BS ISO 16164-2015 Space systems Disposal of satellites operating in or crossing Low Earth Orbit《空间系统 在或者跨越低地球轨道上运行的卫星处理》.pdf

《BS ISO 16164-2015 Space systems Disposal of satellites operating in or crossing Low Earth Orbit《空间系统 在或者跨越低地球轨道上运行的卫星处理》.pdf》由会员分享，可在线阅读，更多相关《BS ISO 16164-2015 Space systems Disposal of satellites operating in or crossing Low Earth Orbit《空间系统 在或者跨越低地球轨道上运行的卫星处理》.pdf（22页珍藏版）》请在麦多课文档分享上搜索。

1、BSI Standards PublicationBS ISO 16164:2015Space systems Disposalof satellites operating in orcrossing Low Earth OrbitBS ISO 16164:2015 BRITISH STANDARDNational forewordThis British Standard is the UK implementation of ISO 16164:2015.The UK participation in its preparation was entrusted to TechnicalC

2、ommittee ACE/68, Space systems and operations.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 correctapplication. The British Standar

3、ds Institution 2015. Published by BSI StandardsLimited 2015ISBN 978 0 580 69951 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 July 2015.Amendments

4、issued since publicationDate Text affectedBS ISO 16164:2015 ISO 2015Space systems Disposal of satellites operating in or crossing Low Earth OrbitSystmes spatiaux Disposition des satellites oprant dans ou cheval de lorbite terrestre basseINTERNATIONAL STANDARDISO16164First edition2015-07-01Reference

5、numberISO 16164:2015(E)BS ISO 16164:2015ISO 16164:2015(E)ii ISO 2015 All rights reservedCOPYRIGHT PROTECTED DOCUMENT ISO 2015, Published in SwitzerlandAll rights reserved. Unless otherwise specified, no part of this publication may be reproduced or utilized otherwise in any form or by any means, ele

6、ctronic 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 officeCh. de Blandonnet 8 CP 401CH-1214 Verni

7、er, Geneva, SwitzerlandTel. +41 22 749 01 11Fax +41 22 749 09 47copyrightiso.orgwww.iso.orgBS ISO 16164:2015ISO 16164:2015(E)Foreword ivIntroduction v1 Scope . 12 Normative references 13 Terms and definitions . 24 Symbols and abbreviated terms . 25 LEO protected region . 26 Primary requirements 36.1

8、 General . 36.2 Ensuring execution of disposal actions 36.3 Priority in selection of a disposal option 46.4 Post-mission lifetime . 46.5 Time in graveyard orbit . 46.6 Extendable antennas in graveyard orbit . 46.7 Passivation 56.8 Probability of successful disposal. 57 Disposal planning requirements

9、 . 57.1 General . 57.2 Documentation of disposal plans 57.3 Procedure for planning for disposal . 67.3.1 General 67.3.2 Manoeuvring to a lower altitude orbit 67.3.3 Augmenting the decay by deploying a device . 67.3.4 Manoeuvring to a higher altitude orbit 77.4 Criteria for executing disposal actions

10、 . 77.5 Contingency planning . 78 Disposal manoeuvre requirements 88.1 Guidelines for calculating the disposal manoeuvre 88.2 Computing the decay orbit lifetime . 88.3 Computing the time in graveyard orbit 88.4 Estimating propellant reserves 88.5 Propellant depletion. 88.6 Determination whether the

11、disposal should be a controlled manoeuvre . 8Annex A (informative) Procedure to select a post-mission disposal option . 9Annex B (informative) Procedure for performing a post-mission disposal manoeuvre .10Bibliography .11 ISO 2015 All rights reserved iiiContents PageBS ISO 16164:2015ISO 16164:2015(E

12、)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 technical committees. Each member body interested in a subject for which a t

13、echnical 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 with the International Electrotechnical Commission (IEC) on all matters

14、 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 needed for the different types of ISO documents should be noted. This docum

15、ent 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 rights. ISO shall not be held responsible for identifying any or all suc

16、h 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 this document is information given for the convenience of users and does

17、 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 to Trade (TBT), see the following URL: Foreword Supplementary informati

18、on .The committee responsible for this document is ISO/TC 20, Space systems, Subcommittee SC 14, Space systems and operations.iv ISO 2015 All rights reservedBS ISO 16164:2015ISO 16164:2015(E)IntroductionThis International Standard prescribes requirements for planning, executing manoeuvres, and opera

19、tions for the post-mission disposal of a spacecraft operating in or crossing Low Earth Orbit. Included are requirements relating to the initiation and successful execution of these disposal actions. ISO 2015 All rights reserved vBS ISO 16164:2015BS ISO 16164:2015Space systems Disposal of satellites

20、operating in or crossing Low Earth Orbit1 ScopeThis International Standard focuses on the post-mission disposal of spacecraft operating in, or crossing, Low Earth Orbit (LEO). The disposal of orbital launch stages operating in, or crossing, LEO is not dealt with in this International Standard.Post-m

21、ission disposal of an Earth-orbiting spacecraft broadly means removing the spacecraft from its operational orbit after the end of mission, manoeuvring it to a region of space where it is less likely to interfere or collide with other operational spacecraft or with orbital debris and passivating.For

22、a spacecraft operating in, or crossing LEO, there are six disposal options that might be used to ensure its compliance with orbital debris mitigation requirements (as stated in ISO 24113). In order of preference, these are the following:a) retrieving it and performing a controlled re-entry to recove

23、r it safely on the Earth;b) manoeuvring it in a controlled manner into a targeted re-entry with a well-defined impact footprint on the surface of the Earth to limit the possibility of human casualty;c) manoeuvring it in a controlled manner to an orbit that has a decay lifetime short enough to meet a

24、ll orbital debris mitigation requirements;d) augmenting its orbital decay by deploying a device so that the remaining orbital lifetime is short enough to meet all orbital debris mitigation requirements;e) allowing its orbit to decay naturally, given that all orbital debris mitigation requirements wi

25、ll be met without the need for a disposal manoeuvre or other action;f) manoeuvring it in a controlled manner to an orbit with a perigee altitude sufficiently above the LEO protected region (i.e. a graveyard orbit) that long-term perturbation forces do not cause it to re-enter the LEO protected regio

26、n within 100 years.This International Standard specifies requirements for the following:a) planning for disposal and passivation of spacecraft operating in LEO to ensure that final disposal is sufficiently characterized and that adequate propellant will be reserved for any propulsive manoeuvre requi

27、red,b) selecting a disposal orbit where the spacecraft will re-enter the Earths atmosphere within the next 25-years, or where the spacecraft will not re-enter the protected region within the next 100-years, andc) estimating, prior to launch, a 90 % or better probability of successfully executing the

28、 disposal manoeuvre.Techniques for planning and executing space hardware disposal are provided that reflect current internationally accepted guidelines and consider current operational procedures and best practices.2 Normative referencesThe following documents, in whole or in part, are normatively r

29、eferenced in this document and are indispensable for 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 23339, Space systems Unmanned spacecraft Estimating the mass of rem

30、aining usable propellantINTERNATIONAL STANDARD ISO 16164:2015(E) ISO 2015 All rights reserved 1BS ISO 16164:2015ISO 16164:2015(E)ISO 24113:2011, Space systems Space debris mitigation requirementsISO 27852, Space systems Orbit lifetime estimationISO 27875, Space systems Re-entry risk management for u

31、nmanned spacecraft and launch vehicle orbital stages3 Terms and definitionsFor the purposes of this document, the terms and definitions given in ISO 24113 and the following apply.3.1ballistic coefficientproduct of the coefficient of drag and the average velocity-normal cross-sectional area divided b

32、y the mass (CdA/m)3.2decay phaseperiod that begins at the end of life of a spacecraft, when it has been placed into its disposal orbit, and ends when the spacecraft has performed a re-entryNote 1 to entry: Only applies for spacecraft performing re-entry.3.3disposal manoeuvreaction of moving a spacec

33、raft to its disposal orbit3.4disposal orbitorbit in which a spacecraft resides following the completion of its disposal manoeuvre3.5graveyard orbitdisposal orbit which locates a spacecraft outside of the protected region3.6passivationact of permanently depleting or making safe all remaining on-board

34、 sources of stored energy in a controlled sequence4 Symbols and abbreviated termsZ altitude above the surface of a spherical EarthdV delta velocityEOMDP end of mission disposal planGEO geostationary orbitLEO Low Earth OrbitSDMP space debris mitigation plan5 LEO protected regionThe LEO protected regi

35、on, defined by ISO 24113 and indicated in Figure 1, is the volume within a shell that extends from the surface of a spherical Earth (with a radius of 6 378 km) up to an altitude (Z) of 2 000 km.2 ISO 2015 All rights reservedBS ISO 16164:2015ISO 16164:2015(E)Orbits in the LEO protected region tend to

36、 have a wide range of starting inclinations. In addition, due to the proximity of the Earth, orbits tend to be strongly perturbed, which cause their parameters to quickly change from the initial conditions. The combination of these two effects means that, while some orbits are more popular than othe

37、rs, any orbit within this volume can be populated.15 15 Z = 2 000 kmZ = ZGEOZGEO- 200 kmZGEO+ 200 km13432Key1 Earth2 equator3 LEO region4 GEO regionZ altitude measured with respect to a spherical Earth whose radius is 6 378 kmZGEOaltitude of the geostationary orbit with respect to a spherical Earth

38、whose radius is 6 378 kmNOTE The dimensions in the figure are not to scale.Figure 1 View in the equatorial plane of Earth and the LEO and GEO protected regions (not to scale)6 Primary requirements6.1 GeneralIf it is possible within the constraints of the design of a spacecraft, the following sub-cla

39、uses define the primary requirements to be placed on the operator of the spacecraft.6.2 Ensuring execution of disposal actions6.2.1 To ensure that a disposal plan is sufficiently characterized and that adequate propellant is reserved for any propulsive manoeuvre required, an end of mission disposal

40、plan (EOMDP) shall be developed, maintained, and updated in all phases of a spacecraft mission.6.2.2 The EOMDP shall form part of the Space Debris Mitigation Plan (SDMP) for the mission. ISO 2015 All rights reserved 3BS ISO 16164:2015ISO 16164:2015(E)6.3 Priority in selection of a disposal option6.3

41、.1 The order of priority in choosing a spacecrafts disposal option is listed in ISO 24113:2011, 6.3.3.2. When selecting one of the six disposal options, i.e. a) to f), the decision shall be justified and documented in the EOMDP.NOTE A graveyard orbit is the least favourable option for disposing of a

42、 LEO spacecraft. The selection of a graveyard orbit is usually only attractive for LEO spacecraft in orbits whose perigee altitude is between 1 400 km and 2 000 km at end of mission. At lower perigee altitudes, disposal orbits with orbital lifetimes of less than 25 years would be more cost-effective

43、. Since missions with perigee altitudes between 1 400 km and 2 000 km are currently rare, the selection of this disposal option is infrequent.6.3.2 The EOMDP shall also include an estimate of the casualty risk posed by the uncontrolled re-entry of the spacecraft.6.3.3 If the casualty risk for uncont

44、rolled re-entry exceeds that specified by an approving agent, then either disposal option a) “retrieval and re-entry” or disposal option b) “targeted re-entry” or disposal option f) “moving to an orbit above the LEO protected region” shall be selected as the disposal method.6.3.4 Irrespective of whi

45、ch disposal option is selected during the design of the spacecraft, at end of mission, if disposal can be achieved through a more preferable option, that option shall be implemented.6.4 Post-mission lifetime6.4.1 If a spacecraft is placed into a disposal orbit with a perigee altitude below 2 000 km,

46、 for which atmospheric re-entry of the spacecraft is the eventual objective then, regardless of how it came to be in this orbit, the post-mission lifetime of this orbit shall be less than 25 years.This clarifies the meaning of ISO 24113:2011, 6.3.3.1 in which it states that a spacecraft operating in

47、 the LEO protected region, with either a permanent or periodic presence, shall limit its post-mission presence in the LEO protected region to a maximum of 25 years from the end of mission.NOTE The 25-year duration is an upper limit. It is preferable to reduce the decay phase duration to as small a t

48、ime period as possible.6.4.2 The consequence of a re-entering spacecraft impacting on the Earth can be controlled with ISO 27875.6.5 Time in graveyard orbit6.5.1 As specified in ISO 24113:2011, 6.3.3.2, if placed into a graveyard orbit, the spacecraft shall remain outside of, and not interfere with,

49、 the LEO protected region for a period of at least 100 years.6.5.2 When selecting disposal option f), a graveyard orbit, a long-term (at least 100-year) orbital perturbation analysis shall be conducted (and documented in the EOMDP) to ensure that the disposal orbit is not altered, particularly by solar and lunar gravitational forces, in such a way that the disposed spacecraft will enter the LEO or GEO protected regions within 100 years.6.6 Extendable antennas in graveyard orbitWhere possible, if a graveyard orbit has been selected,