comment by the manufacturers of the Member countries. After examination and signature of the AE

4、CMA Standard Checking Centre (NPS) and formal agreement of the Official Services of the Member countries it will be published in its final version on yellow paper as an AECMA Standard. 22 April 1986 A.E.C.M.A. W,73&-M-aTeBherbes Mr HILAIRE 75008 PARIS - FRANCE Copyright Association Europeene des Con

5、structeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted without license from IHS-,-,- prEN2735 Page 3 AECMA PREN2735 86 m LOL23LL 0004068 T m 1 Others Cham Ica1 , iment Zn Mn . Si Fe Ni Cu Zr 1.R each 1 total Mg Method of melt

6、lng - Form Sand cast Method of productlon Llmlt dlmenrlons 5.1 Technical specifications 6,2 Qlmentlonal standards - 6.1 Condltlon T5 EN2076-1 and EN2076-3 and Heat treatment Delkary 170 d !3 5 250% / 6 ,C t L. 24 h/ Air cool 6.2 Code letten I- U T5 I Condltlon and Heat treatment uw Delivery conditio

7、n Test plece Heat treatment Smpllng 4 T5 3, T5 4, T5 5, I I Wall thickness of 6 20 mm 6) I Dlmenslonr concerned % Thlcknerr of - cladding on each face Dlrectlon of sample - Temperature 6 9: Room temperature - u) Stress Rpq? MPa) 3 95 3 85 2, 95 Proof - -I - Strength R, MPa *) 5 140 3 120 ?% 130 Elon

8、gation A 96 E 2,5 3 1,5 3 2,5 Reduction of area - E - % I - - Hardness H - 50 (for information) - Shear Strength R, MPa 1 - - Bendlnn k- Impact - - J or J/crn2 - - tamperaturcr OC - - Tlme th - - - W stress 0.g MPa *) W - U o Elongitlon e % - - - Rupture Eiongntlon etnipaire A * strear MPa 1 - - Not

9、es *) 1 MPa= 1 N/mm* i), 2), 3), 4), 5), 6), see line 98 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECMA PREN2735 6 m LOL23LL OOOYOb L m prES273

10、5 Page 4 1 c Designation Notes Typical use I) Zirconium soluble in dilute hydrochloric acid. 2) The values indicated are minima obtained on tensile test specimens conforming 3) Separately cast test saniples. 4) Test samples taken from any zone. 5) Test samples taken from a designated zone. 6) For greater thicknesses values must be agreed. to s.6.5 of EN2076-3. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-