ASD-STAN PREN 2003-2-2000 Aerospace Series Steels Test Methods Part 2 Izod Impact Test (Edition P 1)《航空航天系列 钢材的试验方法 第2部分 悬臂梁式冲击试验 第P1版》.pdf

《ASD-STAN PREN 2003-2-2000 Aerospace Series Steels Test Methods Part 2 Izod Impact Test (Edition P 1)《航空航天系列 钢材的试验方法 第2部分 悬臂梁式冲击试验 第P1版》.pdf》由会员分享，可在线阅读，更多相关《ASD-STAN PREN 2003-2-2000 Aerospace Series Steels Test Methods Part 2 Izod Impact Test (Edition P 1)《航空航天系列 钢材的试验方法 第2部分 悬臂梁式冲击试验 第P1版》.pdf（10页珍藏版）》请在麦多课文档分享上搜索。

1、STD-AECMA PREN 2003-2-ENGL 2000 I 101231L OOL7474 157 Edition approved for publication Comments should be sent within six months after the date of pubiication to AECMA STANDARD NORME AECMA AECMA NORM C5 Chairman prEN 2003-2 Edition P I January 2000 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE

2、INDUSTRIES (AECMA) Gulledelle 94 - B-1200 BRUXELLES - Tel. (+32) 2 775 81 10 - Fax. (+32) 2 775 81 11 ICs: Descriptors: ENGLISH VERSION Aerospace series Steels Test methods Part 2: Izod impact test Srie arospatiale Acier Mthodes dessais Partie 2: Essai de rsilience Izod Luft- und Raumfahrt Stahl Prf

3、verfahren Teil 2: Izod-Kerbschlagbiegeversuch 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 AECMA- Members. It has been technically approved by the experts of

4、 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-identification of the standard. After e

5、xamination and signature of the AECMA Standard Checking Centre (NPS) and formal agreement of the Oficial Services of the Member countries it will be submitted as a draft European Standard to CEN (European Committee for Standardization) for formal vote. 2000-01-31 AECMA Gulledelle 94 8-1200 BRUXELLES

6、 Mr Evetts I I I aecma 2000 COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling ServicesSTD-AECMA PREN 2003-2-ENGL 2000 = 1012311 0017475 O73 Page 2 , prEN 2003-2: 2000 Contents O Introduction 1111.-.,.,.,.,.,.,.,. 1 Scope . , .,. . 2 Normative ref

7、erences 3 Definitions 4 5 Principle . 6 7 Annex A (normative) Test pieces _. . -. Health and safety . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . - -. . .- . .- Testing requirements . Test report . . . . . . . . . . COPYRIGHT Association Europeen

8、e Des Constructeurs de Materiel AerospaceLicensed by Information Handling Services- STD*AECMA PREN 2003-2-ENGL 2000 1012311 0017476 T2T Page 3 prEN 2003-2: 2000 O Introduction This standard is part of the series of EN metallic material standards for aerospace applications. The general organization o

9、f this series is described in EN 4258. I Scope This standard specifies the Izod impact test method for steel products used for aerospace applications. It shall be applied when referred to in the EN technical specification or material standard unless otherwise specified on the drawing, order or inspe

10、ction schedule. 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 dated references, subsequent amendmen

11、ts 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. IS0 286-1: 88 IS0 system of limits and fits - Part 1: Bases of tolerances, deviatio

12、ns and fits EN 2003-3 Aerospace series - Test methods for steel products - Part 3: Calibration of pendulum impact testing machines 1) EN 4258 EN 4259 3 Aerospace series - Metallic materials - General organization of standardization - Links between types of EN standards and their use Aerospace series

13、 - Metallic materials - Definitions of general terms 2) Definitions For the purposes of this standard, the following definitions apply: 3.1 General terms See EN 4259. I) Published as AECMA Standard at the date of publication of this standard 2) In preparation at the date of publication of this stand

14、ard COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling ServicesSTDoAECMA PREN 2003-2-ENGL 2000 W 1012311 0017977 7bb = Page 4 prEN 2003-2: 2000 Parameter Reference in figure AI to A5 3.2 Other terms The definitions of parameters applicable to this

15、 standard are as indicated in figures AI to A5 Table I give the units to be used. Unit Table 1 - Units 1 2 Length of test piece mm Diameter of test piece mm 4 5 mm I 3 I Depth below notch I Angle of notch Degree Root radius of notch mm 7 a mm Distance of plane of symmetry of notch from free end of t

16、est piece and from adjacent notch 6 I mm Degree Distance beiween base of notch (tops of grips) and point of test piece hit by striker Angle between plane of symmetry of notch and longitudinal axis of test piece 9 10 Degree Degree Angle between top face of grips and face holding the test piece vertic

17、al Angle at tip of striker Angle between normal plane to test piece and underside face of striker at striking point Degree II I 12 - Radius at tip of striker Energy absorbed by breakage mm ft.lbf or J as specified 4 Health and safety Resources, test pieces, test samples, test materials, test equipme

18、nt and test procedures shall comply with the current health and safety regulations/laws of the countries where the test is to be carried out. Where materials and/or reagents which may be hazardous to health are specified, appropriate precautions in conformity with local regulations and/or laws shall

19、 be taken. 5 Principle The test consists of breaking by one blow form a swinging pendulum, under conditions defined hereafter, a notched test piece gripped vertically, with the bottom of the notch in the same plane as the upper face of the grips. The blow is struck on the same face as the notch at a

20、 fixed position. The absorbed energy is a measure of the impact strength of the steel. COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling Services Page 5 prEN 2003-2: 2000 STDeAECMA PREN 2003-2-ENGL 2000 I1012311 0017478 8T2 I Parameter Distance b

21、etween base of notch (tops of grips) and point of test piece hit by striker holding test piece vertical Angle between top face of grips and face 6 Testing requirements Value 22 mm o,5 mm 90“ f 0,l“ 6.1 Resources Angle at tip of striker Angle between normal plane to test piece and underside face of s

22、triker at striking point 6.1.1 Equipmenplant 6.1 .I .I Testing machine - shall be constructed and installed rigidly and shall be verified in accordance with EN 2003-3; - the values of its principal characteristics shall comply with table 2 (see also figure Al); - the weight of the anvil and its foun

23、dations shall be at least 40 times the weight of the pendulum; - the plane of swing of the pendulum shall be vertical; - the machine shall be constructed so that the loss of energy (such as from translation, rotation or vibration) in the machine framework during a test is negligible; - the centre of

24、 percussion shall be at the point of impact of the pendulum striker. 75“ I 1“ 100“ Il“ Table 2 - Characteristics of testing machine Reference in figure AI to A5 7 I 1 Radius at tip of striker Speed of striker at instant of impact I 3,5 m.s- I 0,5 rn.s- I 6.1 .i .2 CoolinglHeating equipment - means o

25、f cooling or heating test pieces to the required test temperature. 6.1.1.3 Handling equipment - means of handling tests pieces at sub-zero or elevated test temperatures. - shall be designed and usable in such a way that the temperature of the test pieces is maintained within the permitted temperatur

26、e range. 6.1.2 MaterialsiReagents - degreasing fluids; - recording paper where utilised; - cooling or heating medium for the sub-zero or elevated test temperature specified in the material standard, order, drawing or inspection schedule. 6.1.3 Qualification of personnel Testing to the requirements o

27、f this test method shall only be undertaken andlor supervised by personnel who have demonstrated their competence by a suitable education and appropriate training. COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling ServicesSTD-AECMA PREN 2003-2-EN

28、GL 2000 lJ0123LL 0037477 737 = Page 6 prEN 2003-2: 2000 1 Minimum overall length - - - 1 notch 71 mm - 2 notches 99 mm - 3 notches 127 mm - - - - 2 Diameter of test piece 11,43 mm k 0,025 mm jc12 3 Depth below notch 8,13 mm f 0,05 mm jsll 4 Angle of notch 45“ Il“ - 5 Root radius of notch 0,25 mm I0,

29、025 mm js12 6 Distance of plane of 28 mm f 0,5 mm jsl5 symmetry of notch from free end and adjacent notch 6.2 Test samples/Tect pieces 6.2.1 standard or technical specification. Sampling, number of test pieces and their location shall be as specified in the relevant material Nominal value Parameter

30、References in figure A2 to A5 6.2.2 conform to the appropriate figures as follows: The standard test piece shall have the dimensions and tolerances given in table 3 and shall Figure A2: With single notch Figure A3: With two notches Figure A4: With three notches The notch shall be of V-form (see figu

31、re A5). Where more than one notch is cut in a test piece, the notches shall be spaced and positioned as shown in figures A2 or A4. The plane of symmetry of the notch shall be perpendicular to the longitudinal axis of the test pieces. to,erances Machining IS0 symbol a Table 3 - Tolerances on specifie

32、d test piece dimensions 8 Angle between plane of symmetry of notch and longitudinal axis of test piece 90“ f I“ I a In accordance with IS0 286-1. 6.2.3 The test piece shall be machined all over. Machining shall be carried out in such a way that any alteration of the test piece, for example due to co

33、ld working or heating, is minimized. The notch shall be carefully prepared so that no grooves, parallel to the base of the notch, are visible to the naked eye. The test piece may be marked on an end face. 6.3 Test procedure When required, a written instruction detailing the technique to be used for

34、the testing of a specific material and, when applicable, testing conditions, shall be prepared. COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling Services Page 7 prEN 2003-2: 2000 STD*AECMA PREN 2003-2-ENGL 2000 3032313 0037480 450 W 6.3.1 Test p

35、iece 6.3.1 .I - the longitudinal axis of the test piece shall lie in the plane of swing of the centre of the pendulum; - the notch shall be positioned so that its plane of symmetry coincides with the top face of the grips; - the notch shall be at right angles to the plane of swing of the centre of g

36、ravity of the pendulum: this shall be ensured by the form of the test piece and the method of grip; - the test piece shall be gripped tightly in the anvil grips. The test piece shall be placed in the testing machine such that: 6.3.1.2 During testing of the two-and three-notch test pieces, the materi

37、al remaining for testing after each test shall be examined so that the correct length of test pieces is available above the next notch. Any undesirable deformed metal shall be removed to ensure that the form and length of the test piece are correct before further testing. 6.3.2 Test temperature The

38、test shall be carried out at 10 “C I 0 I 35 “C, unless otherwise specified. In cases of dispute the test shall be performed at 8= 23 “C f 5 “C. If the temperature tolerance is not specified f 2 “C shall be used. For tests at temperatures other than ambient, the test piece shall be immersed in the co

39、oling or heating medium for sufficient time to ensure that the required temperature is reached throughout the test piece (for example, at least 10 min in a liquid medium or at least 30 min in a gaseous medium). The test piece shall be broken within 5 c of the time of removal from the medium. 6.4 Exp

40、ression of results 6.4.1 shall be expressed in the units specified by the material standard, order, drawing or inspection schedule. The results (the absorbed energy for each notch and/or average absorbed energy, as required) 6.4.2 piece was not broken by “x“ (the energy absorbed). If, during the tes

41、t, the test piece is deformed but not broken, the test report shall state that the test 7 Test report All results shall be in written form and the test report shall include, when relevant, at least the following information: - reference to this standard; - any other information relevant to the test

42、(e.g. test condition, test temperature, test equipment, test procedure, nominal energy of the striker, verification, . ); - identification and traceability of the semi-finished product to be tested in accordance with the technical specifications of the test piece; - identification and traceability o

43、f test samples taken from the semi-finished product (e.g. location, orientation, size); - identification and traceability of test pieces taken from test samples (e.g. number, preparation, method, conditioning); - expression of results (e.g. individual or mean values); - recorded plots/graphs when ne

44、cessary; - date of test; - traceability to the individual performing the test work; - any incident which may have affected the results; - any deviation from the test method standard. COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling Services Page

45、 8 STD*AECMA PREN 2003-2-ENGL 2000 LOL23LL 001748L 397 = prEN 2003-2: 2000 Annex A (normative) Test pieces r NOTE: A small radius should be incorporated at the edge of the back grip. Figure AI - Sketch showing angle and radius of striker, and inclination of striker to horizontal for cantilever type

46、test piece (elevation) COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling ServicesI 1 I I- -1 Figure A2 - Single-notch round test piece i+$ fi 1 6 # L 7 - -I- =Y Figure A3 - Two-notch round test piece A-A I A-A I Figure A4 - Three-notch round test

47、 piece COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling ServicesSTD=AECMA PREN 2003-2-ENGL 2000 1012311 0017Lid3 LbT W Page 10 prEN 2003-2: 2000 L 5 Figure A5 - Enlarged view of notch for round test piece COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling Services