BS ISO 16126-2014 Space systems Assessment of survivability of unmanned spacecraft against space debris and meteoroid impacts to ensure successful post-mission disposal《空间系统 为确保成功后.pdf

1、BSI Standards PublicationBS ISO 16126:2014Space systems Assessmentof survivability of unmannedspacecraft against space debrisand meteoroid impacts toensure successful post-missiondisposalBS ISO 16126:2014 BRITISH STANDARDNational forewordThis British Standard is the UK implementation of ISO 16126:20

2、14.The UK participation in its preparation was entrusted to TechnicalCommittee ACE/68/-/1, Space systems and operations - Design,Engineering and Production.A list of organizations represented on this committee can beobtained on request to its secretary.This publication does not purport to include al

3、l the necessaryprovisions of a contract. Users are responsible for its correctapplication. The British Standards Institution 2014. Published by BSI StandardsLimited 2014ISBN 978 0 580 69946 7ICS 49.140Compliance with a British Standard cannot confer immunity fromlegal obligations.This British Standa

4、rd was published under the authority of theStandards Policy and Strategy Committee on 30 April 2014.Amendments issued since publicationDate Text affectedBS ISO 16126:2014 ISO 2014Space systems Assessment of survivability of unmanned spacecraft against space debris and meteoroid impacts to ensure suc

5、cessful post-mission disposalSystmes spatiaux valuation de la capacit de survie des vhicules spatiaux non habits face aux dbris spatiaux et aux impacts de mtorodes pour garantir une limination efficace daprs-missionINTERNATIONAL STANDARDISO16126First edition2014-04-01Reference numberISO 16126:2014(E

6、)BS ISO 16126:2014ISO 16126:2014(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 any form or by any means, electronic or mechanical, including photocopying, o

7、r 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 postale 56 CH-1211 Geneva 20Tel. + 41 22 749 01 11Fax + 41 22 749 09 47E-mail copy

8、rightiso.orgWeb www.iso.orgPublished in SwitzerlandBS ISO 16126:2014ISO 16126:2014(E) ISO 2014 All rights reserved iiiContents PageForeword iv1 Scope . 12 Normative references 13 Terms and definitions . 14 Abbreviated terms 35 Impact survivability assessment requirements 36 Impact survivability asse

9、ssment procedure . 36.1 General . 36.2 Definition of survivability requirement 36.3 Impact risk analysis 37 Procedure for performing a simple impact risk analysis 47.1 General . 47.2 Spacecraft operating parameters and architecture design . 57.3 Identification of critical components and surfaces . 5

10、7.4 Ballistic limits . 57.5 Failure probability analysis 57.6 Completion of analysis . 68 Procedure for performing a detailed impact risk analysis 68.1 General . 68.2 Spacecraft operating parameters and architecture design . 68.3 Identification of critical components. 68.4 Ballistic limits . 78.5 Fa

11、ilure probability analysis 88.6 Iteration of analysis. 8Annex A (informative) Supplementary information on the simple impact risk analysis procedure 10Annex B (informative) Ballistic limit equations 12Annex C (informative) Background information on hypervelocity impact testing and modelling 14Annex

12、D (informative) Method to calculate impact-induced Probability of No Failure .16Annex E (informative) Options for improving impact survivability .17Bibliography .19BS ISO 16126:2014ISO 16126:2014(E)ForewordISO (the International Organization for Standardization) is a worldwide federation of national

13、 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 established has the right to be represented on that committee. Internationa

14、l 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 standardization.The procedures used to develop this document and those intended fo

15、r its further maintenance are described in the ISO/IEC Directives, Part 1. In particular the different approval criteria needed 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.or

16、g/directives). 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. Details of any patent rights identified during the development of the document will be

17、 in the Introduction and/or on the ISO list of patent declarations received (see www.iso.org/patents). Any trade name used in this 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

18、 related to conformity assessment, as well as information about ISOs adherence to the WTO principles in the Technical Barriers to Trade (TBT) see the following URL: Foreword - Supplementary informationThe committee responsible for this document is ISO/TC 20, Aircraft and space vehicles, Subcommittee

19、 SC 14, Space systems and operations.iv ISO 2014 All rights reservedBS ISO 16126:2014INTERNATIONAL STANDARD ISO 16126:2014(E)Space systems Assessment of survivability of unmanned spacecraft against space debris and meteoroid impacts to ensure successful post-mission disposal1 ScopeThis International

20、 Standard defines requirements and a procedure for assessing the survivability of an unmanned spacecraft against space debris and meteoroid impacts to ensure the survival of critical components required to perform post-mission disposal. This International Standard also describes two impact risk anal

21、ysis procedures that can be used to satisfy the requirements. The procedures are consistent with those defined in References 1 and 2.This International Standard is part of a set of International Standards that collectively aim to reduce the growth of space debris by ensuring that spacecraft are desi

22、gned, operated, and disposed of in a manner that prevents them from generating debris throughout their orbital lifetime. All of the primary debris mitigation requirements are contained in a top-level International Standard.3The remaining International Standards, of which this is one, provide methods

23、 and processes to enable compliance with the primary requirements.2 Normative referencesThe 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 references, t

24、he latest edition of the referenced document (including any amendments) applies.ISO 10795:2011, Space systems Programme management and quality Vocabulary3 Terms and definitionsFor the purposes of this document, the terms and definitions given in ISO 10795:2011 and the following apply.3.1at-risk area

25、area of those parts of a surface on a component that are most vulnerable to impacts from space debris or meteoroidsNote 1 to entry: See A.1 for a more detailed explanation of at-risk area.3.2ballistic limitimpact-induced threshold of failure of a structureNote 1 to entry: A common failure threshold

26、is the critical size of an impacting particle at which perforation occurs. However, depending on the characteristics of the item being hit, failure modes other than perforation are also possible.3.3catastrophic collisioncollision leading to the destruction by fragmentation of a spacecraft ISO 2014 A

27、ll rights reserved 1BS ISO 16126:2014ISO 16126:2014(E)3.4critical componentcomponent whose failure would prevent the completion of an essential function on a spacecraft, such as post-mission disposal3.5critical surfacesurface of a component which, when damaged by impact, will cause the component to

28、fail3.6disposalactions performed by a spacecraft to permanently reduce its chance of accidental break-up, and to achieve its required long-term clearance of the protected regionsSOURCE: ISO 24113:2011, 3.4, modified3.7impact survivabilityability of a spacecraft to function after being exposed to the

29、 space debris or meteoroid environmentNote 1 to entry: A measure of impact survivability is the Probability of No Failure (PNF).3.8lethal collisioncollision leading to the loss of a critical component on a spacecraft3.9orbital lifetimeperiod of time from when a spacecraft achieves Earth orbit to whe

30、n it commences re-entrySOURCE: ISO 24113:2011, 3.12, modified3.10protected regionregion in space that is protected with regard to the generation of space debris to ensure its safe and sustainable use in the futureSOURCE: ISO 24113:2011, 3.143.11re-entryprocess in which atmospheric drag cascades dece

31、leration of a spacecraft (or any part thereof), leading to its destruction or return to EarthSOURCE: ISO 24113:2011, 3.15, modified3.12space debrisorbital debrisman-made objects, including fragments and elements thereof, in Earth orbit or re-entering the atmosphere, that are non-functionalSOURCE: IS

32、O 24113:2011, 3.173.13spacecraftsystem designed to perform specific tasks or functions in spaceSOURCE: ISO 24113:2011, 3.182 ISO 2014 All rights reservedBS ISO 16126:2014ISO 16126:2014(E)4 Abbreviated termsBLE ballistic limit equationHVI hypervelocity impactIADC Inter-Agency Space Debris Coordinatio

33、n CommitteeISO International Organization for StandardizationM/OD meteoroid/orbital debrisPNF Probability of No FailurePNP Probability of No PerforationS/C spacecraft5 Impact survivability assessment requirements5.1 During the design of a spacecraft, if an assessment is required to determine the sur

34、vivability of the spacecraft against space debris and meteoroid impacts for the purpose of achieving successful post-mission disposal, then the procedure in Clause 6 shall be followed.5.2 The results of an impact survivability assessment, the methodology used, and any assumptions made shall be appro

35、ved by the customer of the spacecraft.6 Impact survivability assessment procedure6.1 General6.2 and 6.3 describe a procedure for assessing the space debris and meteoroid impact survivability of a spacecraft.6.2 Definition of survivability requirement6.2.1 Specify a requirement for the survivability

36、of the spacecraft against space debris and meteoroid impacts for the purpose of achieving successful post-mission disposal.6.2.2 Express the survivability requirement in terms of a minimum allowable value of impact-induced Probability of No Failure, PNFmin, over the operational phase of the spacecra

37、ft.NOTE The operational phase of a spacecraft can be understood by referring to Annex B in Reference 3.6.3 Impact risk analysis6.3.1 Perform an impact risk analysis to determine and compare the impact-induced Probability of No Failure of the spacecraft, PNFs/c, with the minimum allowable value, PNFm

38、in.6.3.2 If PNFs/cvu; where vl, and vuare the lower and upper transition velocities between the three regions, respectively.For impacts whose velocities are either in the ballistic region or the hypervelocity region, Formula (B.2) is used. However, for impact velocities in the transition region, i.e

39、. between vland vu, linear interpolation is used to calculate the critical particle diameter, as follows:dvvvvdvvvvvdvpuulpllulpu,lim ,lim ,lim-= ()+ ()(B.3)References 2 and 6 provide comprehensive collections of BLEs including several that are specific to multiple walls. The limitations of the form

40、ulae are also clearly identified. ISO 2014 All rights reserved 13BS ISO 16126:2014ISO 16126:2014(E)Annex C (informative) Background information on hypervelocity impact testing and modellingC.1 Hypervelocity impact testingThe most straightforward method of deriving ballistic limit equations (BLEs) is

41、 to run a series of hypervelocity impact (HVI) experiments and to analyse and relate the damage data collected. BLEs shall span the impact velocity ranges of on-orbit impacts, which is approximately 1 kms1to 16 kms1for debris and 11 kms1to 17 kms1for meteoroids. Since laboratory hypervelocity launch

42、ers generally cannot accelerate projectiles above 10 km s1, it is sometimes necessary to combine the laboratory experiments with numerical simulations (e.g. using hydrocodes) to characterize BLEs over the full velocity range. Therefore, HVI tests are necessary to (a) obtain the reference points of B

43、LEs within the testable range and their verification, and (b) provide data for testing (i.e. verification, calibration) of the numerical codes (including models of material behaviour under HVI conditions).The hypervelocity launchers normally used for impact testing are the following: one-stage powde

44、r guns; two-stage light-gas guns; electromagnetic launchers; electrostatic launchers; blast (explosive) launchers.The following types of measurement technique can be employed: process optical registration (high frame-rate photography); process X-ray registration (if possible, multi-flash and multi-a

45、spect X-ray); registration of dynamic pressures, stresses, and impulse by gauges placed into target; registration of time of arrival by contact gages; post-test study of damage (craters, holes, etc.).Reference 2 provides information on several HVI launchers that are capable of simulating space debri

46、s and meteoroid impacts on targets. These have been put through a series of calibration tests, defined by the IADC, the purpose of which is to provide confidence in the results obtained.C.2 Hydrocode modellingIn order to perform numerical simulation of fast transient events, innovative numerical met

47、hods have been under development since the early 1950s. These so-called hydrocodes or wavepropagation codes allow the study of the time-resolved progression of acoustic and shock wave propagation due to impact, penetration, or detonation in fluids and solids. This class of codes is fundamentally bas

48、ed on a spatial and time discretization of the impacting bodies into small elements to which the first principles or conservation formulae for mass, momentum and energy are applied over small time steps. In hydrocodes, the first principles of physics are applied together with a formula of state to g

49、ive the 14 ISO 2014 All rights reservedBS ISO 16126:2014ISO 16126:2014(E)relationships between pressure, density, and internal energy. This provides a complete set of formulae governing hydrodynamic behaviour.Hydrocode modelling complements impact testing as a means of determining ballistic limit equations, particularly at the very high velocities that are characteristic of space debris and meteoroid impacts. Before applying a hydrocode for this purpose, its applicability need