BS ISO 16691-2014 Space systems Thermal control coatings for spacecraft General requirements《空间系统 航天器的热控涂层 一般要求》.pdf

1、BSI Standards PublicationBS ISO 16691:2014Space systems Thermalcontrol coatings for spacecraft General requirementsBS ISO 16691:2014 BRITISH STANDARDNational forewordThis British Standard is the UK implementation of ISO 16691:2014.The UK participation in its preparation was entrusted to TechnicalCom

2、mittee ACE/68/-/8, Space systems and operations - Materials andprocesses.A list of organizations represented on this committee can beobtained on request to its secretary.This publication does not purport to include all the necessaryprovisions of a contract. Users are responsible for its correctappli

3、cation. The British Standards Institution 2014. Published by BSI StandardsLimited 2014ISBN 978 0 580 80364 2ICS 49.025.01; 49.140Compliance with a British Standard cannot confer immunity fromlegal obligations.This British Standard was published under the authority of theStandards Policy and Strategy

4、 Committee on 28 February 2014.Amendments issued since publicationDate Text affectedBS ISO 16691:2014 ISO 2014Space systems Thermal control coatings for spacecraft General requirementsSystmes spatial Revetements pour le contrle thermique des satellites et vehicules spatiaux Exigences gnralesINTERNAT

5、IONAL STANDARDISO16691First edition2014-02-15Reference numberISO 16691:2014(E)BS ISO 16691:2014ISO 16691:2014(E)ii ISO 2014 All rights reservedCOPYRIGHT PROTECTED DOCUMENT ISO 2014All rights reserved. Unless otherwise specified, no part of this publication may be reproduced or utilized otherwise in

6、any form or by any means, electronic or mechanical, including photocopying, or posting on the internet or an intranet, without prior written permission. Permission can be requested from either ISO at the address below or ISOs member body in the country of the requester.ISO copyright officeCase posta

7、le 56 CH-1211 Geneva 20Tel. + 41 22 749 01 11Fax + 41 22 749 09 47E-mail copyrightiso.orgWeb www.iso.orgPublished in SwitzerlandBS ISO 16691:2014ISO 16691:2014(E) ISO 2014 All rights reserved iiiContents PageForeword ivIntroduction v1 Scope . 12 Normative references 13 Terms, definitions, and abbrev

8、iated terms . 13.1 Terms and definitions . 13.2 Abbreviated terms . 44 General 44.1 Functionality . 54.2 Basic components . 65 Selection 66 Test methods for TCC . 86.1 Visual inspection . 86.2 Coating thickness 86.3 Adhesion . 86.4 Thermo-optical properties . 86.5 Resistance (electrical surface resi

9、stance and electrical volume resistivity) 106.6 Outgassing 106.7 UV-resistance . 116.8 Radiation resistance 116.9 tomic oxygen resistance . 116.10 Gloss 116.11 Temperature cycling (influence of temperatures) 116.12 Mass of ejecta 117 Requirements for application 118 Safety requirements for TCC appli

10、cation .129 Identification .1210 Protectors .1211 Packing.1312 Production program of quality assurance 1312.1 General 1313 Changes and revisions .1313.1 Permissive document . 1313.2 Necessary signatures for the confirmatory document 1413.3 Record of changes 14Annex A (informative) General properties

11、 of TCC-I and TCC-II 15Bibliography .17BS ISO 16691:2014ISO 16691:2014(E)ForewordISO (the International Organization for Standardization) is a worldwide federation of national standards bodies (ISO member bodies). The work of preparing International Standards is normally carried out through ISO tech

12、nical committees. Each member body interested in a subject for which a 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. ISO collaborates closely

13、 with the International Electrotechnical Commission (IEC) on all matters of electrotechnical standardization.The procedures used to develop this document and those intended for its further maintenance are described in the ISO/IEC Directives, Part 1. In particular the different approval criteria need

14、ed for the different types of ISO documents should be noted. This document was drafted in accordance with the editorial rules of the ISO/IEC Directives, Part 2 (see www.iso.org/directives).Attention is drawn to the possibility that some of the elements of this document may be the subject of patent r

15、ights. ISO shall not be held responsible for identifying any or all such patent rights. Details of any patent rights identified during the development of the document will be in the Introduction and/or on the ISO list of patent declarations received (see www.iso.org/patents).Any trade name used in t

16、his document is information given for the convenience of users and does not constitute an endorsement.For an explanation on the meaning of ISO specific terms and expressions related to conformity assessment, as well as information about ISOs adherence to the WTO principles in the Technical Barriers

17、to Trade (TBT) see the following URL: Foreword - Supplementary informationThe committee responsible for this document is ISO/TC 20, Aircraft and space vehicles, Subcommittee SC 14, Space systems and operations.iv ISO 2014 All rights reservedBS ISO 16691:2014ISO 16691:2014(E)IntroductionThis Internat

18、ional Standard explains technical information for TCCs selection and application required to confirm their compliance with the requirements of the thermal control for spacecraft.This International Standard classifies thermal control coatings in accordance with their usage in passive and/or active th

19、ermal control subsystems for reduction of external heat absorption or regulation of radiant heat exchange between on-board equipment on spacecraft, their general properties, and their special characteristics for space environment applications.This International Standard also contains special recomme

20、ndations for surface preparation, application of coating systems and curing, and establishes requirements for test methods on estimating properties of thermal control coatings according to their target use. ISO 2014 All rights reserved vBS ISO 16691:2014BS ISO 16691:2014Space systems Thermal control

21、 coatings for spacecraft General requirements1 ScopeThis International Standard defines general requirements for thermal control coatings (TCC) that are applied on metallic and/or non-metallic surfaces of spacecraft and payloads in order to provide the following thermo-optical properties: s: solar a

22、bsorptance; : emittance.The function of TCC is to reduce external heat absorption and/or to regulate radiant heat exchange between on-board equipment on spacecraft.2 Normative referencesThe following documents, in whole or in part, are normatively referenced in this document and are indispensable fo

23、r its application. For dated references, only the edition cited applies. For undated references, the latest edition of the referenced document (including any amendments) applies.ISO 9117-1:2009, Paints and varnishes Drying tests Part 1: Determination of through-dry state and through-dry timeISO 1462

24、4-3, Space systems Safety and compatibility of materials Part 3: Determination of offgassed products from materials and assembled articles3 Terms, definitions, and abbreviated terms3.1 Terms and definitionsFor the purposes of this document, the following terms and definitions apply.3.1.1active therm

25、al control systemsystem where the active thermal control method is usedNote 1 to entry: The active thermal control method is the procedure to control the temperature using mechanical mobile components or fluid, using electric energy from a heater, changing the components thermo-physical property, or

26、 utilizing another technology to change/control the temperature.SOURCE: JERG-2310:20093.1.2coatingcontinuous layer formed from a single or multiple application of a coating material to a substrateSOURCE: ISO 4618:2006INTERNATIONAL STANDARD ISO 16691:2014(E) ISO 2014 All rights reserved 1BS ISO 16691

27、:2014ISO 16691:2014(E)3.1.3coating materialproduct in liquid, paste, or powder form, that, when applied to a substrate, forms a film possessing protective and/or other specific propertiesSOURCE: ISO 4618:20063.1.4coating processprocess of application of a coating material to a substrate, such as dip

28、ping, spraying, roller coating, brushingSOURCE: ISO 4618:20063.1.5coating systemcombination of all coats of coating materials which are to be applied or which have been applied to a substrateSOURCE: ISO 4618:20063.1.6emissivityemittance=M/Mb where M is the radiant exitance of a thermal radiator, and

29、 Mb is the radiant exitance of a blackbody at the same temperatureNote 1 to entry: The following adjectives should be added to define the conditions: Total: If they are related to the entire spectrum of thermal radiation (this designation can be considered as implicit);7 Spectral or monochromatic: I

30、f they are related to a spectral interval centered on the wavelength ;7 Hemispherical: If they are related to all directions along which a surface element can emit or receive radiation;7 Directional: If they are related to the directions of propagation defined by a solid angle around the defined dir

31、ection;7 Normal: If they are related to the normal direction of propagation or incidence to the surface.7SOURCE: ISO 80000-7:2008SOURCE: ISO 163783.1.7paintpigmented coating material which, when applied to a substrate, generally forms an opaque film having protective or specific technical properties

32、SOURCE: ISO 4618:20063.1.8paint filmintact coating that is formed by applying one or multiple layers of coating materials on a substrate2 ISO 2014 All rights reservedBS ISO 16691:2014ISO 16691:2014(E)3.1.9passive thermal control systemsystem where the passive thermal control method is usedNote 1 to

33、entry: The passive thermal control method is the procedure to control the temperature of the component within the specified range by adjusting the paths of conduction and radiation, and by the selection of geometric form of each surface and thermo-physical property of the spacecraft.SOURCE: JERG-231

34、0:20093.1.10payloadset of space segment elements (parts of a space system placed in space to fulfill the space mission objectives)Note 1 to entry: A spacecraft payload is a set of instruments or equipment that performs the user mission.Note 2 to entry: A launcher payload is a set of space segment el

35、ements carried into space in accordance with agreed position, time, and environmental conditions.SOURCE: ISO 10795:20113.1.11primerpaint that has been formulated for use as a priming coat on prepared surfaces3.1.12priming coatfirst coat of a coating system3.1.13solar absorptancesratio of the solar r

36、adiant flux absorbed by a material (or body) to the radiant flux of the incident radiation3.1.14substratesurface to which a coating material is applied or is to be applied3.1.15thermal control coatingTCCcoating that is used to maintain certain temperature conditions of an object by way of establishi

37、ng the balance between the heat absorbed from an environment and/or emitted by internal heat sources and the energy radiated by objects surface in an environment3.1.16varnishclear coating material which, when applied to a substrate, forms a transparent film3.1.17witness samplesample pieces that repr

38、esent the coated productNote 1 to entry: They shall be made in the form of the flat plates using the same coating material with the product, and coated simultaneously. Used for destructive test and test that requires limited size of specimen. ISO 2014 All rights reserved 3BS ISO 16691:2014ISO 16691:

39、2014(E)3.2 Abbreviated termsThe following abbreviated terms are defined and used within this International Standard.BOL beginning of lifeEMC electromagnetic compatibilityEOL end-of-lifeESD electrostatic dischargeTCC(s) thermal control coating(s)TCS(s) thermal control (sub) system(s)QA quality assura

40、nceUV ultravioletVUV vacuum ultraviolet4 GeneralFigure 1 The mapping of thermal control coatings relative to each passive thermal control materialThe action of the space environment strongly depends on the spacecraft service conditions. These are defined by the orbits where spacecraft are intended t

41、o operate.Heat sources which determine the temperature of a spacecraft are mainly solar rays and earth albedo. The quantity of heat emitted from a spacecraft is equal to the sum of heat input and the quantity of internal heat produced from the all equipment of a spacecraft.Nevertheless, there are ge

42、neral factors that exert influence on spacecraft serviceability and efficiency: vacuum, electromagnetic solar radiation, including UV-radiation and VUV-radiation, ionizing radiations, atomic oxygen, temperature, contamination, micrometeoroids, and debris environment effects.4 ISO 2014 All rights res

43、ervedBS ISO 16691:2014ISO 16691:2014(E)When in service, undesirable effects can occur, such as electrostatic charging, generation of spacecraft outer atmosphere, and alternating thermal loads.TCC are generally damaged by UV and charged particle exposure. In addition, at altitudes of roughly 200 km-6

44、00 km erosion of some TCC can occur due to atomic oxygen. Bleaching or whitening of UV/charged particle induced damage of these coatings can also occur from atomic oxygen exposure.TCCs are the elements of passive and/or active TCSs for temperature regulation of spacecraft. The location of thermal co

45、ntrol coatings in relation to other passive thermal control materials is shown in Figure 1 above.TCCs are applied on spacecraft surfaces, individual units, assemblies, and devices that are to be temperature-controlled. They are used to maintain the preset temperature conditions of a spacecraft by es

46、tablishing the balance between the heat absorbed from an environment and/or emitted by on-board sources, the energy redistributed between equipment and spacecraft structure, and the energy radiated in environment.The thermo-optical properties of a TCC are used in TCSs design. TCC shall meet the spec

47、ification requirements at the BOL and maintain required properties at the EOL of the spacecraft.EMC/ESD, ageing, difference of properties between the beginning and the end of service life are defined by service conditions and purposes of spacecraft. These properties are measured when candidate TCC m

48、aterials are under consideration for a TCS in the design stage.The scope depends on the coating to be tested and requirements of designer and/ or production engineer.4.1 FunctionalityWith regard to their functionality, determined by the coatings ability to absorb or reflect the radiant energy, the t

49、hermal control coatings can be classified as follows: I: true absorber (s1, 1); II: solar reflector (s0, 1); III: solar absorber (s1, 0); IV: true reflector (s0, 0).4.1.1 Class IClass I (black) TCCs absorb the heat from higher temperature objects and transmit the heat to lower temperature one, and promote intensification of the radiant heat transfer between surfaces of devices and units, as well as between devices, units, and environment.Black TCCs are mainl