1、AECMA STANDARD NORME AECMA AECMA NORM prEN 6036 Edition P1 December 1995 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES (AECMA) Gulledelle 94 - 8-1200 BRUXELLES - Tel. (32) 2 775 81 10 - Fax. (32) 2 775 81 11 ICs : Descriptors : ENGLISH VERSION Aerospace series Fibre reinforced plasti
2、cs Test method Determination of notched, unnotched and filled hole compression strength Srie arospatiale Matires plastiques renforces de fibres Mthode dessai Dtermination de la rsistance en compression troue, lisse et troue habite Luft- und Raumfahrt Faserverstrkte Kunststoffe Prfverfahren Bestimmun
3、g der Kerbdruckfestigkeit an gekerbten, ungekerbten und gebolzten Probekrpern 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 technic
4、ally 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-identifi
5、cation of the 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 formal vote. Nota - Extra co
6、pies can be supplied by B.N.A.E. - Technopolis 54 - 199, rue Jean-Jacques Rousseau - 921 38 ISSY-LES-MOULINEAUX CEDEX I Comments should be sent within six months after the date of publication to I Edition approved for publication 1995-1 2-1 5 AECMA Gulledelle 94 B-1200 BRUXELLES AIB/TF6 Chairman Mr
7、K. Schneider aecma 1995 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-,-,-_ AECMA PRENxb03b 95 m 10L23LL OOLOLb7 933 Page 2 prEN 6036 : 1995 Contents lis
8、t 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 Procedu re Presentation of the results Test report Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECM
9、ANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECMA PRENxb03b 95 W LO12311 0010Lb8 87T Page 3 prEN 6036 : 1995 1 Scope This standard defines a method to be used to determine the compression strength of notched, unnotched and filled hole fibre reinforced plastics
10、. It is applicable to composite laminates with unidirectional layers or woven fabric reinforcement. This standard does not give any direction necessary to meet health and safety requirements. It is the responsibility of the user of this standard to consult and establish appropriate health and safety
11、 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 publications are listed hereafter. For dated references, subsequent amendment
12、s 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 2374 Aerospace series Glass fibre reinforced mouldings and sandwich Production o
13、f test panels Fibre reinforced plastics Determination of the action of liquid chemicals 1) EN 2489 Aerospace series EN 2565 Aerospace series EN 2743 Aerospace series Preparation of carbon reinforced resin panels for test purpose 1) Fibre reinforced plastics Standard atmospheres for conditioning and
14、testing 1) Fibre reinforced plastics Test method for the determination of the effect of exposure to humid atmosphere on physical and mechanical characteristics EN 2823 Aerospace series - 3 Definitions 3.1 Notched compression strength Maximum compression load experienced by the notched test specimen
15、divided by the initial cross sectional area within the gauge length. 3.2 Unnotched compression strength Maximum compression load experienced by the unnotched test specimen divided by the initial cross sectional area within the gauge length. 1) Published as AECMA Prestandard at the date of publicatio
16、n of this standard 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-,-,-AECIA PRENxb03b 95 W LOL23LL 00LOlb9 70b Page 4 prEN 6036 : 1995 3.3 Filled hole com
17、pression strength Maximum compression load experienced by the filled hole test specimen divided by the initial gross cross sectional area within the gauge length. 3.4 KT value Unnotched compression strength divided by the filled hole compression strength. 3.5 KT value Unnotched compression strength
18、divided by the notched compression strength. 4 Principle of the method A compression test on unnotched specimen is carried out in order to determine the original material strength. The same test is performed either on notched or a filled hole specimen to determine the residual strength. 5 Designatio
19、n of the method The designation of the method shall be in accordance with the following example. Description block Identity block Determination of notched, unnotched and filled hole compression strength Fibre reinforced plastics Number of this standard Specimen types II (see figures 1 to 3) Laminate
20、 configuration A (see table 1) 6 Apparatus 6.1 Compression test machine accurate to within 1 % equipped with facilities to record maximum bad and fitted with suitable grips or used with compression jig featuring a grip and movement alignment system. 6.2 Chamber adapted to the machine to carry out te
21、sts at temperature. The temperature shall be maintained within f 3O C. 6.3 Timer. 6.4 Thermocouple with recorder to monitor temperature for tests at other than ambient. 6.5 Fiat-faced micrometer with 6 mm diameter faces, accurate to 0.01 mm. 6.6 Vernier calliper accurate to the nearest 0,l mm. Copyr
22、ight 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 5 prEN 6036 : 1995 7 Test specimen 7.1 Specimen description For the description, dimensions and toleran
23、ces, see figure 1 for notched type specimen, figure 2 for unnotched type specimen and figure 3 for filled hole type specimen. The laminate configuration for the fibre directions are defined in table 1. 7.2 Test specimen preparation The specimens are cut out from laminates. The coefficient of variati
24、on in the thickness measurements shall be smaller than 2% per laminate. The laminates shall be produced according to EN 2565 for carbon and in accordance with EN 2374 for glass. Special precautions have to be taken to ensure that no delamination occur during machining especially for the drilling of
25、the notched and filled hole test specimens. The laminate should be inspected for example by C-Scan to establish that the laminate is worth testing. If the NDT reveals unacceptable defects, limits defined in the specification invoking the test, the laminate should not be tested. The process parameter
26、s shall be in line with the specification invoking the test. 7.3 Tabs The tests may be performed without the specimen being tabbed. However, if tabs are used they shall be strain compatible with the composite being tested either, by using precured tabs of 2 plies of fabric, lay-up (+45,-45) or by co
27、-bonding using a suitable prepreg system. The precured tabs shall be bonded on both specimen faces with an adhesive system that will meet the temperature and ageing requirements. Care should be taken to avoid the bonding temperature to add any undesired post cure effect to the laminate. 7.4 Number o
28、f specimens Five specimens shall be tested per test condition, except when otherwise specified in the technical specification. If tests are carried out after ageing or at a temperature different from room temperature, care should be taken to assure that room temperature/dry reference specimens, whic
29、h had been machined from the same plate as the specimens under investigation are also tested. 7.5 Ageing In case of tests afer immersion, the conditions shall be according to EN 2489. For tests after exposure to humid atmosphere, the conditioning shall be in accordance with EN 2823. 8 Procedure 8.1
30、Conditioning The storage and testing of as received specimens shall be carried out at (23 f 2)“C, (50 f 5)“h relative humidity in accordance with EN 2743. Aged specimens shall be tested within a maximum of 8 hours after removal from the exposure environment. Copyright Association Europeene des Const
31、ructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 6 prEN 6036 : 1995 8.2 Determination of dimensions Measure and record the thickness and width at three points in the gauge length of the sp
32、ecimen before ageing and again before mechanical testing. Use the micrometer (see 6.5) for the thickness and the vernier calliper (see 6.6) for the width. Average the three measurements. 8.3 Test at ambient temperature Place the specimen in the jaws, ensuring that it is aligned within 1 O and centre
33、d on the machine axis. Note: The jaws shall fully cover the tabs if used. Select the load range such that failure occurs between 20% and 80% of full scale. Compression load shall be applied at a constant cross head speed of 0,5 mm/min. Record the maximum load Pr 8.4 Test at temperature other than am
34、bient Apply a thermocouple (see 6.4) on the composite material as close as possible to the centre of the specimen and seal the thermocouple from the surrounding air by using vacuum bag sealant. After a dry specimen has reached a temperature of 2C below the required elevated temperature or 2C above t
35、he required su-zero temperature, thhe specimen shall be maintained at the required condition for five minutes prior to testing. The above time for aged specimen is 1 minute. The heat up/soak cycle used shall be given in the test report. For specimens that have been subjected to fluid immersion, appl
36、y EN 2489. For specimens that have undergone humidity ageing, apply EN 2823. Follow the same procedure as for the test at ambient temperature. 9 Presentation of the results 9.1 Compression strength OC For notched specimens Om = For filled hole specimens ocf = For unnotched specimens Om = Pr txw Pr t
37、xw Pr txw 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-,-,-AECMA PRENwb03b 95 = 1012311 0010172 2TO Page 7 prEN 6036 : 1995 where : Gcn, Ocf, Ocu are th
38、e compression strength for, notched, filled hole and unnotched specimens, in MPa is the maximum load, in Newton is the specimen width, in millimetres is the thickness of the specimen, in millimetres Pr W t 9.2 Nominal compression strength WC For notched specimens For filled hole specimens Pr CPcf =
39、tn x w For unnotched specimens where : vcn, Vcf, CU are the nominal compression strength for, notched, filled hole and unnotched specimens, in MPa is the maximum load, in Newton is the specimen width, in millimetres is the nominal thickness of the specimen, in millimetres as specified in the relevan
40、t specification Pr W tn - 9.3 KT value (see 3.4) 9.4 KT value (see 3.5) 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-,-,-AECMA PRENub036 95 W 1012311 00
41、10173 137 W Page 8 prEN 6036 : 1995 10 Test report The test report shall refer to this standard and shall include the following. 10.1 10.2 10.3 10.4 10.5 10.6 10.7 10.8 10.9 Complete identification of the material tested, including at least type, source, manufacturers code number, fibre areal weight
42、, filament count, processing details. All details regarding specimen preparation (including when applicable : tabs material, tabs adhesive and curing condition of this adhesive). The measured specimen dimensions. Ageing and/or exposure conditions prior to the test. Date of test, facility and identif
43、ication of individuals performing the test. Equipment, method and test parameters used. Individual values, mean value and standard deviation of compression strength for notched, unnotched and filled hole specimen. KT values Any incident which may have affected the results and any deviation from this
44、 standard. 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-,-,- AECMA PRENxb03b 95 = 1012311 0010174 073 Fibre mass per unit area (9/m2 1 Page 9 prEN 6036
45、: 1995 Quasi-isotropic laminates Type A Table 1 : Laminate configurations Lay-ups for different fibre mass per unit area Directed and quasi-isotropic laminates Tapes 130 -145 160 -1 90 260 -290 ( 45, O , -45,90 ) 4 sym (45, O, -45,90) 3sym (45, O, -45,90) 2sym Fabrics Directed laminates Type B ( O ,
46、45, -45 , O ,90 ) 3 sym ( o ,45 , -45 , O ,90 ) 2 sym ( O, 45, -45, O, 90) 2sym 1) 0“ is equivalent to warp direction and 90“ is equivalent to weft direction 2) n to be determined to have a laminate thickness as close as possible to 4 rnm Copyright Association Europeene des Constructeurs de Materiel
47、 Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECIA PREN*b03b 95 LOL23LL 0030375 TOT Page 10 prEN 6036 : 1995 I Tabs Dimensions in mm L=21 +30mm 1 = tab length : Function of the equipment (test machine, jaws, e
48、tc) and i or the material to be t : according to lay-up (see table 1) tested (tabs must be able to transfer the shear loads). Figure 1 : Notched compression specimen - Type I Dimensions in mrn L = 2 I + 30 mm 1 = tab length : Function of the equipment (test machine, jaws, etc) and / or the material to be t : according to lay-up (see table 1) tested (tabs must be able to transfer the shear loads). Figure 2 : Unnotched compression specimen - Type Il Note: Parallelism of tab faces must be maintained to within 0,05 mm across width and length Tabs faces must be pararallel with specimen faces to
