1、raising standards worldwideNO COPYING WITHOUT BSI PERMISSION EXCEPT AS PERMITTED BY COPYRIGHT LAWBSI Standards PublicationBS ISO 15856:2010Space systems Spaceenvironment Simulationguidelines for radiationexposure of non-metallicmaterialsBS ISO 15856:2010 BRITISH STANDARDNational forewordThis British
2、 Standard is the UK implementation of ISO 15856:2010.The UK participation in its preparation was entrusted to TechnicalCommittee ACE/68/-/4, Space systems and operations - Spaceenvironment (natural and artificial).A list of organizations represented on this committee can beobtained on request to its
3、 secretary.This publication does not purport to include all the necessaryprovisions of a contract. Users are responsible for its correctapplication. BSI 2010ISBN 978 0 580 56552 6ICS 49.140Compliance with a British Standard cannot confer immunity fromlegal obligations.This British Standard was publi
4、shed under the authority of theStandards Policy and Strategy Committee on 31 August 2010.Amendments issued since publicationDate Text affectedBS ISO 15856:2010Reference numberISO 15856:2010(E)ISO 2010INTERNATIONAL STANDARD ISO15856First edition2010-08-01Space systems Space environment Simulation gui
5、delines for radiation exposure of non-metallic materials Systmes spatiaux Environnement spatial Lignes directrices de simulation pour lexposition aux radiations des matriaux non mtalliques BS ISO 15856:2010ISO 15856:2010(E) PDF disclaimer This PDF file may contain embedded typefaces. In accordance w
6、ith Adobes licensing policy, this file may be printed or viewed but shall not be edited unless the typefaces which are embedded are licensed to and installed on the computer performing the editing. In downloading this file, parties accept therein the responsibility of not infringing Adobes licensing
7、 policy. The ISO Central Secretariat accepts no liability in this area. Adobe is a trademark of Adobe Systems Incorporated. Details of the software products used to create this PDF file can be found in the General Info relative to the file; the PDF-creation parameters were optimized for printing. Ev
8、ery care has been taken to ensure that the file is suitable for use by ISO member bodies. In the unlikely event that a problem relating to it is found, please inform the Central Secretariat at the address given below. COPYRIGHT PROTECTED DOCUMENT ISO 2010 All rights reserved. Unless otherwise specif
9、ied, 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 either ISO at the address below or ISOs member body in the country of the requester. ISO copyright office Cas
10、e postale 56 CH-1211 Geneva 20 Tel. + 41 22 749 01 11 Fax + 41 22 749 09 47 E-mail copyrightiso.org Web www.iso.org Published in Switzerland ii ISO 2010 All rights reservedBS ISO 15856:2010ISO 15856:2010(E) ISO 2010 All rights reserved iiiContents Page Foreword iv Introduction.v 1 Scope1 2 Normative
11、 references2 3 Terms, definitions, abbreviated terms and acronyms.2 3.1 Terms and definitions .2 3.2 Abbreviated terms and acronyms .4 4 Space environment radiation characteristics.5 4.1 Sources of radiation in space 5 4.2 Radiation levels for Earth orbits 5 4.3 Methods for charged particle and phot
12、on irradiation6 5 Properties of spacecraft materials 6 5.1 General .6 5.2 Surface properties.6 5.3 Volume (bulk) properties 7 5.4 Measure of radiation action7 6 Requirements for simulation of space radiation7 6.1 Objective.7 6.2 Methodology (test) 7 6.3 Methodology for simulation that involves simul
13、ation of the type of radiation, its spectrum, and intensity 8 7 Radiation sources for simulation 10 7.1 Sources.10 7.2 Low-energy protons 10 7.3 Low-energy electrons .10 7.4 High-energy proton accelerators.10 7.5 High-energy electron accelerators 10 7.6 Ultraviolet radiation.10 8 Alternate simulatio
14、n method11 8.1 Methodology 11 8.2 Standard spacecraft orbits.11 Annex A (informative) Additional information .13 Annex B (informative) Depth dose 15 Annex C (informative) Accelerated tests 21 Bibliography22 BS ISO 15856:2010ISO 15856:2010(E) iv ISO 2010 All rights reservedForeword ISO (the Internati
15、onal 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 technical committees. Each member body interested in a subject for which a technical committee has been
16、 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 with the International Electrotechnical Commission (IEC) on all matters of electrotechnical standa
17、rdization. International Standards are drafted in accordance with the rules given in the ISO/IEC Directives, Part 2. The main task of technical committees is to prepare International Standards. Draft International Standards adopted by the technical committees are circulated to the member bodies for
18、voting. Publication as an International Standard requires approval by at least 75 % of the member bodies casting a vote. Attention is drawn to the possibility that some of the elements of this document may be the subject of patent rights. ISO shall not be held responsible for identifying any or all
19、such patent rights. ISO 15856 was prepared by Technical Committee ISO/TC 20, Aircraft and space vehicles, Subcommittee SC 14, Space systems and operations. BS ISO 15856:2010ISO 15856:2010(E) ISO 2010 All rights reserved vIntroduction The purpose of this International Standard is to establish guideli
20、nes for designing space systems that are highly reliable and will have long mission life spans. It is impossible to reproduce the space environment for ground testing of space system elements because of the variety and complexity of the environments and the effects on materials. The reliability of t
21、he test results depends on simulating the critical effects of the space environments for a particular mission. The main objectives of the simulation are to get test results that are satisfactory for the material behaviour in a space environment and to use existing radiation sources and methods avail
22、able in the test laboratory. Non-metallic materials used in space systems are affected by electrons and protons in a broad energy interval, electromagnetic solar radiation (both the near and the far ultraviolet radiation) and X-ray radiation. The response of non-metallic materials to radiation depen
23、ds on the type of radiation and energy that defines the ionization losses density, and the radiation response of materials depends on these losses. The radiation spectrum and chemical composition of materials define the absorbed dose distribution, especially in the near-the-surface layers. During th
24、e design of the space system, it is necessary to simulate long mission time in reasonable ground time. For this reason, it is necessary to perform accelerated radiation tests requiring the use of dose rates that may be of an order of magnitude greater than in the natural space environment. These hig
25、h dose rates can influence the effects on the properties of materials. Therefore, the main requirement for the correct simulation in radiation tests involves simulating the correct effects of materials in space by considering the type, spectrum (energy), and absorbed dose rate of the radiation. Simu
26、lation is complex because the various properties of materials may respond differently to the approximations of the natural space environment used for testing. In addition, various materials may respond differently to the same simulated space radiation environment. This is valid for different classes
27、 of materials such as polymeric and semiconductor materials. The space engineering materials in space environment are exposed not only to charged particles and electromagnetic solar radiation but also to a number of other environmental factors, e.g. atomic oxygen, deep vacuum, thermocycling, etc. Sy
28、nergistic interactions can significantly increase the material degradation, i.e. decrease the time of operation, but in certain cases (like solar absorptance variation under UV and protons) synergistic interaction can decrease the degradation. These effects are not well understood and have to be sim
29、ulated as far as possible. Space environment simulation at the combined exposure is a much more complicated procedure than the simulation of each factor separately. Development of corresponding standards, both for different factors and different classes of materials, will be provided in the followin
30、g stages of the standard set preparation for space environment simulation at on-ground tests of materials. This International Standard contains normative statements, recommended practices and informative parts. The term “shall” indicates a normative statement. BS ISO 15856:2010BS ISO 15856:2010INTER
31、NATIONAL STANDARD ISO 15856:2010(E) ISO 2010 All rights reserved 1Space systems Space environment Simulation guidelines for radiation exposure of non-metallic materials IMPORTANT The electronic file of this document contains colours which are considered to be useful for the correct understanding of
32、the document. Users should therefore consider printing this document using a colour printer. 1 Scope This International Standard is the first part of a series on space environment simulation for on-ground tests of materials used in space. This International Standard covers the testing of non-metalli
33、c materials exposed to simulated space radiation. Non-metallic materials include glasses, ceramics and polymer-metal composite materials such as metal matrix composites and laminated materials. This International Standard does not cover semiconductor materials used for electronic components. The typ
34、es of simulated radiation include charged particles (electrons and protons), solar ultraviolet radiation and soft X-radiation of solar flares. Synergistic interactions of the radiation environment are covered only for these natural, and some induced, environmental effects. This International Standar
35、d outlines the recommended methodology and practices for the simulation of space radiation effects on materials. Simulation methods are used to reproduce the effects of the space radiation environment on materials that are located on surfaces of space vehicles and behind shielding. This methodology
36、involves: a) the definition of the environment to be simulated using commonly accepted space environment models; b) the definition of the material properties under test or of concern in accordance with the specificity of degradation in the space environment, satellite-specific constraints determinat
37、ion, temperature conditions (constant values or cycled temperature mode), mechanical stress, charging, contamination, etc.; c) the selection of laboratory radiation simulation sources, energies and fluences that will be used to reproduce the kind of orbital radiation and mimic the orbital dose profi
38、les; d) the exposure techniques and procedures used to perform the laboratory simulation including contamination control, acceleration factors (dose rates), temperature control, vacuum levels and atmospheric effects. An alternative method using standard spacecraft orbits and environments is included
39、. This International Standard does not specify the design of material specimens, methods of measuring the properties of materials and characteristics of radiation sources, the design of vacuum systems and the preparation of test reports. The user should select designs and measurement methods based o
40、n the state of the art and the requirements of specific space systems and contracts. This International Standard does not include a list of hazards and safety precautions. The users are responsible for providing safe conditions based on national and local regulations. BS ISO 15856:2010ISO 15856:2010
41、(E) 2 ISO 2010 All rights reserved2 Normative references The following referenced documents are indispensable for the application of this document. For dated references, only the edition cited applies. For undated references, the latest edition of the referenced document (including any amendments) a
42、pplies. IEC 60544-2, Guide for determining the effects of ionizing radiation on insulating materials Part 2: Procedures for irradiation and test ASTM E490, Standard Solar Constant and Zero Air Mass Solar Spectral Irradiance Tables ASTM E512, Standard Practice for Combined, Simulated Space Environmen
43、t Testing of Thermal Control Materials with Electromagnetic and Particulate Radiation 3 Terms, definitions, abbreviated terms and acronyms 3.1 Terms and definitions For the purposes of this document, the following terms and definitions apply. 3.1.1 absorbed dose D amount of energy imparted by ionizi
44、ng radiation per unit mass of irradiated matter NOTE 1 The quotient of d by dm, where d is the mean energy imparted by ionizing radiation to matter of mass dm, is ddDm= NOTE 2 The special name of the unit for absorbed dose is the gray (Gy). 1 Gy = 1 Jkg1. 3.1.2 acceleration factor ratio of dose rate
45、 between simulation and expectation at space application for the same type of radiation 3.1.3 bremsstrahlung brake radiation photon radiation, continuously distributed in energy up to the energy of the incident particle radiation, emitted from a material due to deceleration of incident particle radi
46、ation within the material, mainly due to electrons 3.1.4 depth distribution criterion of absorbed dose ratio of the exponent index, , of the absorbed dose depth profile curve to the material density, NOTE The depth distribution criterion of absorbed dose is measured in square centimetres per gram. 3
47、.1.5 depth dose profile distribution of the absorbed dose through the depth of material 3.1.6 energy fluence total energy of ionizing radiation per unit area of the irradiated surface NOTE Energy fluence is measured in joules per square metre. BS ISO 15856:2010ISO 15856:2010(E) ISO 2010 All rights r
48、eserved 33.1.7 galactic cosmic rays GCR high-energy-charged particle fluxes penetrating the heliosphere from local interstellar space ISO 15390, definition 2.1 3.1.8 heliosphere region surrounding the sun where the solar wind dominates the interstellar medium NOTE Also known as solar cavity. 3.1.9 i
49、onizing radiation any type of radiation consisting of charged particles or uncharged particles or both, that, as a result of physical interaction, creates ions of opposite signs by either primary or secondary processes NOTE Charged particles could be positive or negative electrons, protons or other heavy ions, and uncharged particles could be X-rays, gamma rays, or neutrons. 3.1.10 linear energy transfer LET energy delivered by a charged particle passing through a substance and locally absorbed per unit length of path NOT
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