AECMA PREN 2562-1989 Aerospace Series Unidirectional Laminates Carbon-Thermosetting Resin Flexural Test 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曲折测试.P1版》.pdf

《AECMA PREN 2562-1989 Aerospace Series Unidirectional Laminates Carbon-Thermosetting Resin Flexural Test 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曲折测试.P1版》.pdf》由会员分享，可在线阅读，更多相关《AECMA PREN 2562-1989 Aerospace Series Unidirectional Laminates Carbon-Thermosetting Resin Flexural Test 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曲折测试.P1版》.pdf（9页珍藏版）》请在麦多课文档分享上搜索。

1、A. E. C. M. A. STAN DARD NORME A.E.C.M.A. A.E.C.M.A. NORM Edition approved for publication Comments should-be sent within six months after the date of publication decision 88, Bd. Malesherbes 25th April 1989 A.E.C.M.A. 75008 PARIS - FRANCE prEN 2562 Issue P 1 April 1989 C7 Chairman Mr BEZAUD EDITE P

2、AR LASSOCIATION EUROPENNE DES CONSTRUCTEURS DE MATERIEL AEROSPATIAL 88, boulevard Malesherbes, 75008 PARIS -TL. 45-63-82-85 UDC : Key words : ENGLISH VERSION Aerospace series Unidirectional laminates carbon-thermosetting resin Flexural test Srie arospatiale Stratifis unidirectionnels carbone-rsine t

3、hermodurcissable Essai de flexion Luft- und Raumfahrt Unidirektionale Kohlenstoffaser- Duroplast-Verbundwerkstoffe Biegeprf ung 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 g

4、reen paper for the needs of AECMA-Members. It has been technically approved by the experts of the concerned AECMA Commission following 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

5、is affected, physically or functionally, without re-identification 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 Com

6、mittee for Standardization) for final vote. 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 PREN2562 A7 W 10I231I 0003517 I prEN 2562 Page 2 Issu

7、e P 1 Contents 1 2 3 4 5 6 7 8 9 10 11 12 Scope and field of application References Definitions Principle of the method Designation of the method Test specimens Apparat us Conditioning Procedure Test results Expression of results Test report Copyright Association Europeene des Constructeurs de Mater

8、iel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECMA PREN2562 87 L0123LL 03520-8 H prEN 2562 Page 3 Issue P 1 1 Scope and field of application This standard defines the method for the determination of flexura

9、l strength and modulus of unidirectional carbon-thermosetting resin laminates by a flexural test. This method is restricted to specimens in which the length is parallel to the fibre direction. Note : The elastic modulus measured by this method shall only be considered as an approximate value for YOU

10、NGS modulus. 2 References EN 2489 Aerospace series - Fibre 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 series - Fibres reinforced plastics - Standard atm

11、ospheres for conditioning and testing 2) EN 2744 Aerospace series - Non-metallic materials - Preferred test temperatures 2) EN 2823 Aerospace series - Fibre reinforced plastics - Exposure to humid atmosphere - Parameters for conditioning and testing 2) 3 Definitions 3.1 Deflection (f) The distance m

12、oved during flexing by the upper or lower face of the specimen at the centre of its span compared to its initial position. 3.2 Flexural stress at a given moment during the test The maximum stress of the external fibres of the material in the middle of the span of the specimen between the supports. I

13、t is calculated according to the generalformula given in clzuse 11.1. 1) Published as AECMA pre-standard 2) In preparation Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without l

14、icense from IHS-,-,-AECMA PREN25b2 87 LOL23LI 0003523 T prEN 2562 Page 4 Issue P 1 3.3 Flexural strength at failure (b) The flexural stress at moment of failure. 3.4 Secant modulus at P 12 (Eb) The slope of the straight line passing through the relative stress/strain curve at a point corresponding t

15、o a stress calculated for P /2 aiid a point on the same curve corresponding to a stress calculated for P /lo, P is the failure load of the specimen. R R R R It is calculated according to the formula given in clause 11.2. 4 Principle of the method During a flexural test carried out at constant speed

16、until failure, the deflection at the loading nose is measured as a function of the applied load and the longitudinal relative strain calculated as a function of the applied stress, The specimen is held over a span sufficiently large that the failure does not occur in shear and strains due to shear l

17、oads may be neglected. 5 Designation of the method The designation of the method shall be drawn up according to the following example. Description block dentity block I Example : Flexural test Number of standard - Type of specimen (see sub-clause 6.1) 6 Test specimens The test specimens are taken in

18、 panels prepared according to EN 2565. 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 PREN2562 89 W L0123LL 0003522 L mp - prEN 2562 Page 5 Issu

19、e P 1 6.1 Form and dimensions of specimens Figure 1 - Specimen and test fixture Dimensions in millimetres Symbols - width =b distance between supports = thickness of specimen 1) = h r r length =L loading nose radius - support radii - lV 1 2 10 + 0,2 80 3 0,5 12,5 0,l 100 T 1 2 7 0,2 5 3 - 0,l 10 + 0

20、,2 60 T 1 50 7 0,5 12,5 3 0,l 2 T 0,2 5 z 0,l I 6,2 Number of specimens Use at least 5 specimens. 1) If the layer thickness may lead to uncertainty regarding the number of layers required to obtain material of thickness (2 +- 0,2) m, the number of layers should be stated in the relevant standard for

21、 the product. 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 PREN2562 B7 LOL23LL 0003523 3 prEN 2562 Page 6 Issue P 1 7 Apparatus 7.1 Test fixtu

22、re See figure 1. The test jig shall ensure an accurate positioning of the specimen. The misalignment between loading nose arid supports shall not exceed 0,l mm. 7.2 Micrometer fitted with 6 mm diameter flat measuring faces, accurate to within 0,Ol mm. 7.3 Test machine accurate to within 1% in the lo

23、ad range used. 7.4 Device for recording the deflection as a function of load accurate to within 1% in the deflection range used. 7.5 for tests at temperatures other than ambient. Where required, a temperature chamber controlled so as to conform to EN2744 7.6 Thermocouple and recorder for tests at te

24、mperatures other than ambient. 8 Conditioning In case of tests in the initial condition, the conditioning shall be in accordance with EN 2743. In case of tests after immersion, the conditioning shall conform to EN 2459. In case of tests after exposure to moist heat, the conditioning shall conform to

25、 EN 2823. 9 Procedure 9.1 Make 3 different measurements of the thickness and the width of the specimen to within 0,Ol mm and calculate the mean value. Measure the distance between supports to within 0,l m. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS unde

26、r license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-e a O O AECMA PREN2562 7 LOL2321 000352Li 5 prEN 2562 Page 7 Issue P 1 9.2 For tests at temperatures other than ambient, the period separating the conditioning and start of the test shall conform t

27、o the following conditions : 9.2.1 For Specimens which have not been aged or subjected to immersion the hold time at the test temperature shall be established by preliminary experiment and shall be noted in the test report. 9.2.2 For specimens subjected to immersion, follow the procedure described i

28、n EN 2489. 9.2.3 For humidity aged specimens, follow the procedure described in EN 2823. 9.3 Locate the test specimen in the test jig, with the specified face in contact with the loading nose, ensuring that its axis is perpendicular to the supports. If the face in contact with the loading nose is no

29、t specified, record its type (for instance mold side, bag side, .). 9.4 The load shall be applied at a constant rate : - - 9.5 Record the deflection f with respect to load. of 5 mm/min for specimen with span between supports 1 of 2 mm/miii for specimen with span between supports 1 of 80 mm of 50 mm.

30、 V V 9.6 Record the load at failure PR. 10 Test results The test is only considered to be representative for .the flexural properties of the material if the break is in tension or compression. Failures in a shear mode have to be excluded. Examples : c - 1 Tensile (valid) c -. Shear (not valid) - Com

31、pression (valid) I 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 PREN25b2 89 1012311 0003525 7 prEN 2562 Page 8 Issue P 1 11 Expression of resu

32、lts 11.1 Strength at failure (6 ) in ma b 6b = 3.PR. lV 2.b.h2 where : load at failure, in N R b : width, in mm h thickness, in mm lV : distance between supports, in mm. 11.2 Secant modulus at PR/2 Measure on the load/deflection record. (E ).in MPa b “4 pR . iV3 Eb = 10 . b . hS . (f2 - fi) where :

33、load at failure, in N R : b : width, in mm h thickness, in mm lV : thickness between supports, in mm fl : deflection corresponding to PR/lO, in mm E2 : deflection corresponding to PR/2, in mm. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license wit

34、h AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECMA PREN2562 89 LOL23LL 000352b_-7_j prEN 2562 Page 9 Issue P 1 12 Test report The test report s,al include the following information : 12.1 Nuinber of this standard, brand, identification mark, origin, date

35、of receipt and further data of the tested material. 12.2 Data about the preparation of the test Specimens. 12.3 Measured dimensions of the test specimens (type of specimen chosen), arid face in contact with the central loading nose. 12.4 A graph representing the load measured as a function of deflec

36、tion. 12.5 When test specimeiis have been broken in flexure (tension or compression failure) record the individual values, the arithmetic mean, the standard deviation of the flexural strength at failure 6 b 12.6 When the test specimens have not been broken in flexure (tension or compression failure)

37、, the type of failure shall be described, specifying in an appended note that the calculated stresses are according to paragraph 11.1 and are lower than the flexure strength at failure. 12.7 Record the individual values, the arithmetic mean, the standard deviation of the secant modulus at PR/2 (E ).

38、 b 12.8 Test conditions i.e. temperature and relative humidity deviating from the standard. 12.9 Period of soak at the test temperature, for tests after immersion (see EN 2489), or exposure to htinid atmosphere (see EN 2823). 12.10 Observations on any circumstances liable to influence the results. 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-,-,-