1、A.E.C.M .A. STAN DARD NORM E A. E.C. M .A. A.E.C.M.A. NORM Edition approved for publication 1992-04-30 prEN 3783 Issue P 1 April 1992 Comments should be sent within six months C7 Chairman after the date of publication decision Tecliriopolic - 175. rue Jeaii-Jacques Rousseau 92 1 38 Issy-lec-Moulinea
2、ux Cdex - FRANCE A.E.C M A. M. BEZAUD EDITE PAR LASSOCIATION EUROPENNE DES CONSTRUCTEURS DE MATRIEL AEROSPATIAL Technopolis - 175, rue Jean-Jacques Rousseau - F-92138 Issy-les-Moulineaux Cdex -T I) 47 36 98.76 UDC : Key words ENGLISH VERCION Aerospace series Fibre composite materiais Normalisation o
3、f fibre dominated mechanical properties Srie arospatiale Luft- und Raumfahrt Matriaux composites base de fibres Standardisation des caractristiques Faserverbundwerkstoffe Norm fe rung von fa sera b h ng i g en mech an i sch eil mcaniques lies aux fibres Eigenschaften This Aerospace Series. preistand
4、ard 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 approved by the experts of the concerned Commission following comment by the Member countrie
5、s. 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 standard. After examination and signature of the AECMA Standard Checking Centre (NPS) and f
6、ormal 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. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for
7、 ResaleNo reproduction or networking permitted without license from IHS-,-,-I CEN *PREN*3783 72 3404587 0025823 8 B prEN 3783 Page 2 Contents Scope and field of application References Principie Designation Procedure Test report Copyright Association Europeene des Constructeurs de Materiel Aerospatia
8、l Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-F-c?_ 2 - - - ,- CEN *PREN*3783 92 H 3404589 0025824 T H prEN 3783 Page 3 Description block Nor mal sa ti on of D rooe rtiec 1 Scope and field of application Identity block EN
9、 3 7 8 3 B, This standard describes the procedure for normalisation of fibre dominated mechanical properties. The procedure is valid for carbon, glass and aramid reinforced laminates. 2 References EN 2329 Aerospace series - Textile glass fibre preimpregnates - Test method for the determination of ma
10、ss per unit area Aerospace series - Carbon fibre preimpregnates - Test method for the determination of mass Der unit area i) EN 2557 EN 2564 Aerospace series - Carbon fibre laminates - Test method for the determination of the fibre and resin fractions and porosity content i) 3 Principle When present
11、ing mechanical data in which the characteristic is mostly dependent upon the fibre, it is usual to adjust the result to a specific fibre volume. The method consists of the measurement or calculation of the fibre content by volume of the test laminates or specimens. This fibre content is then used to
12、 adjust the results of mechanical tests which depend, in a linear relationship, upon the fibre volume content. The results are corrected to a predefined nominal content using the rule of mixtures. 1) Published as AECMA pre-standard at the date of publication of the present standard. Copyright Associ
13、ation Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CEN *PREN*3783 92 I 3404589 0025825 L E prEN 3783 Page 4 5 Procedure 5.1 Fibre volume content (Vf) determination 5.1.1
14、Method A (carbon fibre composite only) The fibre content (V,) in % on the te5t laminare is measur-ed by digestion of representative specimens cut from the same laminate as that used fur the mechanical tests to be adjusted. The method to be used is that defined in Et; 2554 The averaye fibre veiume ob
15、tained for the lamicate is the esiult to be used for correction (see 5 2) 5.1.2 Method B and C MeasrJre the thickness (ti) in mrn of he rest I3minate 2s 3:) average of 10 :Jniforrnly spaced wadifigs using a 6 mm to 8 rnm diameter flat faced micrcmeter. If :his thickr:esc is divided by the niJrnber o
16、f plies Used for the !aminate, the measured cuit? aiy thickness in mni is ohrained Itti!. 5.1.2.1 Method B Using the product declared nomiriai cured sly thickness :ifi; 2s defined ir iiie material specification, lhe fibre volume (Vf) in o/ for the laminate is clcciiare4 cisir;g ?!le equatiov 5.1.2.2
17、 Method C Because of accepted tolerances in prepre2 fibre :.nass !,er uni: area 2 certain ii1accGracy in fibre VOIUE estimation will recuit when using method abcve. This variable can be eliminated by iising tue fibre weight measured on the prepreg sample before !aminatiiig. Measure the fibre mass pe
18、r unit area vlf) in g/mZ of a cIiitably representative sample of prepreg according to EN 2329 or EN 2557 (as appropriare). The theoretical cured ply thickness it21 in mm can now be calculated by the equation ; Where Vn is as defined in 5.1.2.1 above and pf is the average fibre density (in g/cm3) of
19、the batch (or batches) used for the material in question. 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-,-,-CEN *PREN*3783 92 3404589 0025826 3 - prEN 37
20、83-Page 5 The laminate fibre volume content is calculated by the equation ; t2 Vf = - Vn tP or Mx IO- Vf = Pf . fp Note : methods B and C require that no fibres be displaced in the laminatino process owing to lateral movement of fibres during consolidation. 5.2 Correction of results The characterist
21、ics which are to be corrected to a nominal fibre content shall be defined in the material specification. These characteristics shall be those which are dominated by the reinforcement (such as tensile, flexural or compression strength and modulus). Unless stated in the technical specification, the pr
22、oportion of fibres (which dominates the property) shall be greater than 20 % in the test direction. Where specified, each result is to be corrected by multiplying the value by the factor k : Where V, in % is the nominal fibre volume as defined in the material specification. This correction is only v
23、alid for fibre volumes close to the nominal, that is to say, according to the following requirement : Unless otherwise stated in the material specification, the value of Vf obtained by method B is to be used. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS u
24、nder license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ICEN *PREN*3783 92 3404589 0025827 5 E prEN 3783 Page 6 6 Test report The test report shall contain the information required by the appropriate test method. In addition, the following informatio
25、n shall also be included. 6,l 6.2 6.3 6.4 Individual and mean corrected results The method used (A, B or Cl The laminate fibre volume (Vf) The nominal fibre volume (V,) to which the results have been normalised. 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-,-,-
