1、Lo 2 D Lo i w I- l E 4 a CL W O O LD s F s I al m - ml O .LI W -J W. I F 7 a 4 k! 0- O UI -I a W G I Lu tl VI U 3 u1 F- o 3 a VI u1 tl Lu z z W w 8 0 4 a 3 w 2 b o 8 -I cc U a w CI t w AECMA PREN2243-OL 0 LOii23LL 0002572 b i -_ _ r 7- ,_ A. E.C, MA. STAN BARD A. E.C.M.A. NORM DRAFT NORME A.E.C.M.A.
2、 prEN2243-1 Edition 1 August 1980 ENGLISH VERSION STRUCTU BAL ADH ESIY ES TEST METHODS PART l -SINGLE LAP SHEAR AEROSPACE SER I ES ADH ES1 FS STRUCTURAUX LUFT-UND RAUMFAHRT MGTHODES DESSAIS STRUKTURELLE KLEBSTOFFE PARTIE 1 - ESSAIS DE CISAILLEMENT PRFVERFAHREN VON EINSCHNITTIG BERLAPPTEN TEIL 1 BEST
3、IMMUNG DER BINDE FEST1 G KEIT KLEBUNGENIMZUGVERSUCH DUN JOINT A RECOUVREMENT SIMPLE SR1 E AEROSPATI AL E The text of this standard, which exists in three equivalent versions (English, French, German) has been drawn up under the responsibility of A EGMA (Association Europenne des Constructeurs de Mat
4、riel Arospatial) and has been circulated to Officid Services. Any reservations expressed by Official Services and not resolved in this hue, have been incorporated in the history sheet which has accompanied this prEN to CEM. It is published on yellow paper as a draft European Standard intended to rec
5、eive, under the same presentation and according to its own rules, the approval of CEN (European Committee for Standardization). Approved by The equivalent versions in French and German languages COMITE DE NORMALISATION can be supplied by B.N.A.E., 8, rue Moreau-Vouthier of A.E.C.M.A. 1977-10-28 9210
6、0 BOULOGNE-BILLANCOURT - FRANCE, COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling ServicesAECMA PREN22C!3-02 0 E LUL23LL 0002573 prEN2243-1 Page 2 CONTENTS 1 SCOPE AND FIELD OP APPLICATION 2 REFERENCES 3 TEST SAMPLES 4 SURFACE PREPARATION 5 BOND
7、ING 6 STORAGE OF SAMPLES AFTER BONDING 7 CUTTING AND PREPARATION OF TEST PIECES 8 TEST CONDITIONS 9 METHOD OF TEST i0 CALCULATION OF RESULTS 11 TEST REPORT COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling ServicesAECMA PREN2243-01 80 E LOL23LL 0
8、002574 T II prEN2243-1 Page 3 DRAFT EUROPEAN STANDARD r AEROSPACE SRIES prEN2243-1 STRUCTURAL ADHESIVES TEST METHODS PART 1 - SINGLE LAP SKEAR 1 SCOPE AND FIELD OF APPLICATION The abjective of this standard is Eo establish the test methods Sor defining the strength of suitable structural adhesives i
9、n metal to metal single lap shear, at ambient and other temperatures, 2 REFERENGES EM2987, EN2088* Aluminium alloy 2014A-Tg or Te2 - Glad sheets and strips - 0,4 mm 5 a Q 6 mm l) RPumiriiurn alloy 2014A-T4 or T4S - Clad sheets and strips - 0,4 mm B a Q 6 rm EN2090, EN20921 EN2334, EN2497, * EN2517,
10、Aluminium alloy AL-PL3Pl-T3 - Clad sheets and strips - . Oj4mmaad6mm AluminTum alloy 707546 (AL-P42Pl-T8) - Glad sheets and strips - ,4 mm 6 a 6 6 mni Acid chromate pickle for alminium alloys i) Dry abrasive blasting of titanium 1) Titanium alloy TLP63 - Annealed - Sheets, strips and plates a s 100
11、m 1) EN2540, Steel FE-PM62 - Sheets I). 3 TEST SAMPLES 3.1 The shape and dimensions af the teck pieces and the panel out of which khe pieces shall be cut, shall be as given in tigure 1, 3,2 Sheet material (General) For general application the following materials shall be used. 3.2.1 3,2,2 Aluminium
12、alloy see ENZOSO, Aluminium alloy see EN2088 1) - These materials aine suitable for use to 15C. 1) In preparation. COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling Servicesr- 1 AECMA PREN2243-OL BO I LOL23Ll 0002595 L W prEN2243-1 Page 4 3.3 She
13、et material (Special) For adhesives having a shear strength higher than approximately 45 MPa the following materials can be used instead of the materials given in clause 3.2. 3.3.1 Aluminium alloy see EN2092. 3,3,2 Aluminium alloy see EN2087 1). These materials are suitable for use up to 15OOC. 3.4
14、Sheet material (For test.temperature above 150C) The following materials shall be used. 3.4,1 3.4.2 Corrosion resisting steel FE-PM62 aefined by EN2540 1) Titanium alloy TI-P63 defined by EN2517 I). 4 SURFACE PREPARATION The surface preparation prior to banding shall conform to EN2334 a) and EN2497
15、1) 5 BONDING The application of the adhesive system (adhesive and primer) as applicable and curing shall be carried out according to the instructions of the adhesive manufacturer or the material standard, 6 STORAGE OF TEST SAMPLES AFTER BONDING After curing the sample made with elevated temperature
16、curing adhesives shall be exposed and/or tested after a storage period of 16 hours under the conditions s given below (unless otherwise specified by the ahesive manufacturer). The sample for room temperature curing adhesives not exposed and/or tested immediately after curing, shall also be stored as
17、 given below (unless other- wise specified by the adhesive manufacturer). Storage conditions : - Room temperature : 23 i 2OC - Relative humidity: 50 age of failure in cohesion and/or adhacion both of adhesive and psssihle adhesive primer, U11Q The average, maximum and minimuin sheas strength values
18、of the tese series, 11.91 Any deviations from this test method shall be desarfbed in detail, 11.9 COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling ServicesprEN2243-1 Page 7 Dimensions in millimetres 1.6 for elurninium alloy l,2 for corrosion res
19、isting steel and titanium alloy The width of separate panels prior %o bonding, given as approx. LOO, depends upon grip length required for the particular testing machine, The tooling holes should be approx. 2 to 4 nun, The direction of rolling of the sheet materia2 shall be parallel to the longitudi
20、nal axis of the test pieces. All the edges of the panels which will be within the bonded joint shall be smooth, without, burrs and at right angles to the faces before surface treatment. COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling ServicesAE
21、CMA PREN2243-OL 80 m LOL23Ll 0002599 9 m prN2243-1 Page 8 Dimensions in millimetres .-. I. . 25-c0,5 . t L 12,5 f 0.6 FIGURE 2 Thermocouple junction placed on metal within shaded portion of bonded area (6 x 7 mm), FIGURE 3 COPYRIGHT Association Europeene Des Constructeurs de Materiel AerospaceLicensed by Information Handling Services
