BS EN 2155-19-1997 Specification for test methods for transparent materials for aircraft glazing - Determination of craze resistance《飞行器玻璃门窗用透明材料的试验方法规范 抗裂纹特性测定》.pdf

1、BRITISH STANDARD AEROSPACE SERIES BS EN 2155-19:1997 Test methods for Transparent materials for aircraft glazing Part 19: Determination of craze resistance The European Standard EN 2155-19:1996 has the status of a British Standard ICS 49.025.99BSEN 2155-19:1997 This British Standard, having been pre

2、pared under the direction of the Engineering Sector Board, was published under the authority of the Standards Board and comes into effect on 15 February 1997 BSI 12-1998 The following BSI references relate to the work on this standard: Committee reference ACE/62 Draft for comment94/715195 DC ISBN058

3、0263770 Committees responsible for this British Standard The preparation of this British Standard was entrusted to Technical Committee ACE/62, Aerospace structural transparencies and non-reinforced plastics, upon which the following bodies were represented: British Plastics Federation Defence Resear

4、ch Agency Society of British Aerospace Companies Limited Amendments issued since publication Amd. No. Date CommentsBSEN 2155-19:1997 BSI 12-1998 i Contents Page Committees responsible Inside front cover National foreword ii Foreword 2 Text of EN2155-19 3BSEN 2155-19:1997 ii BSI 12-1998 National fore

5、word This British Standard has been prepared by Technical Committee ACE/62 and is the English language version of EN2155-19: 1996 Aerospace series Test methods for transparent materials for aircraft glazing Part19: Determination of craze resistance published by the European Committee for Standardiza

6、tion (CEN). EN2155-19 was produced as a result of international discussion in which the United Kingdom took an active part. A British Standard does not purport to include all the necessary provisions of a contract. Users of British Standards are responsible for their correct application. Compliance

7、with a British Standard does not of itself confer immunity from legal obligations. Summary of pages This document comprises a front cover, an inside front cover, pages i and ii, theEN title page, pages2 to4 and a back cover. This standard has been updated (see copyright date) and may have had amendm

8、ents incorporated. This will be indicated in the amendment table on theinside front cover.EUROPEAN STANDARD NORME EUROPENNE EUROPISCHE NORM EN2155-19 August1996 ICS49.040.10 Descriptors: Aircraft industry, glazing, translucent glasses, transparent plastic, test, determination, crack strength English

9、 version Aerospace series Test methods for transparent materials for aircraft glazing Part19: Determination of craze resistance Srie arospatiale Mthodes dessais pour matriaux transparents pour vitrages aronautiques Partie19: Dtermination de la rsistance au fendillement “crazing” Luft-und Raumfahrt P

10、rfverfahren fr transparente Werkstoffe zur Verglasung von Luftgahrzeugen Teil19: Bestimmung der Spannungsribestndigkeit This European Standard was approved by CEN on1995-04-13. CEN members are bound to comply with the CEN/CENELEC Internal Regulations which stipulate the conditions for giving this Eu

11、ropean Standard the status of a national standard without any alteration. Up-to-date lists and bibliographical references concerning such national standards may be obtained on application to the Central Secretariat or to any CEN member. This European Standard exists in three official versions (Engli

12、sh, French, German). A version in any other language made by translation under the responsibility of a CEN member into its own language and notified to the Central Secretariat has the same status as the official versions. CEN members are the national standards bodies of Austria, Belgium, Denmark, Fi

13、nland, France, Germany, Greece, Iceland, Ireland, Italy, Luxembourg, Netherlands, Norway, Portugal, Spain, Sweden, Switzerland and United Kingdom. CEN European Committee for Standardization Comit Europen de Normalisation Europisches Komitee fr Normung Central Secretariat: rue de Stassart 36, B-1050

14、Brussels 1996 Copyright reserved to CEN members Ref. No. EN2155-19:1996 EEN2155-19:1996 2 BSI 12-1998 Foreword This European Standard has been prepared by the European Association of Aerospace Manufacturers (AECMA). After inquiries and votes carried out in accordance with the rules of this Associati

15、on, this Standard has received the approval of the National Associations and the Official Services of the member countries of AECMA, prior to its presentation to CEN. This European Standard shall be given the status of a national standard, either by publication of an identical text or by endorsement

16、, at the latest by February1997, and conflicting national standards shall be withdrawn at the latest by February1997. According to the CEN/CENELEC Internal Regulations, the national standards organizations of the following countries are bound to implement this European Standard: Austria, Belgium, De

17、nmark, Finland, France, Germany, Greece, Iceland, Ireland, Italy, Luxembourg, Netherlands, Norway, Portugal, Spain, Sweden, Switzerland and the United Kingdom. Contents Page Foreword 2 1 Scope 3 2 Definition 3 3 Apparatus and materials 3 4 Specimens 3 5 Conditioning 4 6 Procedure 4 7 Test report 4 F

18、igure 1 Loading condition for flat sheet 3EN2155-19:1996 BSI 12-1998 3 1 Scope This standard specifies the test method to determine the resistance of transparent sheet to the effect of a solvent environment while subjected to a load. No method has been developed yet for specimens with a thickness 6m

19、m shall be machined on one face only to6mm thickness and the non-machined face shall be tested. 4.3 A hole of6mm diameter shall be drilled with its centre15mm from one end and on the centre line of the specimen to facilitate loading (seeFigure 1). Figure 1 Loading condition for flat sheetEN2155-19:1

20、996 4 BSI 12-1998 5 Conditioning 5.1 The specimens shall be conditioned at(23 2)C, (50 5)% relative humidity for at least48h prior to testing under the same conditions. 5.2 The apparatus and solvent (in a suitably stoppered container) shall be pre-conditioned as for the specimens. 6 Procedure 6.1 Fo

21、r unstretched material the test specimens shall be freely suspended in an air-circulating oven and maintained at a temperature of (155 2)C for a period of30min. After allowing to cool to room temperature under draught-free conditions the specimens are annealed in an air-circulating oven to the manuf

22、acturers instructions, then allowed to cool to room temperature under draught-free conditions. After annealing and cooling the width and thickness shall be measured at the position of the fulcrum with an accuracy of 0,02mm. 6.2 For stretched acrylic material the test specimens shall be freely suspen

23、ded in an air-circulating oven and maintained at a temperature of (75 2)C for a period of16h and then allowed to cool under draught-free conditions. Prior to testing the width and thickness shall be measured at the position of the fulcrum with an accuracy of 0,02mm. 6.3 The specimens shall be set up

24、 as cantilever beams and loaded with the specified outer fibre stress which is calculated from the following formula. where: 6.4 After application of the load for10min and while still under load, propanol-2 (isopropyl alcohol) shall be applied to each specimen by means of a20mm 20mm filter paper pat

25、ch placed on the upper surface and centered on the fulcrum and kept wet with the solvent. 6.5 The filter paper patch shall be removed after30min and the specimen examined for evidence of crazing. 6.6 There shall be no crazing (group of cracks) on the tested surface. Individual cracks shall be disreg

26、arded. Unless the cracks are over3mm in length, edge crazing shall be disregarded. 7 Test report The test report shall include the following: number of this standard; material type; batch number; stress applied; appearance of specimen after test; compliance/non-compliance with the requirements of6.6

27、. s is the outer fibre stress, in megapascals; B is the specimen width measured, in millimetres; A is the specimen thickness measured, in millimetres; L is the distance from the fulcrum point to the load application point, in millimetres measured to the nearest0,1mm. load (newtons) s B A 2 6 L - =bl

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