AECMA PREN 7000-11-1999 Aerospace Series Non-Metallic Materials Rules for the Drafting and Presentation of Material Standards Part 11 Preimpregnates Edition P 1《航空航天系列系列 非金属材料 材料标准.pdf

《AECMA PREN 7000-11-1999 Aerospace Series Non-Metallic Materials Rules for the Drafting and Presentation of Material Standards Part 11 Preimpregnates Edition P 1《航空航天系列系列 非金属材料 材料标准.pdf》由会员分享，可在线阅读，更多相关《AECMA PREN 7000-11-1999 Aerospace Series Non-Metallic Materials Rules for the Drafting and Presentation of Material Standards Part 11 Preimpregnates Edition P 1《航空航天系列系列 非金属材料 材料标准.pdf（21页珍藏版）》请在麦多课文档分享上搜索。

1、STD-AECMA PREN 7000-lL-ENGL 1999 LO12333 0036585 T2b a A STANDARD E AECMA AECMA NOR prEN 9006-II1 Edition P I September 1999 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES (AECMA) Gulledelie 94 - B-1200 BRUXELLES - Tel. (t32) 2 775 81 10 - Fax. (+32) 2 775 81 11 ICs: ! Descriptors: EN

2、GLISH VERSION Aerospace series Non-metallic materials Rules for the drafting and presentation of material standards Pakt II 1 : Preirnpregnates Srie arospatiak Luft- und Raumfahrt Matriaux non-mtalliques Nichtmetallische Werkstoffe Rgles pour la rdaction et Ia prsentation des normes de matriaux Part

3、ie 14 : Primprgns Regeln fur die Erstellung und die Gestaltung von Werkstoffnormen Teil 41: Vorimprgnierte This “Aerospace Series“ Prestandard has been drawn up under the responsibility of AiFCMA (The European Association of Aerospace Industries). If is published on green paper for the needs of AECM

4、A-Members. It has been technically 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 fo an extent that interchangeability is affected, physically or fun

5、ctionally, without re-identification of the standard. Affer 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 draff European Standard to CEN (European Committee for Standardization) fo

6、r formal vote. Nota - Extra copies can be supplied by B.N.A.E. - Technopolis 54 - 199, rue Jean-Jacques Rousseau - 92138 ISSY-LES-MOULINEAUX CEDEX I I Edition approved for publication I Comments should be sent within six months after the date of publication to 1999-09-30 AECMA Guiledeiie 94 B-1200 B

7、RUXELLES C7 Chairman Mr Wright aecma 1991 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-,-,-STD*AECMA PREN 7000-11-ENGL 1999 W 1012311 00165Bb 962 E Page

8、 3 prEN 7000-1 I: 1999 O Introduction This standard is part of a series of non-metallic materials standards for aerospace applications. The general organisation of this series is described in EN 4385. This document is a level 2 document as defined in EN 4385. I Scope This standard specifies the rule

9、s for drafting and presentation of EN aerospace series non-metallic materials standards for fibre reinforced resin matrix preimpregnates for aerospace applications. This standard shall be used in conjunction with EN 7000-1. 2 References 2.1 Normative references This European Standard incorporates by

10、 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 amendments to or revisions of any of these publications apply to this European standa

11、rd only when incorporated in it by amendment or revision. For undated references the latest edition of the publication referred to applies. EN 7000-1 Aerospace series - Non-metallic materials - Rules for the drafting and presentation of material standards - Part 1: General rules. 2.2 Informative ref

12、erences EN 3074 EN 4385 Drawing annotation for composite structures Aerospace series - Non-metallic materials - General organisation of standardisation - Links between types of standards. 3 Definitions, symbols and abbreviations See EN 7000-1. 4 Rules for the drafting and presentation NOTE: The exam

13、ples given below are only intended to illustrate the rules, and may not correspond to real standardised EN products. Prcvious page is blank Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking pe

14、rmitted without license from IHS-,-,-STD-AECMA PREN 7000-ll-ENGL 1999 H LOL23LL 003b587 BTq Sl Page 4 prEN 7000-1 1 : 1999 4. I Title of the material standard See EN 7000-1 and annex D of this standard. The following are examples of descriptions which shall be used; these examples may be supplemente

15、d by other descriptions as required by the relevant Working Group. . 1. Type of reinforcement - glass fibre - carbon fibre - aramid fibre - hybrids 2. Form of reinforcement - unidirectional - plain weave - twillweave - satin weave (4 harness, 8 harness, etc.) 3. Type of resin matrix - epoxy - phenol

16、ic - bismalimide - polyester - polyimide - cyanate ester 4. Additional information - cure temperature - use temperature - nominal cured ply thickness - sandwich structures 4.2. Contents See EN 7000-1 and annex D of this standard. 4.3. Clause O onwards See EN 7000-1 and annex D of this standard. 4.4.

17、 General requirements See EN 7000-1 4.4.1. The characteristic numbers applicable to table 1 are given in annex A of this standard. All of the characteristics given in table 1 are mandatory and shall be completed in accordance with EN 7000-1 and annex D of this standard. Table 1 - General requirement

18、s 4.4.2. Tables 2 to 4 See EN 7000-1 and annex D of this standard. The characteristic numbers applicable to tables 2 to 4 are given in annex B of this standard. The rules for writing the ply lay-up code used to define the test laminate lay-up sequence are given in annex C of this standard. Copyright

19、 Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-STD-AECMA PREN 7000-ll-ENGL 1777 LOL23LL 00Lb588 735 Page 5 prEN 7000-1 1: 1999 Annex A (norm at ive) Table AI -

20、 Characteristic numbers applicable to Table 1 for preimpregnates: General requirements Characteristic number 1.001 1 .o02 1 .O03 1 .O04 1 .O05 1.006 1 .O07 1.008 1 .o09 1.010 1.011 1.013 I .O93 1 .o94 1 .O95 1 .O96 1.999 I .o98 Characteristic Material description Formulation Form & method of product

21、ion/nominal dimension Technical specification Grade Service temperature Visual Freedom from defects Application Storage Shelf life Processing condi tion Quality assurance Designation Packaging Identification marking Health safety and environment Notes Copyright Association Europeene des Constructeur

22、s de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Characteristic Used in table Infra-red Formulation - HPLC - GPC 2 X X X Annex B (normative) Table BI - Characteristic numbers applicable to Tables 2 to

23、 4 for preirnpregnates: Other requirements Characteristic number 3 4 - 102 103 104 Composition - resin content - fibre content - volatile content - emission of phenol X 105 Glass transition - DSC DMA I X X 106 X X - X Reactivity - tack - gel time/viscosity Rheology - resin flow 107 1 o9 Flammability

24、 - flammability - smoke density - toxic gases - heat release 110 Dimensional - thickness/ply X 112 Electromagnetic - RF measurement X 114 Water humidity absorbtion I X 301 Density - masshnit area - preimpregnate - masshnit area - reinforcement - fibre density - resin density X X X X 303 Thermomechan

25、ical - thermal expansion X 305 Tensile properties - strength - modulus - open hole X X X (continued) 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-,-,-ST

26、D-AECMA PREN 7000-IL-ENGL Ici99 U LO123LL 00Lb590 393 111 Page 7 prEN 7000-1 1 : 1999 Table BI - Characteristic numbers applicable to Tables 2 to 4 for preimpregnates: Other requirements (concluded) Characteristic number I Characteristic Used in table 12 3 4 - Tensile properties - sandwich flatwise

27、tensile in-plane shear Compressive properties - strength - modulus Flexural properties - strength - modulus Flexural properties - sandwich - bending stress Flexural shear Peel properties interlaminar shear climbing drum peel Bearing properties - strength X I 323 Notched/unnotched tensile X I 325 Not

28、chedhnnotched compression X Resistance to aeronautical fluids X Resistance to dry heat - interlaminar shear X Resistance to wet heat - interlaminar shear - in-plane shear - tensile properties - compressive properties - bearing strength Outgassing Water absorbtion - total immersion - high humidity No

29、tes X X - X - 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-,-,-Annex C (normative) C.1 Rules for defining the abbreviated code used to designate ply lay

30、-up sequence for test laminates The abbreviated code to be used to designate the ply lay-up sequence of laminate test pieces shall be generated by the following rules: NOTE: the abbreviated code used to designate the ply lay-up sequence of composite components is defined in EN 3074 - “Drawing annota

31、tion for composite structures“. a) The constituent plies shall be listed in sequence (left to right) starting from the chosen reference side, and the full listing enclosed in square brackets. e.g. + 45/- 451 b) Each unidirectional (tape) ply shall be represented by a number showing the orientation,

32、in degrees, of the fibre direction with respect to the selected reference axis of the multi-ply test laminate. When the f or the 7 symbols are used with unidirectional plies, two adjacent plies are indicated, with the top sign being the first of the two. e.g. fibre axis + 45“ P * fibre axis - 45“ c)

33、 For a fabric ply, both angles subtended by the warp and the weft axes shall be indicated, and separated by a comma. However, for a fabric ply at an angle of 45“, it is normal practice to shorten to a single angle code preceded by a f or a T symbol, the top sign being the first of the two. e.g. (+ 4

34、5,- 45) or (f 45) d) Fibre orientation angles shall be denoted as positive when measured in an anticlockwise direction from the reference axis as viewed from the reference side of the laminate. Angles between O“ and 90“ only shall be used, with a negative sign (together with the acute angle) being u

35、sed to indicate any obtuse angles. For all single plies at positive angles, the positive sign is normally omitted, but all negative signs shall be included. e.g. 45/- 451 e) Fabric plies shall be differentiated from unidirectional plies by inserting their ply codes in round brackets. e.g. 45/- 451 -

36、 unidirectional plies (I 45) - fabric plies 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-,-,-STD-AECMA PREN 7000-1L-ENGL 1999 1012311 00Lb592 Lbb Page9

37、prEN 7000-1 I : 1999 f) Adjacent plies of differing orientation shall be separated by a slash. e.g. 45/- 451 or (k 45)/(0,90) g) Adjacent plies of the same orientation shall be indicated in abbreviated form by attaching a numerical subscript to the ply angle to denote their number. h) Specific seque

38、nces of plies which are repeated within the laminate are termed “sets”. Adjacent sets shall be indicated in abbreviated form by enclosing in square brackets and attaching a numerical subscript to denote the number of sets. A set shall be coded in accordance with the same rules that apply to a single

39、 Ply. e.g. II(+ 4)/(0,90)141 NOTE: Square brackets are also used in rule a), but this double use is unlikely to result in any misinterpretation. i) A subscript “s” following the definition of a laminate having an even number of plies indicates that the code for only one half of the laminate is shown

40、, the other half being its mirror image. When the IS subscript is used for laminates having an odd number of plies, the centre ply shall be overlined, and the remaining laminate construction mirrored around this centre ply. e.g. (? 45)2/(0,90)s or (I 45)2/(0,90)s j) A subscript IR” (for “Reversed”)

41、following the definition of a ply within a laminate indicates that the reference face of that ply (the reference face is that face of an assymetric ply in which the warp fibres predominate) is further away from the laminate reference side than the non-reference face. When the reference face of the p

42、ly is closer to the laminate reference side than the non-reference face, then a subscript is not required. e.g. (I 45)/(+ 45)R/(0,90)s Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitt

43、ed without license from IHS-,-,-STD*AECMA PREM 7000-11-ENGL 2999 m LO123LL 00Lb593 OT2 Page 10 prEN 7000-1 I: 1999 C.2 Typical examples of the use of the abbreviated code EXAMPLE 1 : Five ply tape laminate. 0*/90/tr II EXAMPLE 2: Seven ply fabric laminate Fabric ply (0,90) Fabric ply Fabric ply Fabr

44、ic ply (0,90) Fabric ply (- 45, + 45) centre line Fabric ply Fabric ply (90,O) (+ 45, - 45) (+ 45, - 45) (- 45, + 45) EXAMPLE 3: Ten ply mixed tape/fabric laminate O/* 45/(k 45)/90, Tape ply O Tapeply +45 Tape ply -45 Fabric ply Tapeply 90 Tape ply 90 centre line Fabric ply Tape ply -45 Tape ply +45

45、 Tape ply O + 45, - 45 - 45, + 45 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-,-,-Annex D (informative) Example EN xxxx June 1999 AECMA C7MIG5 Aerospac

46、e series Non-metallic materials Glass fibre thermosetting preimpregnate 4 harness satin weave E glass/ adhesive epoxy resin preimpregnate Cured at up to 125C for continuous use at up to 80C Nominal cured ply thickness 0,125 mm Srie arospatiale French titie Luft- und Raumfahrt German title (continued

47、) 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-,-,-STD-AECMA PREM 7000-LL-ENGL 1997 1111 LOL23LL 00Lb595 775 N Page 12 prEN 7000-1 1 : 1 999 Example (co

48、ntinued) Page 2 EN xxxx Blank page (continued) 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 13 prEN 7000-1 1 : I999 STD-AECMA PREN 70aO-LL-ENGL

49、 1979 3032333 0036596 BOL Example (continued) Page 3 EN xxxx O Introduction This standard is part of the series of non-metallic materials standards for aerospace applications. The general organisation of this series is described in EN 4385. This standard is a level 3 document as defined in EN 4385. It has been prepared in accordance w