BS ISO 14200-2012 Space environment natural and artificial Guide to process-based implementation of meteoroid and debris environmental models orbital altitudes below GEO + 2000 km《.pdf

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1、raising standards worldwideNO COPYING WITHOUT BSI PERMISSION EXCEPT AS PERMITTED BY COPYRIGHT LAWBSI Standards PublicationBS ISO 14200:2012Space environment (naturaland artificial) Guide toprocess-based implementationof meteoroid and debrisenvironmental models (orbitalaltitudes below GEO + 2 000km)B

2、S ISO 14200:2012 BRITISH STANDARDNational forewordThis British Standard is the UK implementation of ISO 14200:2012.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

3、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 correctapplication. The British Standards Institution 2012. Published by BSI StandardsLimited 2012ISBN 978 0

4、580 67955 1ICS 49.140Compliance with a British Standard cannot confer immunity fromlegal obligations.This British Standard was published under the authority of theStandards Policy and Strategy Committee on 31 December 2012.Amendments issued since publicationDate Text affectedBS ISO 14200:2012 ISO 20

5、12Space environment (natural and artificial) Guide to process-based implementation of meteoroid and debris environmental models (orbital altitudes below GEO + 2 000 km)Environnement spatial (naturel et artificiel) Lignes directrices pour une mise en oeuvre fonde sur les processus des modles environn

6、ementaux des mtorodes et des dbris (altitudes dorbite infrieures GEO + 2 000 km)INTERNATIONAL STANDARDISO14200First edition2012-11-15Reference numberISO 14200:2012(E)BS ISO 14200:2012ISO 14200:2012(E)ii ISO 2012 All rights reservedCOPYRIGHT PROTECTED DOCUMENT ISO 2012All rights reserved. Unless othe

7、rwise 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 either ISO at the address below or ISOs member body in the country of the requester.ISO copyright

8、 officeCase postale 56 CH-1211 Geneva 20Tel. + 41 22 749 01 11Fax + 41 22 749 09 47E-mail copyrightiso.orgWeb www.iso.orgPublished in SwitzerlandBS ISO 14200:2012ISO 14200:2012(E) ISO 2012 All rights reserved iiiContents PageForeword ivIntroduction v1 Scope . 12 Normative reference . 13 Terms and de

9、finitions . 14 Abbreviated terms 35 Guidelines for the implementation of meteoroid and space debris environmental models 45.1 Overview of the implementation concept . 45.2 Impact fluxes estimation into a project . 45.3 Meteoroid and debris model implementation procedure . 45.4 Capabilities of meteor

10、oid and space debris environment models . 56 Traceability assurance . 56.1 Overview of traceability concept. 56.2 Assurance of traceability in a project 57 International project 5Annex A (informative) Capability of meteoroid environment models 6Annex B (informative) Capability of space debris enviro

11、nment models 8Annex C (informative) Example of Comparison of Debris Flux Values among ORDEM2000, MASTER-2005 and MASTER2009 .12Bibliography .15BS ISO 14200:2012ISO 14200:2012(E)ForewordISO (the International Organization for Standardization) is a worldwide federation of national standards bodies (IS

12、O 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 established has the right to be represented on that committee. International organizations, gove

13、rnmental 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 standardization.International Standards are drafted in accordance with the rules given in the ISO/IEC D

14、irectives, 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 voting. Publication as an International Standard requires approval by at least 75 % of the member b

15、odies 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 such patent rights.ISO 14200 was prepared by Technical Committee ISO/TC 20, Aircraft and space vehic

16、les, Subcommittee SC 14, Space systems and operations.iv ISO 2012 All rights reservedBS ISO 14200:2012ISO 14200:2012(E)IntroductionEvery spacecraft or launch vehicle orbital stage in an Earth orbit is exposed to a certain flux of micrometeoroids and man-made space debris. Collisions with these parti

17、cles take place with hypervelocity. The impact risk is evaluated in the design phases of a spacecraft or the launch vehicle orbital stage. Many meteoroid and space debris environment models have been studied and developed which describe populations of meteoroids and/or space debris. These models can

18、 be used as interim solutions for impact risk assessments and shielding design purposes. However, there are different methods in existence for reproducing the observed environment by means of mathematical and physical models of release processes, for propagating orbits of release products, and for m

19、apping the propagated environment onto spatial and temporal distributions of objects densities, transient velocities, and impact fluxes. Until a specific standard for the space debris environment is defined, a common implementation process of models should be indicated for impact risk assessment and

20、 design of a spacecraft. ISO 2012 All rights reserved vBS ISO 14200:2012BS ISO 14200:2012Space environment (natural and artificial) Guide to process-based implementation of meteoroid and debris environmental models (orbital altitudes below GEO + 2 000 km)1 ScopeThis International Standard specifies

21、the common implementation process for meteoroid and debris environment models for risk assessment of spacecraft and launch vehicle orbital stages. This International Standard gives guidelines for the selection process of models for impact risk assessment and ensures the traceability of using models

22、throughout the design phase of a spacecraft or launch vehicle orbital stage.2 Normative referenceThe following documents, in whole or in part, are normatively referenced in this document and are indispensable for its application. For dated references, only the edition cited applies. For undated refe

23、rences, the latest edition of the referenced document (including any amendments) applies.ISO 17666:2003, Space systems Risk management3 Terms and definitionsFor the purposes of this document, the terms and definitions given in ISO 17666 and the following apply.3.1engineering modelenvironment model t

24、hat provides clear and concise information that engineers need3.2geostationary Earth orbitEarth orbit having zero inclination and zero eccentricity; whose orbital period is equal to the Earths sidereal rotation periodSOURCE: ISO 24113:2011, definition 3.83.3geosynchronous Earth orbitEarth orbit with

25、 an orbital period equal to the Earths sidereal rotation period3.4gravitational focusingforce of the Earths gravitational field that attracts meteoroids, changes their trajectories, and therefore increases the flux3.5impact fluxnumber of impacts per unit area and per unit period3.6impact riskrisk of

26、 impact against meteoroids and debris on spacecraftINTERNATIONAL STANDARD ISO 14200:2012(E) ISO 2012 All rights reserved 1BS ISO 14200:2012ISO 14200:2012(E)3.7interplanetaryapplicable regime of the meteoroid environment model from Earth with astronomical units (AU)3.8launch vehicle orbital stagestag

27、e of a launch vehicle that is designed to achieve orbitSOURCE: ISO 24113:2011, definition 3.93.9low earth orbitEarth orbit with an apogee altitude that does not exceed 2 000 km3.10mass densitymass per unit volume3.11meteoroidparticles of natural origin that result from the disintegration and fragmen

28、tation of comets and asteroids which orbit round the sun3.12meteorid / (space) debris environment(al) modeltool that simulates realistic descriptions of the meteoroid and debris environment of Earth, and performs risk assessment via flux predictions on user defined target orbit 3.13space debrisorbit

29、al debris man-made objects, including fragments and elements thereof, in Earths orbit or re-entering the atmosphere, that are non-functionalSOURCE: ISO 24113:2011, definition 3.173.14space systemsystem consisting of a space segment that includes a launch segment, spacecraft segment and a ground segm

30、ent with a tracking control segment and a mission segmentSOURCE: ISO 23041:20073.15spacecraftsystem designed to perform specific tasks or functions in spaceSOURCE: ISO 24113:2011, definition 3.183.16traceabilityability to trace the history, application or location of that which is under consideratio

31、nSOURCE: ISO 9000:20052 ISO 2012 All rights reservedBS ISO 14200:2012ISO 14200:2012(E)4 Abbreviated termsAU Astronomical UnitsCME Chemistry of Meteoroid ExperiementDISCOS Database and Information System Characterising Objects in SpaceESA European Space AgencyEuReCa EUropean REtrievable CArrierGEO Ge

32、ostationary Earth OrbitGUI Graphical User InterfaceHAX Haystack Auxiliary RadarHST Hubble Space TelescopeHST-SA Hubble Space Telescope Solar ArrayHST (SM1) Hubble Space Telescope (Service Mission 1)HST (SM3B) Hubble Space Telescope (Service Mission 3B)IDES Integrated Debris Evolution SuiteIMEM Inter

33、planetary Meteoroid Engineering ModelISO International Organization for StandardizationISS International Space StationLDEF Long Duration Exposure FacilityLEGEND LEO- to -GEO Environment Debris ModelLEO Low Earth OrbitMASTER Meteoroid and Space Debris Terrestrial Environment ReferenceMEM Meteoroid En

34、gineering ModelMSFC Marshall Space Flight CenterNASA National Aeronautics and Space AdministrationORDEM Orbital Debris Engineering ModelPROOF Program for Radar and Observation ForecastingSDMP Space Debris Mitigation PlanSSN Space Surveillance NetworkSSP Space Station ProgramSTS Space Transportation

35、System ISO 2012 All rights reserved 3BS ISO 14200:2012ISO 14200:2012(E)5 Guidelines for the implementation of meteoroid and space debris environ-mental models5.1 Overview of the implementation concept5.1.1 If an impact flux assessment is required, it shall be performed in accordance with the risk ma

36、nagement process specified by ISO 17666.5.1.2 The results of an impact flux assessment, the methodology used, and any assumptions made shall be documented.NOTE Impact flux assessments are sometimes performed in order to satisfy the requirements of a Space Debris Mitigation Plan (SDMP). See Reference

37、 1 for a description of the content of an SDMP.5.2 Impact fluxes estimation into a projectWhen a spacecraft or launch vehicle orbital stage is designed or planned, the risk caused by impacts of meteoroids and space debris shall be evaluated. For the risk assessment, impact fluxes of meteoroids and s

38、pace debris on the spacecraft or launch vehicle orbital stage shall be estimated.5.3 Meteoroid and debris model implementation procedure5.3.1 GeneralImpact fluxes on a spacecraft or launch vehicle orbital stage are calculated using a combination of design data (i.e. configuration, orbit), meteoroid

39、environment model and space debris environment model. When the meteoroid environment model and space debris environment model applies to a spacecraft or launch vehicle orbital stage design; the following procedure should be followed.5.3.1.1 Step 1: Model selection agreementThe model(s) which is (are

40、) applied to a spacecraft or launch vehicle orbital stage design is (are) selected by mutual agreement between the customer and the supplier of the spacecraft or launch vehicle orbital stage. Moreover, the traceability of the model(s) application shall be ensured.5.3.1.2 Step 2: Model selectionTo se

41、lect a suitable environment model for the mission of a spacecraft or launch vehicle orbital stage, the customer and the supplier should consider the capabilities of candidate models. Model capabilities are described in 5.4.When selecting a model, consideration should be given to the fact that enviro

42、nment models have uncertainties which can lead to large differences in the flux results. It is recommended that the customer and the supplier compare the flux results from several models.5.3.1.3 Step 3: implementation of meteoroid and space debris environment models on a projectWhen implementing an

43、environment model on a project there are several important considerations, such as traceability of the development of the model, its maintenance, and user convenience. The following approaches are recommended to estimate the impact fluxes on a spacecraft design and/or component design:a) Engineering

44、 models (analysis codes) which are institutionally maintained by national agencies are considered as candidates for applicable models for the design.b) When a critical component is designed, the model which produces the maximum risk (the worst case) is selected among candidate models.4 ISO 2012 All

45、rights reservedBS ISO 14200:2012ISO 14200:2012(E)The use of models other than those listed in 5.4 is permissible.5.4 Capabilities of meteoroid and space debris environment models5.4.1 Meteoroid environment modelsCapabilities of meteoroid environment models are described in Annex A. Comparison of imp

46、act fluxes among models are described in Reference 4.5.4.2 Space debris environment modelsCapabilities of space debris environment models are described in Annex B. Comparison of impact fluxes among three engineering models, which are published by NASA and ESA, are described in References 5, 6, 7. An

47、 example of comparison impact flux among three models is described in Annex C for information.6 Traceability assurance6.1 Overview of traceability conceptTraceability of the meteoroid and space debris model application process shall be guaranteed in all design phases of a spacecraft.6.2 Assurance of

48、 traceability in a project6.2.1 Risk assessments of meteoroid and space debris impactsWhen risk assessments of meteoroid and space debris impacts are required, the following items shall be recorded in each design phase of the spacecraft or launch vehicle orbital stage:a) the justification for the se

49、lected spacecraft risk assessment model;b) all input and output parameters and their values;c) any assumptions made regarding the input design parameters, and the reasons for those assumptions;d) any corrections made to output parameters, reasons for the corrections and any assumptions made, and details of correction methods and correction results.NOTE Output parameters can be corrected by applying a safety factor, life factor or margin of safety. Such corrections can also take into account new information on t