AECMA PREN 6034-1995 Aerospace Series Carbon Fibre Reinforced Plastics Test Method Determination of Interlaminar Fracture Toughness Energy Mode II - GIIc Edition P1《航空航天系列.纤维加固塑料试验.pdf

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1、AECMA STANDARD NORME AECMA AECMA NORM Edition approved for publication 1995-1 2-1 5 prEN 6034 Edition PI December 1995 AIBITFG Chairman Mr K. Schneider Comments should be sent within six months after the date of publication to AECMA Gulledelle 94 6-1 200 BRUXELLES PUBLISHED BY THE EUROPEAN ASSOCIATI

2、ON OF AEROSPACE INDUSTRIES (AECMA) Guiledelle 94 - 8-1200 BRUXELLES - Tel. (32) 2 775 81 10 - Fax. (32) 2 775 81 11 ICs : Descriptors : ENGLISH VERSION Aerospace series Carbon fibre reinforced plastics Test method Determination of interlaminar fracture toughness energy Mode II - GIIC Srie arospatial

3、e Matires plastiques renforces de fibres de carbone Mthode dessai Dtermination de lnergie de tnacit en rupture interlaminaire Mode II - GIIC Luft- und Raumfahrt Kohlenstoffaserverstrkte Kunststoffe Prfverfahren Bestimmung der interlaminaren Energiefreisetzungsrate Mode II - GI, This “Aerospace Serie

4、s“ 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 the concerned Technical Committee following comment by the Member c

5、ountries. 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 examination and signature of the AECMA Standard Checking Centre (NPS)

6、 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. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA

7、Not for ResaleNo reproduction or networking permitted without license from IHS-,-,- AECMA PREN+b034 95 = 10123Ll OOLOL59 867 = Page 2 prEN 6034 : 1995 Contents list 1 2 3 4 5 6 7 8 9 10 Scope Normative references Definitions Principle of the method Designation of the method Apparatus Test specimen P

8、rocedure Presentation of the results Test report 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-,-,-Page 3 prEN 6034 : 1995 1 Scope This standard specifie

9、s the procedure to determine the mode II interlaminar fracture toughness energy GI, of carbon fibre composites manufactured from unidirectional fibre tape or woven fabric. This standard does not give any directions necessary to meet health and safety requirements. It is the responsibility of the use

10、r of this standard to consult and establish appropriate health and safety precautions. 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 publ

11、ications are listed herafter. For dated references, subsequent amendments 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. EN 2565 Aer

12、ospace series Preparation of carbon fibre reinforced resin panels for test purposes I EN 2743 Aerospace Series Reinforced Plastics Standard procedures for conditioning and testing ” EN 2823 Aerospace series Fibre reinforced plastics Test method for the determination of the effect of exposure to humi

13、d atmosphere on physical and mechanical characteristics - Parameters for conditioning and testing ” EN 6033 Carbon Fibre Reinforced Plastics Determination of interlaminar fracture toughness energy - Mode I - Glc-test 3 Definitions 3.1 Interlaminar fracture toughness energy The interlaminar fracture

14、toughness energy is the energy per unit plate width which is necessary to produce an unit crack growth at an interlaminar crack between two plies of a laminate. 3.2 Mode II The mode indicates the method by which the load is applied to produce the crack. Mode II crack extends as a result of shear for

15、ces at the crack tip introduced by a flexural test. 3.3 GI, GI, is the designation of the interlaminar fracture toughness energy determined by a mode II test procedure. I Published as AECMA Prestandard at the date of publication of this standard Copyright Association Europeene des Constructeurs de M

16、ateriel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,- AECMA PRENMb034 95 W LOL23LL OOLOLb1 415 = Description block Carbon fibre reinforced plastic materials Page 4 prEN 6034 : 1995 Identity block EN t 334 - 4 P

17、rinciple of the method The end notched flexure specimen is used for mode II testing. A precracked specimen is loaded in a three point bend fixture (see figure 21 until crack propagation onset. The load applied to the specimen and the cross head displacement of the test machine are recorded continuou

18、sly during the test. The total fracture toughness energy is calculated from the initial crack length and load-displacement diagram. 5 Designation of the method Number of this standard 6 Apparatus 6.1 Test machine accurate to within 1 % in the load range used. 6.2 Device for recording the deflection

19、as a function of load accurate to within 1 % in the deflection range used. 6.3 Vernier caliper accurate to the nearest 0,l mm. 6.4 Flat face micrometer accurate to the nearest 0,Ol mm 6.5 Microscope of a magnification of 15 - 25 7 Test specimen 7.1 Test specimen description To achieve reproducable t

20、est results the G,-test shall only be performed with specimens (see figure 1) where the initial crack has been introduced in a defined mode I procedure (see EN 6033). The test specimen shall be cut from the residual part of G, specimen tested or at least loaded and cracked per EN 6033, and fulfillin

21、g the following requirements. 7.2 Test specimen preparation Prepare the required laminates according to EN 2565 method B for carbon. The crack front remains approximately a straightline perpendicular to the longitudinal direction of the specimen (as presumed by the marks performed on both already pa

22、inted longitudinal side faces of the specimen to locate the crack tips after crack stabilization unter the mode I loading). The uncracked portion of the specimen is of sufficient length to comply with the requirements of figure 1. Copyright Association Europeene des Constructeurs de Materiel Aerospa

23、tial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,- - AECMA PREN*b034 95 1012311 0010162 351 Page 5 prEN 6034 : 1995 The observation during the mode I loading did not show neither fibre bridgings nor moving of the crack to

24、plies adjacent to the mid plies. The specimen shall be cut in a way that the specified remaining crack length of figure 1 is guaranteed. Specimens longer than 1 12 mm can be used to realize a serie of tests for the determination of GlIc if needed. Appropriate identification shall be maintained throu

25、ghout the specimen preparation to ensure traceability to the GI, specimen and to the original laminate. If not otherwise defined by the specification invoking the test, three specimens shall be tested per test condition. CAUTION: When testing fabric material, the results may be influenced by the pos

26、ition of the crack between the layers (nested, unnested etc.). It shall be clearly stated which interlaminar area shall be tested and how to manufacture the specimens. 8 Procedure 8.1 Conditioning If not otherwise defined by the specification invoking the test, specimens to be tested dry or in the a

27、s cured state , should first be conditioned at (23 f 2)OC, (50 f 51% RH in accordance with EN 2743, same requirements to be applied to perform room temperature testing. Aged specimens shall be tested directly after ageing procedure (a maximum storage of 8h at (23 f 2C is allowed before testing). 8.2

28、 Determination of dimensions The width and length of the specimens shall be measured using a vernier caliper (see 6.3). A minimum of three thickness measurements distributed over the specimen shall be made using a flat face micrometer of 6.4, the average shall be recorded. 8.3 Testing the crack leng

29、th has to be measured by vernier caliper (see 6.31, using the microscope (see 6.51. A thin layer of white ink applied to the longitudinal side faces of the specimen may be used to facilitate this measurement. For the entire duration of the test, a continuous load-displacement record shall be made, m

30、easuring the displacement of the loading nose. Place the specimen in the test fixture in accordance with figure 2, assuring the position of the initial crack : a = (35 t llmm. The following procedure shall then apply: Adjust the load cell reading at zero Remove any slack between the loading nose and

31、 the specimen by making the needed displacement - Adjust the displacement reading at zero if necessary 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-,-,-

32、 - - AECMA PRENxb034 95 = LOL23LL OOLOLb3 298 9 Page 6 prEN 6034 : 1995 Adjust the displacement reading at zero if necessary Load the specimen under displacement control at a displacement rate of 1 mm/min Optically observe the crack tip in order to detect the crack propagation onset (microscope of 6

33、.5) Record the critical load at delamination crack onset and stop the loading as soon as evidence of crack propagation has been confirmed by a small load drop 8.4 Elevated and sub-zero temperature tests If not otherwise defined by the specification invoking the test, apply a thermocouple on the spec

34、imen as close as possible to cracked area of the specimen and seal the thermocouple from the surrounding air by using vacuum bag sealant. The soak time at test temperature, defined by the specification invoking the test, shall be (5 & 0,5)min for dry specimens and in accordance with EN 2823 for cond

35、itioned specimen. If more then one determination is provided for, wait for crack stabilization under load and mark the current tip location on the painted sides of the specimen Unload the specimen to zero The complete procedure shall be repeated for the subsequent determinations when needed. Unless

36、otherwise specified, the remaining uncracked portion of the specimen shall be delaminated after removal from the test fixture (cooling the specimen down to liquid nitrogen temperature will facilitate this operation). Verification measurements of the crack lengths shall then be made from the crack fr

37、ont (thumbnail marks) on the fractured specimen. Care shall be taken to protect the delamination surfaces for later inspection of failure mode if requested. The results shall be analysed in accordance with 9. 9 Presentation of the results 9.1 Calculation To calculate GI, the following formula shall

38、be used : 9 x P x a x d x 1000 2xw (1/4 L3 + 3a3) - G IIC - where : GIIC d P a W L is the fracture toughness energy, in J/mZ is the crosshead displacement at crack delamination onset, in millimetres is the critical load to start the crack, in Newton is the initial crack length (see figure 21, in mil

39、limetres is the width of the specimen, in millimetres is the span length (see figure 21, in millimetres 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-,-,

40、- AECMA PREN*b034 95 LOL23LL 0010164 124 m Page 7 prEN 6034 : 1995 9.2 Test results validation The test results and calculation shall be valid if the crack front is approximately perpendicular to the specimen longitudinal direction and does not extensiveley change from a straigthline across the widt

41、h of the fractured test specimen. 10 Test report The test report shall refer to this standard and include the following : 10.1 10.2 10.3 10.4 10.5 10.6 10.7 10.8 Complete identification of the tested material, including manufacturers name, designation, batch number etc. All details about the prepara

42、tion of specimens Measured dimensions of the specimens Ageing and/or exposure conditions prior to the test Date of test, facility and identification of individuals performing the test Equipment, method and test parameters used Individual test results and calculations plus a typical set of load-displ

43、acement curves. The individual curves shall be kept in file by the test laboratory. Any incident which may have effected the results and any deviation from this standard. Movement of the crack to plies adjacent to the mid plies shall be reported. Copyright Association Europeene des Constructeurs de

44、Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 8 prEN 6034 : 1995 a cuts from G, specimen loading nose (steel) - I r, = 12,5 2 0,l rfl I 1 -5 I -m “t / I 110 mm (25,O -L 0,2) mm (3,O I O,2) mm (40 f

45、 1) rnrn - I - W t - C - - Figure 1 : Test specimen support (steel) r2 = 5,O = 0,l - u2 I L = 100 t 0,5 All dimensions in mm Figure 2 : Test fixture 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-,-,-