1、BSI Standards PublicationBS ISO 16699:2015Space systems Disposal oforbital launch stagesBS ISO 16699:2015 BRITISH STANDARDNational forewordThis British Standard is the UK implementation of ISO 16699:2015.The UK participation in its preparation was entrusted to TechnicalCommittee ACE/68, Space system
2、s 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 Standards Institution 2015.Published
3、 by BSI Standards Limited 2015ISBN 978 0 580 73124 2ICS 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 2015.Amendments/corrigenda issued since p
4、ublicationDate T e x t a f f e c t e dBS ISO 16699:2015 ISO 2015Space systems Disposal of orbital launch stagesSystmes spatiaux limination des tages orbitaux de lanceursINTERNATIONAL STANDARDISO16699First edition2015-11-01Reference numberISO 16699:2015(E)BS ISO 16699:2015ISO 16699:2015(E)ii ISO 2015
5、 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, electronic or mechanical, including photocopying, or posting on the int
6、ernet 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 Vernier, Geneva, SwitzerlandTel. +41 22 749 01 11Fax +41 22 749 09 47copy
7、rightiso.orgwww.iso.orgBS ISO 16699:2015ISO 16699:2015(E)Foreword ivIntroduction v1 Scope . 12 Normative references 13 Terms and definitions . 14 Abbreviated terms 25 Primary requirements 25.1 Launch provider/Payload owner coordination 25.2 Selection of disposal option . 35.3 Disposal manoeuvre plan
8、ning and documentation 35.4 Reliability for disposal 45.5 Criteria for executing disposal action 45.6 Contingency planning . 45.7 Exceptions . 46 Disposal planning requirements . 56.1 Determination whether the disposal must be a controlled manoeuvre 56.2 Estimating orbit lifetime . 56.3 Computing th
9、e time in graveyard orbit region 5Bibliography 6 ISO 2015 All rights reserved iiiContents PageBS ISO 16699:2015ISO 16699:2015(E)ForewordISO (the International Organization for Standardization) is a worldwide federation of national standards bodies (ISO member bodies). The work of preparing Internati
10、onal 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, governmental and non-governmental, in liaison with IS
11、O, 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 for its further maintenance are described in the ISO/IEC Directives, Par
12、t 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.org/directives).Attention is drawn to the possibility that some of the e
13、lements 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 in the Introduction and/or on the ISO list of patent declarations rece
14、ived (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 related to conformity assessment, as well as information about ISOs adh
15、erence 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 SC 14, Space systems and operations.iv ISO 2015 All rights reservedBS I
16、SO 16699:2015ISO 16699:2015(E)IntroductionA launch vehicle stage plays a critical role in moving a spacecraft toward or into its final mission orbit. Once the spacecraft has been delivered to the desired orbit, the stage can be separated from the spacecraft. If the stage itself is in orbit and is de
17、activated at this point, it becomes another object added to the growing population space debris an uncontrolled object that may threaten operating satellites for the remainder of the stages orbit lifetime. And a launch vehicle stage may also be a source for large numbers of smaller threatening objec
18、ts if residual propellants, pressure vessels or other sources of stored energy explode or if it is involved in a collision with another object.This International Standard in one of several standards focused on minimizing the growth of space debris, and removing orbital launch stages from orbit or mo
19、ving them to non-threatening orbits at the end of their missions is an important component of this strategy. This International Standard provides guidance on how a spacecraft owner and a launch service provider can work together to develop spacecraft deployment options leading to removal of an orbit
20、al launch stage either by re-entering the stage into the atmosphere in a short time or by leaving the stage in or moving the stage to an orbit that does not intersect regions of heavy use by satellite missions for a very long time. This International Standard also calls for eliminating all sources o
21、f stored energy remaining in the stage prior to its final disposal (except in cases where the stage will execute a controlled re-entry into the atmosphere). ISO 2015 All rights reserved vBS ISO 16699:2015BS ISO 16699:2015Space systems Disposal of orbital launch stages1 ScopeThis International Standa
22、rd focuses on disposal of launch vehicle stages used during launch of spacecraft to be operated in space where the orbital launch stages are left in orbit after the spacecraft are released.End-of-mission disposal of launch vehicle orbital stages broadly means removing the stages from the protected r
23、egions of space (see ISO 24113) so as not to collide or otherwise interfere with the other users of those protected regions in the future. ISO 24113 also requires that “During the disposal phase, a spacecraft or launch vehicle orbital stage shall permanently deplete or make safe all remaining on-boa
24、rd sources of stored energy in a controlled sequence.” These “passivation” actions are typically either accomplished in the course of disposal, or immediately follow the disposal operations. In this document, the term “disposal actions” refers to both disposal manoeuvres and to passivation actions (
25、note: passivation actions are not required after the final manoeuvre leading to a controlled re-entry).ISO 24113 provides six options for spacecraft or orbital launch stage disposal. This International Standard specifies techniques for planning and executing disposal of orbital launch stages that ar
26、e consistent with ISO 24113 requirements, 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 referenced in this document and are indispensable for its
27、application. For dated references, only the edition cited applies. For undated references, the latest edition of the referenced document (including any amendments) applies.ISO 24113:2011, Space systems Space debris mitigation requirementsISO 27852, Space systems Estimation of orbit lifetimeISO 27875
28、, Space systems Re-entry risk management for unmanned spacecraft and launch vehicle orbital stages3 Terms and definitionsFor the purpose of this document, the terms and definitions given in ISO 24113:2011, and the following apply.3.1decay orbitorbit which will result in the re-entry of the space sys
29、tem within a specified time3.2decay phaseperiod that begins at the end of the operational phase of a space system, when it has been placed into its decay orbit, and ends when the space system has performed a re-entryNote 1 to entry: This only applies for space systems performing re-entry.3.3deorbit
30、manoeuvreaction of moving a space system to a new orbit that will cause the space system to re-enter the atmosphereINTERNATIONAL STANDARD ISO 16699:2015(E) ISO 2015 All rights reserved 1BS ISO 16699:2015ISO 16699:2015(E)3.4controlled re-entrymanoeuvring a space system in a controlled manner into a t
31、argeted re-entry with a well-defined impact footprint on the surface of the Earth to limit the possibility of human casualtyNote 1 to entry: This generally means that the object will re-enter the Earths atmosphere less than one orbit revolution from the time of initiation of the final deorbit manoeu
32、vre.3.5graveyard orbit regionorbit region outside of protected regions such as LEO and GEO3.6orbital launch stagelauncher orbital propulsive element that is discarded by the time the payload reaches orbit, usually only the last propulsive element3.7passivationelimination of all stored energy on a sp
33、ace system to reduce the chance of break-upNote 1 to entry: Typical passivation measures for spacecraft include venting or burning excess propellant, discharging batteries, and relieving pressure vessels (see ISO 16127 for examples).3.8uncontrolled re-entryre-entry where no specific manoeuvre is use
34、d to control the time and location of the re-entry pointNote 1 to entry: Therefore, the re-entry time and location of the space object are random and unknown.4 Abbreviated termsEOMDP end-of-mission disposal planGEO geostationary Earth orbitLEO low Earth orbitOLSDP orbital-launch-stage disposal plan5
35、 Primary requirementsControlled re-entry is the baseline approach; all other options should only be used if a controlled re-entry is not feasible.5.1 Launch provider/Payload owner coordinationThe spacecraft mission designer and the launch provider shall jointly design the launch phase of the mission
36、 to enable disposal of the orbital launch stage. Specifically:a) The spacecraft mission designer shall specify the desired injection conditions to the launch service provider.b) Using the information provided by the spacecraft mission designer, the launch service provider shall develop a candidate l
37、aunch and spacecraft injection scenario and for that scenario shall provide the final orbit parameters after final engine cut off and an estimate of the orbit lifetime of all orbital launch stages released during launch and injection of the owners spacecraft (see ISO 27852).c) The launch service pro
38、vider shall estimate the casualty expectation for an uncontrolled re-entry of all orbital stages provided by the launch service provider for which a controlled re-entry is not 2 ISO 2015 All rights reservedBS ISO 16699:2015ISO 16699:2015(E)planned. The casualty expectation for an uncontrolled re-ent
39、ry of each launch vehicle stage shall be computed as specified in ISO 27875.d) The launch service provider and the spacecraft mission designer shall iterate on the payload separation / injection conditions and select separation / injection conditions such that the spent stage can meet an appropriate
40、 disposal requirement as specified in ISO 24113. As an example, once the spacecraft mission designer has specified a desired injection orbit, the launch provider may then present options (if available) for orbital launch stage disposal. In some instances, the specified injection orbit may not lead t
41、o satisfactory disposal options. The launch provider and the spacecraft mission designer may then explore alternative injection orbits that offer better conditions for disposal of the orbital launch stage. If the spacecraft is to perform significant propulsive manoeuvres subsequent to injection (e.g
42、. orbit raising, inclination change, drift rate change, etc.), then an alternative injection orbit may yield equivalent results and be acceptable to the spacecraft mission designer. A typical example would be a trade-off between orbital inclination and perigee altitude for a transfer orbit injection
43、 in which the velocity required to achieve the spacecraft final orbit remains unchanged. This type of coordination can lead to mutually beneficial solutions in terms of mission objectives and orbital launch stage disposal.NOTE Responsibility for the orbital stage disposal remains with the LS-provide
44、r.5.2 Selection of disposal optiona) If the orbital launch stage after payload separation will be in an orbit with a perigee altitude of less than 2 000 km and a controlled re-entry is not planned, the casualty expectation for a random re-entry of the launch vehicle stage shall be computed by an acc
45、eptable method (e.g. see ISO 27875).b) For the re-entry of an orbital launch stage (or any part thereof), the maximum acceptable casualty risk shall be set in accordance with norms issued by approving agents.1) If the casualty expectation is lower than the value specified, the stage may be placed in
46、 a final orbit that will decay within 25 years (see ISO 27852).2) If the casualty expectation exceeds the value specified, the stage shall be either directed to re-enter and impact in a well-defined impact footprint on the surface of the Earth to limit the possibility of human casualty via a control
47、led deorbit manoeuvre or shall be moved to a graveyard orbit region.c) If the orbital launch stage is to be left in an orbit where disposal by orbit decay or controlled re-entry are not available options, the orbital launch stage shall be left in or moved to a final graveyard orbit region.In all cas
48、es except controlled re-entry, the stage shall be passivated after the nominal decay or sending to the graveyard orbit region is reached. Passivation is not required after successful completion of the final manoeuvre leading to a controlled re-entry. Should there be an anomaly and disposal manoeuvre
49、s cannot be accomplished, passivating the upper stage will lower the risk posed to operational systems.NOTE Some kinds of upper stages have negative temperature balance which is sufficient for passivation.5.3 Disposal manoeuvre planning and documentationAn orbital-launch-stage disposal plan (OLSDP) shall be developed, maintained and updated in all phases of mission and launch system design and shall be included in the overall end-of-mission disposal plan (EOMDP) defined in ISO 24113. The OLSDP shall include:a) details of the nominal orbit wher
