ASD-STAN PREN 2597-1990 Aerospace Series Carbon Thermosetting Resin Undirectional Laminates Tensile Test Perpendicular to the Fibre Direction (Issue P 1)《航空航天系列 碳热固性树脂不定向层压板 垂直于纤维方.pdf

《ASD-STAN PREN 2597-1990 Aerospace Series Carbon Thermosetting Resin Undirectional Laminates Tensile Test Perpendicular to the Fibre Direction (Issue P 1)《航空航天系列 碳热固性树脂不定向层压板 垂直于纤维方.pdf》由会员分享，可在线阅读，更多相关《ASD-STAN PREN 2597-1990 Aerospace Series Carbon Thermosetting Resin Undirectional Laminates Tensile Test Perpendicular to the Fibre Direction (Issue P 1)《航空航天系列 碳热固性树脂不定向层压板 垂直于纤维方.pdf（11页珍藏版）》请在麦多课文档分享上搜索。

1、CEN PRENbZ597 90 340q589 0006582 5 m Edition approved for publication A.E.C.M.A. STANDARD NORME A.E.C.M.A. A.E.C.M.A. NORM Comments should be sent within six months C7 Chairman after the date of publication decision prEN 2597 Issue P 1 October 1990 EDITE PAR LASSOCIATION EUROPEENNE DES CONSTRUCTEURS

2、 DE MATERIEL AROSPATIAL 88. boulevard Malesherbes, 75008 PARIS - TEL. 45-63-82-85 UDC : Key words : ENGLISH VERSION Aerospace series Carbon thermosetting resin unidirectional laminates Tensile test perpendicular to the fibre direction Srie arospatiale Luft- und Raumfahrt Stratifis unidirectionnels U

3、nidirektionale Kohlenstoffaser- Essai de traction Zugprfung senkrecht carbone/rsine thermodurcissable Duroplast-Verbundwerkstoffe perpendiculairement au sens des fibres zur Faserrichtung This .Aerospace Series. pre-standard has been drawn up under the responsibility of AECMA (Association Europenne d

4、es Constructeurs de Matriel Arospatial). It is published on green paper for the needs of AECMA-Members. It has been technically approved by the experts of the concerned Commission following comment by the Member countries. Subsequent to the publication of this pre-standard, the technical content sha

5、ll 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) and formal agreement of the Official Services of the Member countries it willbe submi

6、tted as a draft European Standard to CEN (European Committee for Standardization) for final vote. Mr. BEZAUD I A.E.C.M.A. I 88, Bd. Malesherbes 1990-1 0-31 75008 PARIS - FRANCE aecma 1990 COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling Services

7、I CEN PREN*2597 90 = 340Li583 0006583 7 m prEN 2597 Page 2 Content c 1 2 3 4 5 6 7 8 9 10 11 12 Scope and field of application References Principle of the method Definitions Designation of the method Test specimens App ar a tu s Conditioning Procedure Expression of results Validity Test report 8 Ann

8、ex A COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling Services1 Scope and field of application This standard specifies a tensile test method for determining the ultimate tensile strength and tensile modulus and, if required, the Poissons ratio a

9、nd elongation at rupture in tension for carbon fibre-reinforced unidirectional. laminates. This procedure is only applicable to test specimens where the direction of the fibres is perpendicular to the direction of the load applied. 2 References EN 2489 Aerospace series - Fibre reinforced plastics -

10、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 - Reinforced plastics - Standard atmospheres for conditioning and testing 2) EN 2344 Aerospace series - Non-metallic materia

11、ls - Preferred test temperatures 3) EN 2823 Aerospace series - Fibre reinforced plastics - Test method for the determination of the effect of exposure to humid atmospheres on physical and mechanical characteristics 2) 3 Principle of the method The method entails the measurement of strains in the mat

12、erial perpendicular to the axis of fibres ( E ), and, if required, parallel strains ( 6 ), in terms of the stress applied, Juring a tensile test carried out at a conLiant rate of displacement until failure occurs. The proposed test method defines two types of test specimens (type A and type B) which

13、 give significantly different results as far as means and scatter are concerned. It is mandatory to specify on what type of test specimen the result was obtained. 4 Definitions 4.1 Tensile stress at a given moment during the test Tensile load experienced by the test specimen at a particular moment d

14、uring the test, per initial unit cross sectional area within the gauge length. %22 4.2 Tensile strength at failure Tensile stress at the time of failure occurs. It is calculated using the formula given in clause 10.1, 1) Published as AECMA prestandard at the date of publication of the present standa

15、rd. 2) In preparation at the date of publication of the present standard. 3) Published as AECMA standard at the date of publication of the present standard. COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling Services:CEN PREN82597 90 m 3904589 000

16、6585 O m prEN 2597 Page 4 4.3 Strain ( E, and c22) Variation in the distance between gauge marks on the test specimen gauge length, produced by a tensile load and expressed with respect to the initial distance between gauge marks, E, is the strain measured parallel to the axis of the fibres. E is th

17、e strain measured perpendicular to the axis of the fibres (in 22 the laminate plane). *22 4.4 Percentage elongation at failure Increase in the distance between the marks on the gauge length of the test specimen, produced by a tensile load, expressed as a percentage of the initial distance between th

18、e gauge marks and measured at the moment of failure. It is calculated using the formula given in clause 10.4. 4.5 Secant modulus in tension Px/2 (ET22) Slope of the straight line passing through the point of the diagram showing stress/strain perpendicular to the fibre axis corresponding to a stress

19、calculated from P /2, and through the point on the same diagram corresponding to a stress calculated from Pg/lO, where P is the load at failure of the specimen. This modulus is calculated using the formula given in clause 10.2. 4.6 Poissons ratio Absolute value of the ratio of the variation of strai

20、n E to the variation of strain E It is calculated using the formula given in clause 10.3. B R ( $21) 22 measured between PB/10 and PB/2 (see figure 2). 1- 1 5 Designation of the method The designation of the method is as follows : Example : Description block Identity Block EN 2597 - B c Tensile test

21、 Type of test 1 Number of standard 1 Type of specimen (see annex A) COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling ServicesCEN PREN*2597 90 = 340Li589 0006586 2 _ . _ prEN 2597 Page 5 6 Test specimens The test specimens are taken from unidirectional panels prepared according to EN 2565. The bow resulting from a curvature and measured according to figure 1 shall meet the following relation : f 1 - 7 - 7 d 50 +, I. t COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling Services