AECMA PREN 2243-3-2001 Aerospace Series Non-Metallic Materials Structural Adhesives Test Method Part 3 Peeling Test Metal-Honeycomb Core Edition P 1《航空航天系列非金属物质结构用粘结剂.第3部分 剥离试验用金属-.pdf

《AECMA PREN 2243-3-2001 Aerospace Series Non-Metallic Materials Structural Adhesives Test Method Part 3 Peeling Test Metal-Honeycomb Core Edition P 1《航空航天系列非金属物质结构用粘结剂.第3部分 剥离试验用金属-.pdf》由会员分享，可在线阅读，更多相关《AECMA PREN 2243-3-2001 Aerospace Series Non-Metallic Materials Structural Adhesives Test Method Part 3 Peeling Test Metal-Honeycomb Core Edition P 1《航空航天系列非金属物质结构用粘结剂.第3部分 剥离试验用金属-.pdf（10页珍藏版）》请在麦多课文档分享上搜索。

1、 AECMA STANDARD NORME AECMA AECMA NORM Edition approved for publication prEN 2243-3 Edition P I December 2001 Comments should be sent within six months after the date of publication to Material Domain PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES - STANDARDIZATION (AECMA-STAN) Gulled

2、elle 94 - 8-1200 BRUXELLES - Tel. (+32) 2 775 81 10 - Fax. (+32) 2 775 81 11 ICs: Will supersede EN 2243-3: 1991 Descriptors: ENGLISH VERSION Aerospace series Non-metallic materials Structural adhesives Test method Part 3: Peeling test metal-honeycomb core Srie arospatiale Matriaux non-mtalliques Sy

3、stme dadhsifs structuraux Mthodes dessai Partie 3 : Essai de pelage mtal-nid dabeilles Luft- und Raumfahrt Nichtmetallische Werkstoffe Strukturelle Klebstoffsysteme Prfverfahren Teil 3: Trommelschlversuch fr Waben kernverbunde This !Aerospace Series“ Prestandard has been drawn up under the responsib

4、ility of AECMA-STAN (The European Association of Aerospace Industries - Standardization). It is published on green paper for the needs of the European Aerospace Industry. It has been technically approved by the experts of the concerned Domain following member comments. Subsequent to the publication

5、of this Prestandard, 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 review by users and formal agreement of AECMA-STAN it will be submifted as a draft European S

6、tandard to CEN (European Committee for Standardization) for formal vote. 2001 -1 2-28 AECMA-STAN Gulledelle 94 B-1200 BRUXELLES Mr Pays I l aecma 2001 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or ne

7、tworking permitted without license from IHS-,-,-Page 2 prEN 2243-3: 2001 Contents Page O I 2 3 3.1 3.2 4 5 6 6.1 6.2 6.3 7 7.1 7.2 7.3 7.4 7.5 7.6 7.7 8 8.1 8.2 8.3 8.4 8.5 9 10 11 . . . Scope . Normative references . . PrincipleiTechnique . Reso u rces . . Apparatus . MaterialclReagents . Qualifica

8、tion of personnel . . Test samplesflest pieces . . Surface preparation before bonding Bonding Cutting of panels and preparation of test pieces . . Dimensions measurement . Determination of rolling load . Expression of results . Test report . 3 3 3 3 3 3 4 4 4 4 4 4 4 4 5 5 5 5 5 5 5 5 6 6 6 6 6 7 7

9、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 3 prEN 2243-3: 2001 I O Introduction This standard is part of the series of EN non-metallic materi

10、al 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. I Scope This standard defines the general requirements for the determination of strength of structural adhesives by testing in peel met

11、al to honeycomb core joints, at ambient or other temperatures. 2 Normative references This European Standard incorporates by dated or undated reference, provisions from other publications. These normative references are cited at the appropriate places in the next and the publications are listed here

12、after. For dated references, subsequent amendments to or revisions of any of these publications apply to this European Standard only when incorporated in it by amendment or revision. For undated references the latest edition of the publication referred to applies. IS0 7500-1 Metallic materials - Ver

13、ification of static uniaxial testing machines - Part 1: Tensionkompression testing machines - Verification and calibration of the force-measuring system Aerospace series -Aluminium alloy AL-P2024- - T3 - Clad sheet and strip - 0,3 mm I a I 6 mm 1) Aerospace series - Chromic-sulphuric acid pickle of

14、aluminium and aluminium alloys Aerospace series - Non-metallic materials - General organisation of standardisation - Links between types of standards 1) Aerospace series - Aluminium honeycomb core 2) EN 2090 EN 2334 EN 4385 EN 4606 3 Definitions, symbols and abbreviations 3.1 Definit ions Not applic

15、able 3.2 Symbols and abbreviations For the purposes of this standard, the following symbols and abbreviations apply: F Peeling load (in newtons); F, FI W T Rolling load (in newtons) = Load necessary to roll up the skin; Peeling and rolling load (in newtons); Width of test piece (in centimeter); Peel

16、ing strength (in newtons. centimeterkentimeter). 1) Published as AECMA Prestandard at the date of publication of this standard 2) In preparation at the date of publication of this standard Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AE

17、CMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 4 prEN 2243-3: 2001 4 Health and safety This standard does not necessarily include all health and safety requirements, associated with its use. Persons using this standard shall be familiar with normal laborat

18、oryltest house practices. It is the responsibility of the user to establish satisfactory health and safety practices and to ensure conformity with any European, national or local lawslregulations. 5 Princip I eTec h n iq ue Not applicable 6 Resources 6. I Apparatus All test equipment shall be calibr

19、ated at intervals not exceeding 12 months. 6.1 .I Tensile testing machine The tensile testing machine shall conform to class 1 of IS0 7500-1. The failing load of the test specimen shall be within 1 O % and 90 % of the upper limit of the selected loading range of the machine. 6.1.2 Fixing The peeling

20、 jig consists of a drum with lateral flanges, flexible load strips or cords and suitable clamps for fastening the test pieces in. The arrangement shown in figure 1 has proved efficient. The drum radius is 50 mm. The radii of the flanges including half the thickness of the flexible load strips or cor

21、ds are 12,5 mm larger than the drum radius. The top clamp, for introducing the load into the test piece, and the clamp on the drum shall be disposed so that the covering layers are tangential to the drum surface in the beginning of test as shown in figure 1. The drum shall be counter-balanced by fix

22、ing a mass on the drum opposite the clamp. The maximum mass of the peeling jig shall not exceed 3,5 kg. 6.1.3 Recorder It shall record continuously the displacement (see figure 3) relative to the load applied throughout the test until total failure occurs. 6.2 Not applicable Mat er i alslcieag e n t

23、s 6.3 Qualification of personnel Not applicable 7 Test samples/Test pieces 7.1 Materials Aluminium alloy EN 2090 Honeycomb core: see EN 4606. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking

24、permitted without license from IHS-,-,-Page 5 prEN 2243-3: 2001 7.2 EN 2334 unless otherwise specified. SI rface preparation before bonding 7.3 Bonding The application and curing of the adhesive system (adhesive and primer) shall be carried out according to the material standard unless otherwise agr

25、eed with the adhesive system manufacturer. 7.4 Dimensions of panels The test panel shall be of sufficient size to permit the manufacture of at least one test piece (see figure 2). 7.5 They shall be stored under the following conditions: Storage of test panels after bonding - temperature : (2312) OC;

26、 - relative humidity ; (50 i 5) %. 7.6 The panels shall be cut into test pieces (see figure 2). The panels made with high temperature curing adhesives shall be cut only after a storage period of 16 hours (see note 1). For batch acceptance testing, this 16 hours period can be omitted. Nevertheless, f

27、or temperature Cutting of panels and preparation of test pieces NOTE 1 curing adhesive, care shall be taken to cut panels only when their temperature is down to ambient. Perform the cutting operation so as to avoid overheating ( 50 OC) or mechanical damage to the joint (see note 2). NOTE 2 A fine-to

28、oth, circular or band saw has been found suitable for this purpose. Cutting shall be straight and parallel. The use of cooling liquids is not permitted, unless otherwise specified. 7.7 Test pieces 7.7.1 Dimensions See figure 2. 7.7.2 Number of specimens See material standard. 7.7.3 Identification Ea

29、ch test piece shall be marked to identify the panel from which it was cut and its position in the panel. Ensure top skin is labelled for traceability. 8 Testi ng procedure 8.1 Dimensions measurement Measure the width w of test piece with an accuracy off 0,l mm. Copyright Association Europeene des Co

30、nstructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 6 prEN 2243-3: 2001 8.2 Fixing See figure 1. The test piece shall be carefully fixed to the drum as shown in figure 1. The other end of

31、the test piece shall be fixed on the top of the test machine using the top clamp. When the test piece with the peeling jig is suspended on the top grid of the test machine, fastened by means of a bolt through the clamp, the test machine indicator shall be set at O and the yoke of the peeling jig sha

32、ll be fastened by means of a bolt to a fitting in the bottom grip of the machine. 8.3 Test temperatures When the test temperature is different from ambient temperature (23 rt 2) OC, then the chamber including jig shall be stabilised within the test temperature tolerance for at least 30 minutes prior

33、 to inserting the test piece. The temperature control of the test piece shall be carried out using a thermocouple. The junction of the thermocouple shall be firmly attached to the test piece in immediate contact with the metal. It shall be shielded from direct heating. 8.4 Loading For test temperatu

34、re different from ambient, and unless otherwise specified, a minimum exposure time of 10 minutes at the required temperature shall be applied prior to loading. For non-ambient temperature tests, there is a requirement for the test portion of the specimen to be NOTE within the specified temperature t

35、olerance throughout the period of loading to failure. The exposure time of 1 O minutes is normally sufficient to fulfil this requirement. Nevertheless, the test laboratory may be required to prove the heat dwell concept (procedure and conditions) by means of temperature/time records on dummy specime

36、n(s) incorporating thermocouple(s) embedded in drilled hole(s) within the test portion of the specimen. These records shall be made available to demonstrate the validity of the heat dwell conditions. In this case, for tests under non-ambient conditions, the specimen shall be placed in the grips of t

37、he test machine and the temperature monitored according to the heat dwell concept previously established. When it reaches the lower (or upper, for temperature below ambient) limit of the test temperature tolerance, allow the specimen to dwell within the tolerance band for a minimum of 3 minutes prio

38、r to loading. The test shall be completed within a maximum dwell of 1 O minutes. The heat-upldwell cycle used shall be given in the test report. The load shall be applied at a uniform jaws separation of 25 mm/min. A minimum length of 150 mm shall be peeled. Record the load-displacement curve. 8.5 De

39、termination of rolling load Rolling load Fo is determined by fixing an unbonded facing sheet as described in 6.3.2, in the peeling jig and test machine, and applying a traction load to roll it up. The load used shall be recorded during the rolling operation and shall remain approximately constant. 9

40、 Expression of results The peeling diagram shall be evaluated as follows: The average peeling and rolling load FI shall be determined over a peeling length of 125 mm, by inserting the estimated average value into the diagram as shown in figure 3. The results of the first 25 mm of the peel separation

41、 on the specimen as shown on the peeling diagram after the first maximum load are to be excluded from the assessment of the average value. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking per

42、mitted without license from IHS-,-,-Page 7 prEN 2243-3: 2001 Description block PEEL STRENGTH In case of doubt, the average peeling load shall be determined by means of a planimeter. The value of peeling load F is calculated by the following equation: F = Fj - Fo Identity block The peeling strength s

43、hall be expressed as follows: F r=- W 10 Designation EXAMPLE: Number of this standard I1 Test report The test report shall include: - reference to the test method designation; - the type of tensile testing machine, the speed of loading, the exposure conditions and test temperature; - complete identi

44、fication of the adhesive system, including the type, manufacturer, date of manufacture, batch number, material standard or specification number; - complete identification of the metal and honeycomb core used; - detailed information about the surface preparation before bonding; - application and bond

45、ing conditions including the bonding method (press, autoclave, .), pressure on the adhesive joint, heat-up rate, curing time and temperature; - information about individual test piece including traceability from panel, actual dimensions, sheet thickness and bond line thickness; - type of recorder; -

46、 expression of individual results, including peel load, nature and location of failure with estimated percentage of failure in cohesion and/or adhesion in adhesive or primer; - associated diagram; - in case of multiple tests: - number of test pieces; - average, standard deviation, maximum and minimu

47、m values of the test series. - traceability to personnel performing the test work; - any incident which may have affected the result; - any deviation from this standard described in detail; - date of test. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS unde

48、r license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 8 prEN 2243-3: 2001 Dimensions in millimetres c r -E I t- c 75 3 I- Key 1 Topclamp 2 Drum 3 Countermass 4 Flange 5 Clamp 6 Yoke 7 Load strips i Figure 1 - Peeling jig Copyright Association Eur

49、opeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 9 prEN 2243-3: 2001 - /* / - - - 1 Axis of honeycomb 2 Unprotected core 3 Material, see EN 2090 Material, see EN Cell size 6,4 Foil thickness: 0,08 or Oll 3 1 P 75 f 0,5 Dimensions in millimetres op 212 4606 Figure 2 -Test piece Copyrigh