1、AECMA STANDARD prEN 2243-4 NORME AECMA Edition P 1 AECMA NORM December 2001 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES - STANDARDIZATION (AECMA-STAN) Gulledelle 94 - 8-1200 BRUXELLES - Tel. (+32) 2 775 81 10 - Fax. (+32) 2 775 81 11 Will supersede EN 2243-4: 1991 Edition approved
2、for publication 2001-12-28 ICs: Descriptors: Comments should be sent within six months after the date of publication to AECMA-STAN Mr Pays Gulledelle 94 Material Domain B-1200 BRUXELLES ENGLISH VERSION Aerospace series Non-metallic materials Structural ad hesives Test method Part 4: Metal-honeycomb
3、core flatwise tensile test Srie arospatiale Matriaux non-mtalliques Mthodes dessai Partie 4 : Essai de traction perpendiculair pour mtal-nid dabeilles Systme dadhsifs structuraux Luft- und Raumfahrt Nichtmetallische Werkstoffe Strukturelle Klebstoffsysteme Prfverfahren Teil 4: Zugversuch senkrecht z
4、ur Deck chicht fr Wabenkernverbunde This “Aerospace Series“ Prestandard has been drawn up under the responsibility 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 technica
5、lly approved by the experts of the concerned Domain following member comments. Subsequent to the publication 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
6、examination and review by users and formal agreement of AECMA-STAN it will be submitted as a draft European Standard to CEN (European Committee for Standardization) for formal vote. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not
7、 for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 2 prEN 2243-4: 2001 Contents Page O 1 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 8 8.1 8.2 8.3 8.4 9 10 11 Introduction . Normative references . Definitions, symbols and abbreviations Health and safety
8、. . PrinciplelTechnique Ressources . . Qualification of personnel Materials Surface preparation before bonding Storage of test panels after bonding Cutting of panels and preparation of type B test pieces Testing procedure Dimensions meacurem Fixing . Test temperatures . Expression of results . Test
9、report . Designation 3 3 3 4 4 4 4 4 4 4 4 4 5 5 5 5 5 5 5 6 6 6 6 6 7 7 7 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 3 prEN 2243-4: 2001 O
10、Introduction This standard is part of the series of EN non-metallic material 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 th
11、e determination of strength of structural adhesives by testing in tension metal to honeycomb core joints, at ambient or other temperatures. Two types of test pieces are defined: Type A: direct bonding of honeycomb to facing blocks; Type B: bonding of honeycomb between the two facing sheets, then bon
12、ding of the whole to the facing blocks. 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 hereafter. For dated refere
13、nces, 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 EN 2090 EN 2334 EN 2419 EN 2497 EN 2540 EN 3456
14、 EN 3464 EN 3487 EN 4385 EN 4606 Metallic materials - Verification 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 5 a 5 6
15、mm 1) Aerospace series - Chromic-sulphuric acid pickle of aluminium and aluminium alloys Aerospace series -Aluminium alloy AL-P2024- - T351 - Plate - 6 mm e a I 80 mm 1) Aerospace series - Dry abrasive blasting of titanium and titanium alloys Aerospace series - Steel FE-PM3902 (X7CrNiAI17-7) - Air m
16、elted - Solution treated and precipitation hardened - Sheet and strip - a I 6 mm - I 240 MPa S R, I 1 450 MPa 1) Aerospace series - Titanium alloy TLP64001 - Annealed - Sheet and strip, hot rolled - a56mml) Aerospace series - Titanium alloy Ti-P64001 - Annealed - Plate - 6 mm a I 100 mm 1) Aerospace
17、 series - Steel FE-PA13 - Softened - 500 I R, 5 700 MPa - Bar for machining - De 5 100 mm 1) Aerospace series - Non-metallic materials - General organisation of standardisation - Links between types of standards 1) Aerospace series - Aluminium honeycomb core 2) 1) Published as AECMA Prestandard at t
18、he date of publication of this standard 2) In preparation at the date of publication of publication of this standard Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted without licens
19、e from IHS-,-,-Page 4 prEN 2243-4: 2001 3 Definitions, symbols and abbreviations 3.1 Not applicable Def i n it ions 3.2 Symbols and abbreviations For the purposes of this standard, the following symbols and abbreviations apply: R F Li Dimensions in millimetres. Tensile strength (in mega pascals); Lo
20、ad at failure (in newtons); 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 IaboratoryAest house practices. It is the responsibility of the user to establish satisfac
21、tory health and safety practices and to ensure conformity with any European, national or local laws/regulations. 5 Not applicable P ri n ci p le/Tec h n i q u e 6 Resources 6.1 Apparatus All test equipment shall be calibrated at intervals not exceeding 12 months. 6.1 .I Tensile testing machine The t
22、ensile testing machine shall conform to class 1 of IS0 7500-1. The failing load of the test specimen shall be within 10 % and 90 % of the upper limit of the selected loading range of the machine. 6.1.2 Recorder It shall record continuously the displacement relative to the load applied throughout the
23、 test until total failure occurs. 6.2 MaterialslReagents Not applicable 6.3 Qualification of personnel Not applicable Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted without licen
24、se from IHS-,-,-Page 5 prEN 2243-4: 2001 7 Test samplesnest pieces 7.1 Materials 7.1 .I Honeycomb core: see EN 4606. Aluminium alloy EN 241 9 (facing blocks) or EN 2090 (facing sheets). For test temperatures up to 150 OC 7.1.2 Honeycomb core: see EN 4606. Corrosion resisting steel EN 2540 (facing sh
25、eets) or EN 3487 (facing blocks) or titanium alloy EN 3456 and EN 3464. NOTE 1 These are the preferred (reference) alloys for high temperature test, but aluminium alloys defined in 7.1.1 can also be used. NOTE 2 The same material has to be used for all the tests if results have to be compared. For t
26、est temperatures above 150 OC 7.2 Surface preparation before bonding EN 2334 or EN 2497 according to the material, or another specified preparation. 7.3 Bonding The application and curing of the adhesive system (adhesive and primer) shall be carried out according to the material standard unless othe
27、rwise agreed with the adhesive system manufacturer. 7.4 The test panel shall be of sufficient size to permit the manufacture of at least one test piece (see figure 1). Dimensions of panels (type B test piece) 7.5 They shall be stored under the following conditions: Storage of test panels after bondi
28、ng - temperature : (2312) OC; - relative humidity : (50 f. 5) %. 7.6 The panels shall be cut into test pieces (see figure 1). The panels made with high temperature curing adhesives shall be cut only after a storage period of 16 hours (see note 1). NOTE 1 For batch acceptance testing, this 16 hours p
29、eriod can be omitted. Nevertheless, for temperature 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 (I 50 OC) or mechanical damage to the joint (see note 2). Cutting of panels and preparation
30、of type B test pieces NOTE 2 A fine-tooth, 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. Test piece shall be bond onto blocks by using a cold curing type adhesive. The a
31、pplication and curing of the adhesive system (adhesive and primer) shall be carried out according to it material standard, and care shall be taken to avoid any mechanical or thermal effect than could damage the joint to be tested. Copyright Association Europeene des Constructeurs de Materiel Aerospa
32、tial Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 6 prEN 2243-4: 2001 7.7.1 Dimensions See figure 1. 7.7.2 Number of specimen See material standard. 7.7.3 Identification Each test piece shall be marked to identify th
33、e panel from which it was cut and its position in the panel. a Testing procedure 8.1 Di men si0 n s me as u remen t Measure the specimen side dimensions LI and Lz with an accuracy off 0,l rnm. 8.2 Fixing The ends of the test piece shall be carefully fixed to the testing machine by mean of the holes
34、provided for this purpose in the facing blocks. The attachment points of the machine and the test piece have to be aligned in such a way that an imaginary straight line can go through the centre of the test piece and the axis of the attachment points of the machine. 8.3 Test temperatures When the te
35、st temperature is different from ambient (23 f 2) “C, then the chamber including jig shall be stabilised within the test temperature tolerance for at least 30 min prior inserting the test piece. The temperature control of the test piece shall be carried out using a thermocouple. The junction of the
36、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 temperature different from ambient, and unless otherwise specified, a minimum exposure time of IO minutes at the required temperature shall be a
37、pplied prior to loading. The load shall be applied at a uniform jaws separation of 1 mm/min. (see note 1). NOTE 1 and 13 mmlmin, or at rate between 2 O00 Nlmin and 3 O00 N/min. For test other than qualification, it can be tolerated to apply the load at speed between 0,5 mmlmin Record the load-displa
38、cement curve (see note 2). NOTE 2 For non-ambient temperature tests, there is a requirement for the test portion of the specimen to be within the specified temperature tolerance throughout the period of loading to failure. The exposure time of ten minutes is normally sufficient to fulfill this requi
39、rement. Nevertheless, the test laboratory may be required to prove the heat dwell concept (procedure and conditions) by means of temperaturehme records on dummy specimen(s) incorporating thermocouple(s) embedded in drilled hole(s) within the test portion of the specimen. These records shall be made
40、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 the test machine and the temperature monitored according to the heat dwell concept previously established. When it reaches the lower
41、(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 prior to loading. The test shall be completed within a maximum dwell of IO minutes. The heat-upldwell cycle used shall be given in the t
42、est report. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 7 prEN 2243-4: 2001 9 Expression of results The tensile strength shall be calculated
43、as follows: R = F/Ll.L* IO Designation EXAMPLE: Description block Identity block FLATWISE TENSILE STRENGH EN2243-4A Number of this standard Type of test piece (A or B) 11 Test report The test report shall include: - reference to the test method designation; - the type of tensile testing machine, the
44、 speed of loading, the exposure conditions and test temperature; - the type of test piece used (A or B); - complete identification of the adhesive system, including the type, manufacturer, date of manufacture, batch number, material standard or specification number; - complete identification of the
45、metal and honeycomb core used; - detailed information about the surface preparation before bonding; - application and bonding conditions including the bonding method (press, autoclave, .), pressure on the adhesive joint, heat-up rate, curing time and temperature; - information about individual test
46、piece including traceability from panel, actual dimensions, sheet thickness and bond line thickness; - type of recorder; - 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; - a
47、ssociated diagram; - in case of multiple tests: - number of test pieces; - average, standard deviation, maximum and minimum 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
48、 in detail; - date of test. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 8 prEN 2243-4: 2001 Dimensions in millimetres Cell size: 6,4 TYPE A T
49、YPE B (For honeycomb material: see EN 4606) Key 1 Facing blocks 2 Facing sheet 3 Adhesive 4 Honeycomb core 5 Face of reference Figure 1 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-
