1、AECMA STANDARD NORME AECMA AECMA NORM prEN 3074 Edition P 2 August 2003 ICs: Descriptors: ENGLISH VERSION Aerospace series Drawing annotation for composite laminate structure Supersedes issue P 1 February 1991 Srie arospatiale Indications a porter sur les dessins pour les lments composites obtenus p
2、ar drapage Luft- und Raumfahrt Zeichnungsangaben fr Verbundwerkstoff-Laminatstrukturen following member comments. content shall not be changed to an extent that interchangeabill tionally, without re-identification of the standard. CEN national members have then to implement the standards con Replace
3、 page 1 of the previous issue by this page Wlthdrawal approved I Comments should be sent within six months I Engineering Procedures Domain 31 August 2003 after the date of publication to Gulledelle 94 AECMA-STAN B-I 200 BRUXELLES Copytight 2003 O by AECMA-STAb Copyright Association Europeene des Con
4、structeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ICEN PREN*3074 93 3404589 O033670 4 1 prEN 3074 page 2 Contents Scope and field of application ._ Terminology Drawing annot at ion Annex A Cop
5、yright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-a a CEN PREN*307Li 71 3YOLi589 0013671 b W prEN 3074 page 3 1.0 SCOPE AMI FIR-O OF APPLICATION The purpose
6、 of this standard is to specify the drawing annotation for composite laminate structure, intended for aerospace construction. 2.0 TERMINOLOGY BALANCEO PLIES The same quantity and orientation of plies equally distributed about the neutral axis. BROAOGOOOS Unidirectional fibre pre-preg as supplied in
7、various widths greater than 300mm wide (commonly 1.2m wide). CO-BONO A method of creating assemblies whereby uncured components are simultaneously cured and bonded with an adhesive to previously cured components in a single operation. CO-CURE A method of creating assemblies whereby components are cu
8、red together with, orwithout, an adhesive in a single opera tion. COMPOSITE COMPONENT an assembly. A cullection of cured plies forming a part, or part of L AMINATE Two or more plies cured together. LAY-UP The operations carried out in laying the plies in sequence on the tool face. LAY-UP DATUM LAY-U
9、P DIAGRAM A diagram showing the direction of the fibres. A table showing the design requirements relative to the operation number, ply identification, orientation, lay-up sequence and stagger index. LAY-UP SEQUENCE the tool face. The order of lay-up of each ply commencing at NEUTRAL AXIS (NA) is a l
10、ine through the centre of thickness of a component and hence may not be straight. NOMINAL LAMINATE THICKNESS boundary. The nominal laminate thickness quoted by the suppliers multiplied by the number of plies within a given OPERATION No An operation number is given to the lay-up of one thickness of f
11、ibre. The numbers are sequential from the tool face. There may be several pfies in a single operation. The same ply can be used for several different operation numbers. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo
12、reproduction or networking permitted without license from IHS-,-,-CEN PLY PLY OROPOFF PLY ORIENTATION PLY PART No. PLY STAGGER START POINT PLY STAGGER INDEX PREDICTED LAMINATE THICKNESS P R E- PR EG SYMMETRY TAPE TOOL FACE UNBALANCE0 PLIES I PREN*3074 93 m 3404589 O033672 8 m I prEN 3074 page 4 One
13、thickness of composite material of required peripheral shape. This is the termination of a ply, where it is necessary to change the thickness of a component. The angular direction in which the fibres are to lie according to the lay-up datum. These angles are given in the lay-up table. Identification
14、 number allocated to a ply. The origin point from which tape or broad goods edges commence. The position of a tape or broad goods edge within a ply profile relative to the ply stagger start point. Le. The amount by which the position of the ply edge is offset to avoid coincident joints occuring thro
15、ughout the laminate thickness. See fig 2. Predicted thickness of a component after curing, taking into account the effects of consolidation, material type, bleed, etc. This includes any fibreglass layers, metallisation etc present in the lay-up. Composite ma ter ia 1 fibres p re-impregnated with res
16、in. In order to prevent distortion of the component during the cure cycle, it is necessary that the orientation of the plies are mirrored about the neutral axis of each component (Le. balanced lay-up). Composite fibre pre-preg as purchased in various widths with the fibres arranged unidirectionally
17、along the rolled out length. The surface against which the plies are subsequently cured. Oifferen t quantities of 00/900/450/1350 plies distributed unequally each side of the neutral axis. UNIDIRECTIONAL Characteristic direction of a tape corresponding (U.0.) to the direction of the fibres. WARP Lon
18、gitudinally orientated yarn in a woven fabric. WEFT WOVEN FABRIC Direction at right angles to the warp. Woven composite fibre material (pre-preg) yarns normally supplied on a reel in one continuous lengt,. - Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS un
19、der license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CEN PREN*3074 91 m 3404589 0033673 T m prEN 3074 page 5 3.0 DRAWING ANNOTATION O 3.1 Plies 3.1.1 Number of Plies Number of plies, which is the number of plies in each individual thickness area, s
20、hall be stated on the drawing in the lay-up diagram. 3.1.2 Ply thickness Ply thickness, which is the nominal thickness of one ply after curing, shall be stated on the drawing, or in the part list, or in the lay-up diagram. 3.1.3 Ply identification O Each ply shall be identified on the drawing and in
21、 the lay-up diagram by means of a 3 digit number and could be prefixed with the letter P, see fig 3. This number is for ply identification only and should not be confused as being a part number. Where a ply is made up of portions only one identity number shall be used. The ply identity shall be show
22、n on the drawing as below (with arrows or points), / 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-,-,-iCE.N PREN83074 91 W 3404589 0013b74 L PEN 3074 pa
23、ge 6 3.1.4 Handed Plies Opposite handed single plies shall carry the same ply number as the as drawn ply. Component profile (type) / As drawn I O“ 45* Opposite hand 3.1.5 Position of ply on component Position of ply on component shall be stated on the drawing or in the lay-up diagram. Examples are s
24、hown in annex A. 3.1.6 Ply Data Each ply in an operation shall be defined and shall consist of:- * the ply periphery * fibre orientation * ply stagger datum * ply identity * tooling information if common (e.g. lugs/holes) - *- - Copyright Association Europeene des Constructeurs de Materiel Aerospati
25、al Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CEN PREN*3074 73 = 3404587 O033675 3 prEN 3074 page 7 tn 3.1.7 Laminate thickness Laminate thickness shall be stated on the drawing for each different thickness as follows: t
26、 P Where: tn = Total Nominal Thickness tP = Total Predicted Thickness - note t,., value includes all structural and non-structural layers including metallisation, glass layers, etc. (not mandatory). W = Nominal Thickness 00 plies Nominal thickness = X = Nominal Thickness 90 Plies sum of all plies Y
27、= Nominal Thickness 45O Plies in actual direction Z = Nominal Thickness 135O Plies i or W = Number of Oo plies Number of plies = X = Number of 90 plies sum of all plies in Y = Number of 45O plies actual direction. Z = Number of 135O plies i 3.2 Orientation of Warp or Fibres The direction of fibres s
28、hall be stated as symbol on the drawing and the value shall be given in the lay-up diagram for each ply. Symbol on drawing:- 135“ “ - The symbol may be rotated to suit the drawing presentation but is drawn by convention anti-clockwise for the AS-ORAWN component, -* Copyright Association Europeene de
29、s Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I CEN PREN*3074 91 3404589 0033676 5 3.3 3.4 3.5 3.G 3.7 3.n prEN 3074 page 8 Operation Number Each applied ply shall be given an operati
30、on number, in sequence from the tool face. Where several (island) plies occur at the same level in the lay-up, they shall be included in thesame operation number. Tool Face The tool face shall be indicated in the lay-up diagram and/or on the drawing. Stagger Index Where the width of the ply is less
31、thai the width of the component then lengths of tape/broadgoods shall be laid alongside each other to form a complete layer. In order that the joints do not coincide with joints in other layers of the same orientation, it is necessary to indicate the required values of stagger. Stagger is the amount
32、 of displacement of the plies in one layer relative to any other layer of the same orientation. An indication of the start point and the direction shall be indicated on the drawing. (Fig i), The index of the stagger shall be indicated on the drawing and in the lay-up diagram. Ma terial Material (Fab
33、ric or tape) shall be stated on the drawing, or in the parts list or in another similar document (specification), which is referenced on the drawing or parts list. Cay-up diagram The diagram shall consist of the essential information stated in each of these paragraphs. At least orientation of warp o
34、r fibres, ply identification and lay-up order/sequence shall be stated. Examples are shown in annex A where method shown on pages 1 and 3 are most suitable for components with many thickness variations (e.g. large wing skin panels) and method shown on page 5 is more suitable to components with few t
35、hickness variations. Additional Drawing annotation Following shall be noted on drawing or instruction sheet: Fillet Radius Fastener Hole prepara tion Neutral axis if convenient Protection Treatment Structural Classifica tion Tolerances Inspec tion Requirements Part Ident if ica tion Copyright Associ
36、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 PRENr3074 91 3404589 0013b77 7 - prEN 3074 page 9 FIG 1 O Example to explain stagger index (not for use on drawing
37、face) Start point O Stagger dimension x(see fig 2) Stagger dimension 2x (see fig 2) FIG 2 Indication of stagger symbol on drawing - -5 543210 STAGGER INDEX Scale to be noted Directions of the stagger is square angle to the fibre direction Copyright Association Europeene des Constructeurs de Materiel
38、 Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-ICEN PREN*3074 91 3404589 0013b78 9 W i prEN 3074 page 10 e PO25 / BROADGOODS JOINT PLY PORTIONS NOT IDENTIFIED INDIVIDUALLY FIG 3 TYPICAL PLY .r- -. .- - - O ,- I
39、i I 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-,-,-CEN PREN*3074 71 m 3404587 0013679 O m , - _ Lay-up diagram Example 1 Annex A page 1 to prEN 3074
40、 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-,-,-I l !CEN PREN83074 91 m 3404589 0013b80 7 m Annex A page 2 to prEN 3074 NOTES REGARDING NUMBERS WITHIN
41、 CIRCLES in example 1 Operation Number - Ply Identification No. - CAO Level - Ply Material - Orientation - Stagger Index - Area Code - Number of Plies - Ply Presence - In sequence from tool face. Include all plies that can be laid up together within one operation. Quote ply identification no/s e.g.
42、PO38 to be laid up within operation number quoted above. The level on which ply profile is to be found within CAO drawing file. To be quoted e.g. as a flag note symbol. Quote angle at which ply is to be laid up relative to lay-up datum e.g. Oo, 90, 45O or 1350. Quote position relative to the stagger
43、 start point at which the ply is laid. Quote alpha character identities (e.g. A, or AF etc). Avoid the use of letters I and O. Insert total number of plies present within each area/island. . Sub-totals relating to ply orientations are not required. Indicate the presence of a ply by a thick horizonta
44、l line across the centre of each area at the appropriate operation number. i- “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-,-,-CEN PREN*3074 41 34045
45、89 0013681 9 Lay-up diagram Annex A page 3 to prEN 3074 Example 2 page l(2) e Theoretical thickness c Y a W n oc O z 0 z OR I E NTATI O N SYMBOLS AREAS o a) .- -i% LI- o, 1 o, 1 O, 2 o, 1 O, 3 s20 s21 / / 11 /# / 22 11 21 1 14 166 - 30 -30 30 30 - - - 13 12 - 161 156 &$ FABRIC Il 10 9 - - 151 146 14
46、1 - -4 5 90 O O 90 45 -4 5 - - - - - o, 4 8 7 - 136 131 - 6 126 5 121 4 3 2 1 - - - 11 6 11 1 106 - - 45 0,3 I - 35 35 - +- 101 O, 3 - NUMBEF OF :ABRICS O, 4 o, 1 e= - IUMBER IF TAPES (1) THE ORDER IN WHICH THE LAYERS ARE ARRANGER IS COUNTED FROM THE DATUM FACE. O Copyright Association Europeene des
47、 Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,- CEN PREN*3074 91 W 3i.104589 O033682 O - Annex A page 4 to prEN 3074 Lay-up diagram Example 2 page 2 Drawing presentation Co 0 z t- U W v
48、, I I I I I I I I I I I , !G I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I . I I I a I I I G! I I I I I I I I I I O O cn O L* I I I I I I I I I , t I l w o 2 E x I- Q Q c m I I I I I I I I * I I i - I I I l I I I I I I I -_- I I I I I I I I I I I .J * I I 1 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-,-,-CEN PREN83074 91 W 340458
