AECMA PREN 2561-1989 Aerospace Series Unidirectional Laminates Carbon-Thermosetting Resin Tensile Test Parallel to the Fibre Direction Issue P 1《航空航天系列碳纤维增强塑料 单项碾压热硬化碳树脂平行于纤维方向延展测试.pdf

1、AECMA PREN2561 89 1012333 0003506 3 i -, A. E. C. M. A. STAN DAR D NORME A.E.C.M.A. A.E.C.M.A. NORM prEN 2561 Issue P I April 1989 EDITE PAR LASSOCIATION EUROPENNE DES CONSTRUCTEURS DE MATERIEL AEROSPATIAL 88, boulevard Malesherbes, 75008 PARIS - TEL. 45-63-82-85 UDC : Key words ENGLISH VERSION Aero

2、space series Unidirectional laminates carbon-thermosetting resin Tensile test parallel to the fibre direction Srie arospatiale Stratifis unidirectionnels carbone-rsine thermodurcissable Essai de traction paralllement au sens des fibres Luft- und Raumfahrt Unidirektionale Kohlenstoffaser- Duroplast-V

3、erbundwerkstoffe Zugprfung parallel zur Faserrichtung This Aerospace Series pre-standard 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 approve

4、dby the experts of the concerned AECMA Commission folloiUing comment by the Member countries. Subsequent to the publication of this pre-standard, the technical content shall not be changed to an extent that interchangeability is affected, physically or functionally, without re-identification of the

5、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 final vote. Nota - Extra copies can be sup

6、plied by B.N.A.E. - 8, rue Moreau-Vauthiet - 92100 BOULOGNE-BILLANCOURT Edition approved for publication Comments should be sent within six months C7 Chairman after the date of publication decision 25th April 1989 A.E.C.M.A. Mr BEZAUD 88, Bd. Malesherbes 75008 PARIS - FRANCE 0 aecma 1989 COPYRIGHT A

7、ssociation Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling Services AECMA PREN25bL 89 LOL23LL 0003507 5 prEN 2561 Page 2 Issue P 1 Contents 1 2 3 4 5 6 7 8 9 10 11 12 Scope and field of application Ref ererices Principle of the method Definitions Designation of the

8、method Test specimens Apparat us Conditioning Procedure Expression of results Vaiidit y Test report Annex A COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling ServicesAECMA PREN25bL 87 1012311 0003508 7 D prEN 2561 Page 3 Issue P 1 1 Scope and fie

9、ld of application This standard specifies the procedure for determining t.,e ultimate tens strength tensile modulus and, if required, the POISSONS ratio and elongation rupture in tension for carbon fibre reinforced unidirectional laminates. le at This procedure is only applicable to test specimens w

10、here the axis is parallel to the direction of the fibres. 2 References EN 2489 Aerospace series - Fibres reinforced plastics - Determination of the action of liquid chemicals 1) EN 2565 Aerospace series - Preparation of carbon fibre reinforced resin panels for test purposes 1) EN 2743 Aerospace seri

11、es - Fibres reinforced plastics - Standard atmospheres for conditioning and testing 2) EN 2744 Aerospace series - Non-metallic materials - Preferred test temperatures 2) EN 2823 Aerospace series - Fibres reinforced plastic materials - Exposure to humid atmosphere - Parameters for conditioning and te

12、sting 2) 3 Principe of the method The method entails the measurement of the longitudinal and, if required, the lateral strains in the material, in terms of the load applied, during a tensile test carried out at a constant rate of displacement until failure occurs. 4 Def nit ions 4.1 Tensile load exp

13、erienced by the test specimen at a particular moment during the test, per initial unit cross sectional area within the gauge length. Tensile stress at a given moment during the test 1) Published as AECMA pre-standard 2) In preparation COPYRIGHT Association Europeene Des Constructeurs de Materiel Aer

14、ospaceLicensed by Information Handling ServicesAECMA PREN2561 87 4 1012311 0003509 9 prEN 2561 Page 4 Issue P 1 1) 4.2 Tensile stress at failure Tensile stress at the time failure occurs. It is calculated using the formula given in clause 10.1. 4.3 Stress at failure normalised to the fibre (6,) Tens

15、ile load supported by the fibres in the test specimen at the time failure occurs, per initial unit cross-section of area of the fibres in the gauge leng t h . It is calculated using the formula given in clause 10.2. 4.4 Variation in the distance between gauge marks on the test specimen gauge length,

16、 produced by a tensile load and expressed with respect to the initial distance between the gauge marks. e Eq2 is the relative strain measured perpendicular to the axis of the fibres (in tfie plane of the laminate). Relative strains ( e, and e22) is the relative strain measured parallel to the axis o

17、f the fibres. 11 4.5 Percentage elongation at rupture (A%) Increase in the distance between the marks on the test specimen gauge length, produced by a tensile load and expressed as a percentage of the initial distance between the gauge marks and measured at the moment of failure. It is calculated us

18、ing the formula given in clause 10.6. 4.6 Secant modulus for PR/2 (ETll) Clope of the straight line passing through the point of the. diagram showing stresc/relative strain parallel to load axis, corresponding to a stress calculated from P /2 and through the point on the same diagram corresponding t

19、o a stress calculated from PR/lO, where P is the load at failure for the specimen. It is calculated using the formula given in para 10.3, R R 4.7 Modulus normalised to the fibre (Ef) Clope of the straight line passing through the point of the diagram showing stress/relative strain parallel to load a

20、xis, corresponding to a fibre stress calculated using PR/2, and through the point on the same diagram corresponding to a fibre stress calculated from P /lo. It is calculated using the formula in clause 10.4. R 4.8 POISSONS ratio ( a12) Absolute value of the ratio of the increase in relative strain t

21、o the measured between P /2 and Pif10 (see 12.1 Reference to this standard, trade mark, identification codes, origin, date of receipt and other detaiis regarding the tested product. 12.2 All details regarding specimen preparation. 12.3 The measured specimen dimensions and the type of specimen chosen

22、. 12.4 The test conditions, for example test temperature, relative humidity if these differ from standard. 12.5 Period of soak at the test temperature, for tests after immersion (see EN 2489) or exposure to humid atmosphere (see EN 2823). 12.6 Present a diagram showing recorded load against time or

23、strain. 12.7 Stress to failure 6T11 and the mode of failure, 12.8 The method of relative strain measurement (extensometer or strain gauges), 12.9 The secant modulus at PR/2 (ETll), 12.10 POISSONS ratio d12, 12.11 The stress normalise to the fibre 6 (if required), f o 12.12 The secant modulus at P /2

24、 normalised to the fibre (Ef) (if required). R 12.13 Elongation per cent: AX at rupture, 12.14 Observations on any circumstances liable to influence the results, 12.15 The individual values, arithmetic mean and standard deviation shall be noted. 6 COPYRIGHT Association Europeene Des Constructeurs de

25、 Materiel AerospaceLicensed by Information Handling ServicesAECMA PREN25b1 49 W 1012311 0003516 b - - prEN 2561 Page 11 Issue P 1 Annex A Form and dimensions of test specimen Test Set-up Figure A.l q - Test specimen and test jig, types A and B I L Figure A.2 - Test specimen and test jig, type C COPY

26、RIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling ServicesAECMA PREN2561 89 m 3012333 0003537 8 m prEN 2561 Page 12 Issue P 1 I I I Dimensions iii millimetree 250 + 1 Width b 10 - + 0,5 16 2 0,5 16 - + 0,5 I 250 -t- 1 - 250 + 1 - Length L - Thickness

27、 h 2 I + 0,2 1 - + 0,2 (1) Length of specimen end tabs t 50 - t 80 (2) 50 5 t 80 (2) (3) Projection of jaws C Gripped length d Free part g 90 g 150 - 130 90 g 150 - - Comments : (1) If the ply thickness causes any uncertainty regarding the number of layers necessary to obtain a material of the requi

28、red thickness, this number of plies shall be specified in the particular specification for the product. (2) Type A and B test specimens are provided with end tabs of 1581 glass-epoxy laminate, arranged at 2 45“ (thickness between 0,5 mm and 1 nun) and bonded onto the specimen using an adhesive. The

29、type of adhesive and its curing cycle shall be compatible with the test conditions, the thermal characteristics of the end tabs and that of the composite material being tested. (3) Type C test pieces do not have any end tabs. This type of test piece should be reserved for machines with jaws whose grip strength is regulated during the test (hydraulic device or equivalent), COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling Services