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1、IS0 b773 94 4851903 0576635 444 I NTERNAT I O NAL STAN DAR D IS0 6773 Second edition 1994-1 0-01 Aerospace - Fluid systems - Thermal shock testing of piping and fittings Aronautique et espace - Systmes de fluides - Essai de choc thermique des tuyauteries et raccords Reference number IS0 6773:1994(E)
2、 Copyright International Organization for Standardization Provided by IHS under license with ISO Licensee=NASA Technical Standards 1/9972545001 Not for Resale, 04/28/2007 04:59:20 MDTNo reproduction or networking permitted without license from IHS -,-,- IS0 6773 94 485J03 0576636 380 IS0 6773:1994(E
3、) Foreword IS0 (the International Organization for Standardization) is a worldwide federation of national standards bodies (IS0 member bodies). The work of preparing International Standards is normally carried out through IS0 technical committees. Each member body interested in a subject for which a
4、 technical committee has been established has the right to be represented on that committee. International organizations, governmental and non-governmental, in liaison with ISO, also take part in the work. IS0 collaborates closely with the International Electrotechnical Commission (IEC) on all matte
5、rs of electrotechnical standardization. Draft International Standards adopted by the technical committees are circulated to the member bodies for voting. Publication as an International Standard requires approval by at least 75 % of the member bodies casting a vote. International Standard IS0 6773 w
6、as prepared by Technical Committee ISO/TC 20, Aircraft and space vehicles, Subcommittee SC 1 O, Aerospace fluid systems and components. This second edition cancels and replaces the first edition (IS0 6773:1982), the figure of which has been technically revised and the text clarified in places. o IS0
7、 1994 All rights reserved. Unless otherwise specified, no part of this publication may be reproduced or utilized in any form or by any means, electronic or mechanical, including photocopying and microfilm, without permission in writing from the publisher. International Organization for Standardizati
8、on Case Postale 56 CH-1 21 1 Genve 20 Switzerland Printed in Switzerland II Copyright International Organization for Standardization Provided by IHS under license with ISO Licensee=NASA Technical Standards 1/9972545001 Not for Resale, 04/28/2007 04:59:20 MDTNo reproduction or networking permitted wi
9、thout license from IHS -,-,- IS0 6773 94 = 45L903 O576637 217 INTERNATIONAL STANDARD 0 IS0 IS0 6773:1994(E) Aerospace - Fluid systems - Thermal shock testing of piping and fittings 1 Scope This International Standard provides an environmental test method for thermal shock testing of fluid system pip
10、ing and fittings, excluding hose and hose as- semblies. 2 Normative reference The following standard contains provisions which, through reference in this text, constitute provisions of this International Standard. At the time of publi- cation, the edition indicated was valid. All standards are subje
11、ct to revision, and parties to agreements based on this International Standard are encouraged to investigate the possibility of applying the most re- cent edition of the standard indicated below. Mem- bers of IEC and IS0 maintain registers of currently valid International Standards. IS0 6772:1988, A
12、erospace - Fluid systems - Im- pulse testing of hydraulic hose, tubing and fitting as- semblies. 3 Required characteristics The test assemblies shall not leak or burst during temperature and pressure cycling procedures de- scribed in clause 4. 4 Method of test 4.1 Test apparatus The test assemblies
13、shall be mounted in a test fixture similar to that shown in figure 1 capable of providing the specified test fluid, ambient temperatures and circuit pressures corresponding to the system classi- fication specified in IS0 6772. 4.2 Test fluid The specified test fluid shall be a system fluid or hy- dr
14、aulic fluid which is compatible with the item being tested and the specified system pressure and tem- perature. 4.3 Hot test chamber testing Mount the test assemblies in a temperature chamber, connect them to a pressure source and fill them with the specified test fluid. Then pressurize the as- semb
15、lies to at least the nominal circuit service press- ure and raise the temperature in the test chamber to at least the maximum specified for the circuit. Hold this temperature for a minimum of 2 h. At the end of this period, while still at at least the maximum tem- perature, release the hot test flui
16、d and replace it within 20 s with test fluid initially at or below the minimum specified temperature. Within an additional 20 s, raise the test pressure to at least proof pressure and maintain this pressure for at least 1 min and then release it for at least an additional 1 min. Then repeat the l-mi
17、n proof test. Observe the assemblies contin- uously during the two l-min pressurization periods to determine any leakage. 4.4 Cold test chamber testing Following a cooling period to room temperature, re- apply at least the nominal circuit pressure and lower the chamber temperature to at least the mi
18、nimum specified. Hold this temperature for a minimum of 2 h. At the end of this period while still at low tem- perature, release the cold fluid and replace it with test 1 Copyright International Organization for Standardization Provided by IHS under license with ISO Licensee=NASA Technical Standards
19、 1/9972545001 Not for Resale, 04/28/2007 04:59:20 MDTNo reproduction or networking permitted without license from IHS -,-,- IS0 b773 94 = 48.51903 057bb38 153 = IS0 6773:1994(E) - - - Test items - - - 0 IS0 T fluid initially at at least the maximum circuit tempera- ture within 20 s. Within an additi
20、onal 20 s, raise the pressure to the proof pressure specified for the cir- cuit, and maintain this pressure for at least 1 min. Observe the specimens closely to determine any 4.5 Test schedule The procedures described in 4.3 or 4.4 shall be re- peated in sequence three times to complete the re- leak
21、age. Manome ter 1/4 turn valve quirements of the thermal shock test. 7 Thermometer 7 Y L Manometer L P Heat exchanger system (CO2 may be used to obtain - 55 C temperature) 1/4 turn valve (feed) Hydraulic pump -4 Hand valve Pressuresource NOTE - The graphic symbols conform to IS0 121 9-1 :I 991, Flui
22、d power systems and components - Graphic symbols and circuit diagrams - Part 1: Graphic symbols. Figure 1 - Thermal shock test apparatus 2 Copyright International Organization for Standardization Provided by IHS under license with ISO Licensee=NASA Technical Standards 1/9972545001 Not for Resale, 04
23、/28/2007 04:59:20 MDTNo reproduction or networking permitted without license from IHS -,-,- IS0 6773 94 W 4851703 057bb39 09T = IS0 6773:1994(E) 0 IS0 ICs 49.080.00 Descriptors: aircraft, aircraft equipment, hydraulic systems, fluid circuits, piping, pipes (tubes), pipe fittings, tests, thermal shock tests. Price based on 2 pages Copyright International Organization for Standardization Provided by IHS under license with ISO Licensee=NASA Technical Standards 1/9972545001 Not for Resale, 04/28/2007 04:59:20 MDTNo reproduction or networking permitted without license from IHS -,-,-