Space systems — Prevention of break-up of unmanned spacecraft

ISO 16127:2014 defines the requirements to reduce the risk of in-orbit break-up of unmanned spacecraft, both during and after their operational lives. The aim would be met by reducing the possibility of a break-up caused by an unplanned internally caused event and by depleting to a safe level all the sources of stored energy at the end of a spacecraft's life. ISO 16127:2014 is designed for use in planning, verifying and implementing the prevention of break-up of a spacecraft. ISO 16127:2014 applies only to unmanned spacecraft operating in Earth orbit.

Systèmes spatiaux — Prévention de l'éclatement des navettes sans pilote

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Status
Withdrawn
Publication Date
12-Feb-2014
Current Stage
9599 - Withdrawal of International Standard
Completion Date
14-Jul-2022
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INTERNATIONAL ISO
STANDARD 16127
First edition
2014-02-15
Space systems — Prevention of break-
up of unmanned spacecraft
Systèmes spatiaux — Prévention de l’éclatement des navettes sans
pilote
Reference number
ISO 16127:2014(E)
©
ISO 2014

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ISO 16127:2014(E)

COPYRIGHT PROTECTED DOCUMENT
© ISO 2014
All 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 internet or an intranet, without prior
written permission. Permission can be requested from either ISO at the address below or ISO’s member body in the country of
the requester.
ISO copyright office
Case postale 56 • CH-1211 Geneva 20
Tel. + 41 22 749 01 11
Fax + 41 22 749 09 47
E-mail copyright@iso.org
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Published in Switzerland
ii © ISO 2014 – All rights reserved

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ISO 16127:2014(E)

Contents Page
Foreword .iv
Introduction .v
1 Scope . 1
2 Normative references . 1
3 Terms and definitions . 1
4 Implementation . 2
4.1 Design process. 2
4.2 Verification . 2
4.3 Prevention of break-ups until end of life . 3
4.4 Prevention of break-up after end of life. 3
5 Stored energy sources . 3
5.1 Systems storing energy . 3
5.2 Electrical systems . 4
5.3 Propulsion systems . 4
5.4 Pressurized systems . 5
5.5 Other energy sources . 5
Annex A (informative) Procedure for estimating break-up probability. 6
Bibliography . 9
© ISO 2014 – All rights reserved iii

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ISO 16127:2014(E)

Foreword
ISO (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 technical
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 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 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 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 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 related to conformity
assessment, as well as information about ISO’s adherence to the WTO principles in the Technical Barriers
to Trade (TBT) see the following URL: Foreword - Supplementary information
The committee responsible for this document is ISO/TC 20, Aircraft and space vehicles, Subcommittee
SC 14, Space systems and operations.
iv © ISO 2014 – All rights reserved

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ISO 16127:2014(E)

Introduction
An ever-increasing number of man-made items are orbiting the Earth and bring with them ever-
increasing risk of collisions. This can have implications on the operational requirements of both manned
and unmanned spacecraft.
One potential source of space debris is the break-up of unmanned spacecraft both during and after the
end of their operational lives. This break-up could be due either to external collisions or to internal
factors caused by the existence of stored energy sources onboard the spacecraft. A cloud of debris from
a single spacecraft having broken up poses a significantly greater threat of collision than the original
spacecraft.
This International Standard defines the requirements to reduce the probability of a spacecraft breaking
up, both during and after its operational life. It also defines the requirements for passivation of the
spacecraft, which is the process by which all sources of stored energy are removed.
© ISO 2014 – All rights reserved v

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INTERNATIONAL STANDARD ISO 16127:2014(E)
Space systems — Prevention of break-up of unmanned
spacecraft
1 Scope
This International Standard defines the requirements to reduce the risk of in-orbit break-up of
unmanned spacecraft, both during and after their operational lives. The aim would be met by reducing
the possibility of a break-up caused by an unplanned internally caused event and by depleting to a safe
level all the sources of stored energy at the end of a spacecraft’s life. This International Standard is
designed for use in planning, verifying, and implementing the prevention of break-up of a spacecraft.
This International Standard applies only to unmanned spacecraft operating in Earth orbit. It does not
apply to manned space vehicles or launch vehicle orbital stages. Additionally, it does not cover nuclear
power sources within spacecraft.
This International Standard is not applicable to fragmentation as a result of external particle impacts
(which includes fragmentations triggered by external particle impact but powered by internal energy
sources).
2 Normative references
The 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, the latest edition of the referenced document (including any amendments) applies.
ISO 14623, Space systems - Pressure vessels and pressurized structures — Design and operation
ISO 24638, Space systems — Pressure components and pressure system integration
ISO 24113:2011, Space systems — Space debris mitigation requirements
3 Terms and definitions
For the purposes of this document, the terms and definitions given in ISO 24113:2011 and the following
apply.
3.1
acquiring organization
organization that plans and manages the development and acquisition contracts for the space system
Note 1 to entry: The responsibilities of the acquiring organization include the engineering and technical aspects
of the space system’s design and operations.
3.2
break-up probability
combined probability of the occurrence of all anomalous events, excluding meteoroid or debris impact,
that leads to the generation of orbital debris
3.3
passivation
elimination of all stored energy on a space system to reduce the chance of break-up
Note 1 to entry: Typical passivation measures include venting or burning excess propellant, discharging batteries,
and relieving pressure vessels.
© ISO 2014 – All rights reserved 1

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ISO 16127:2014(E)

4 Implementation
4.1 Design process
In accordance with ISO 24113, the spacecraft shall be designed to prevent break-ups while in orbit, both
before end of life and after the end of life.
The spacecraft shall be designed to prevent break-ups while in orbit until its end of life, in accordance
with probability levels defined in ISO 24113:2011, 6.2.2.1, and to enable passivation before its end of life.
Calculations shall be performed to determine the accidental break-up probability. Annex A reports an
example of an acceptable detailed evaluation approach.
The design process and the definition of the operations (including operational and disposal phases)
shall prevent potential failures which could occur during operational life, but also after the end of life.
All onboard sources of stored energy, such as residual propellants, batteries, high-pressure vessels,
self-destructive devices, flywheels, and momentum wheels, shall be depleted or safed and permanently
deactivated once they are no longer required for the mission operation.
The spacecraft provider shall produce a break-up prevention plan. This plan shall be reviewed and
updated as part of the normal spacecraft design review process. The acquiring organization/operator
shall be involved with these design reviews and approve the proposed solutions. All management shall
be done in accordance with ISO 24113.
When producing the break-up prevention plan, a system level risk assessment approach shall be used.
Each source of stored energy shall be considered: what potential failure modes could result in an in-
orbit break-up of the spacecraft (including post-disposal phase) and what can be performed to mitigate
the risk in the design, operational, and disposal phases of the mission as well as after the end of life.
Annex A provides further details regarding producing the plan.
The plan shall be developed by considering each item containing stored energy. The design shall take
into account the following influences:
— the environmental extremes expected to be encountered during the operational life and following
passivation, but excluding re-entry phase;
— mechanical degradation during the mission and following passivation;
— chemical decomposition;
— the effect of potential failure modes of the spacecraft during the mission, and what effect they would
have on the ability to passivate the spacecraft.
The robustness of the design shall be confirmed during the design review process, to ensure that
adequate reliability and quality control has been performed to inhibit any failure that could lead to a
break-up event with a probability as defined in ISO 24113.
4.2 Verification
Throughout the ground phases of a mission, i.e. design, manufacture, AIT (Assembly, Integration,
and Test), and launch, the implementation of the break-up prevention plan shall be reviewed. All the
hardware and software designed specifically for the purpose of break-up prevention should be verified
either by test, demonstration, analysis, or simulation (in that order of preference).
2 © ISO 2014 – All rights reserved

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ISO 16127:2014(E)

4.3 Prevention of break-ups until end of life
4.3.1 Monitoring during operations
For the operations of the spacecraft, procedures should be defined to allow monitoring of the relevant
...

DRAFT INTERNATIONAL STANDARD ISO/DIS 16127
ISO/TC 20/SC 14 Secretariat: ANSI
Voting begins on Voting terminates on

2012-04-24 2012-09-24
INTERNATIONAL ORGANIZATION FOR STANDARDIZATION  •  МЕЖДУНАРОДНАЯ ОРГАНИЗАЦИЯ ПО СТАНДАРТИЗАЦИИ  •  ORGANISATION INTERNATIONALE DE NORMALISATION


Space systems — Prevention of break-up of unmanned
spacecraft
ICS 49.140













To expedite distribution, this document is circulated as received from the committee
secretariat. ISO Central Secretariat work of editing and text composition will be undertaken at
publication stage.
Pour accélérer la distribution, le présent document est distribué tel qu'il est parvenu du
secrétariat du comité. Le travail de rédaction et de composition de texte sera effectué au
Secrétariat central de l'ISO au stade de publication.



THIS DOCUMENT IS A DRAFT CIRCULATED FOR COMMENT AND APPROVAL. IT IS THEREFORE SUBJECT TO CHANGE AND MAY NOT BE
REFERRED TO AS AN INTERNATIONAL STANDARD UNTIL PUBLISHED AS SUCH.
IN ADDITION TO THEIR EVALUATION AS BEING ACCEPTABLE FOR INDUSTRIAL, TECHNOLOGICAL, COMMERCIAL AND USER PURPOSES, DRAFT
INTERNATIONAL STANDARDS MAY ON OCCASION HAVE TO BE CONSIDERED IN THE LIGHT OF THEIR POTENTIAL TO BECOME STANDARDS TO
WHICH REFERENCE MAY BE MADE IN NATIONAL REGULATIONS.
RECIPIENTS OF THIS DRAFT ARE INVITED TO SUBMIT, WITH THEIR COMMENTS, NOTIFICATION OF ANY RELEVANT PATENT RIGHTS OF WHICH
THEY ARE AWARE AND TO PROVIDE SUPPORTING DOCUMENTATION.
©  International Organization for Standardization, 2012

---------------------- Page: 1 ----------------------
ISO/DIS 16127

Copyright notice
This ISO document is a Draft International Standard and is copyright-protected by ISO. Except as permitted
under the applicable laws of the user’s country, neither this ISO draft nor any extract from it may be
reproduced, stored in a retrieval system or transmitted in any form or by any means, electronic,
photocopying, recording or otherwise, without prior written permission being secured.
Requests for permission to reproduce should be addressed to either ISO at the address below or ISO’s
member body in the country of the requester.
ISO copyright office
Case postale 56 • CH-1211 Geneva 20
Tel. + 41 22 749 01 11
Fax + 41 22 749 09 47
E-mail copyright@iso.org
Web www.iso.org
Reproduction may be subject to royalty payments or a licensing agreement.
Violators may be prosecuted.

ii © ISO 2012 – All rights reserved

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ISO 16127   (N617) Version: March 2012


Contents



1 Scope. 1
2 Normative references. 1
3 Definitions of terms . 1
4 Acronyms and Abbreviations . 2
4.1 Abbreviations.2
5 Implementation . 2
5.1 Design process .2
5.2 Verification .3
5.3 Prevention of break-ups until end of life .3
5.3.1 Monitoring during operations .3
5.3.2 Debris mitigation measures in the case of malfunction.3
5.4 Prevention of break-up after end of life.3
6 Stored energy sources. 4
6.1 Electrical systems.4
6.1.1 Batteries .4
6.2 Propulsion Systems.4
6.2.1 System design .4
6.2.2 Propulsion system passivation .4
6.2.3 Solid rocket motors.5
6.3 Pressurised systems.5
6.3.1 Heat pipes / fluid loops .5
6.4 Other energy sources.5
6.4.1 Rotating hardware.5
6.4.2 Other devices .5

Annex - A   Procedure for Estimating Break-up Probability 7
Bibliography 9
 iii

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ISO 16127   (N617) Version: March 2012

Foreward

ISO (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 technical 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 of electrotechnical standardization.
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 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 such patent
rights.
ISO XXXX was prepared by Technical Committee ISO/TC 20, AIRCRAFT AND SPACE
VEHICLES, Subcommittee SC 14, SPACE SYSTEMS AND OPERATIONS.


iv

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ISO 16127   (N617) Version: March 2012

Introduction

An ever increasing number of man made items are orbiting the Earth, and bring with them
ever increasing risk of collisions. This can have implications on the operational requirements
of both manned and unmanned spacecraft.

One potential source of space debris is the break-up of un-manned spacecraft both during
and after the end of their operational lives. This break-up could be due either to external
collisions, or to internal factors caused by the existence of stored energy sources onboard the
spacecraft. A cloud of debris from a single spacecraft having broken up, poses a significantly
greater threat of collision than the original spacecraft.

This standard defines the requirements to reduce the probability of a spacecraft breaking up,
both during and after its operational life. It also defines the requirements for passivation of the
spacecraft, which is the process by which all sources of stored energy are removed.




 v

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ISO 16127   (N617) Version: March 2012

Space systems — Prevention of break-up of unmanned
spacecraft

1 Scope

This standard defines the requirements to reduce the risk of on-orbit break-up of un-manned
spacecraft, both during and after their operational lives. The aim would be met by reducing
the possibility of a break-up caused by an unplanned internally-caused event and by depleting
to a safe level all the sources of stored energy at the end of a spacecraft’s life. This standard
is designed for use in planning, verifying and implementing the prevention of break-up of a
spacecraft.

This standard applies only to un-manned spacecraft operating in earth orbit. It does not apply
to manned space vehicles, or launch vehicle orbital stages. Additionally it does not cover
nuclear power sources within spacecraft.

The document excludes fragmentation as a result of external particle impacts including
fragmentations triggered by external particle impact but power by internal energy sources.

2 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) applies.

ISO 14623:2003, Space Systems – Pressure vessels and pressurised structures – Design
and operation

ISO 24638:2008, Space Systems – Pressure components and pressure system integration

ISO 21347:2005, Space systems – Fracture and damage control

ISO 24113:2011, Space systems – Space debris mitigation requirements

ISO 17666:2003, Space systems – Risk management

ISO 10795:2011, Space Systems – Programme management – Glossary of terms for use in
ISO standards for space systems and operations


3 Definitions of terms
For the purposes of this document, the terms and definitions given in ISO 24113:2010 and the
following apply.

3.1
acquiring organisation
The organization that plans and manages the development and acquisition contracts for the
space system
NOTE - The responsibilities of the acquiring organization include the engineering and
technical aspects of the space system’s design and operations.

3.2
break-up probability
The combined probability of the occurrence of all anomalous events, excluding meteoroid or
debris impact, that leads to the generation of orbital debris

1

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ISO 16127   (N617) Version: March 2012


3.3
passivation
The elimination of all stored energy on a space system to reduce the chance of break-up.
Typical passivation measures include venting or burning excess propellant, discharging
batteries and relieving pressure vessels.

4 Acronyms and Abbreviations
4.1 Abbreviations
The following abbreviations are used within this document

ISO International Organization for Standardization
AIT Assembly, Integration and Test

5 Implementation
5.1 Design process
In accordance with ISO24113, the spacecraft shall be designed to prevent break-ups whilst in
orbit, both before end of life and after the end of life.

The spacecraft shall be designed to prevent break-ups whilst in orbit until its end of life, in
accordance with probability levels defined in ISO24113 para 6.2.2.1, and to enable
passivation before its end of life. Calculations shall be performed to determine the accidental
break-up probability. Annex A (informative) reports an example of an acceptable detailed
evaluation approach.

The design process and the definition of the operations (including operational and disposal
phases) shall prevent potential failures which could occur during operational life, but also after
the end of life. All onboard sources of stored energy, such as residual propellants, batteries,
high-pressure vessels, self destructive devices, flywheels and momentum wheels shall be
depleted or safed and permanently deactivated once they are no longer required for the
mission operation.

The spacecraft provider shall produce a break-up prevention plan. This plan shall be reviewed
and updated as part of the normal spacecraft design review process. The acquiring
organisation / operator shall be involved with these design reviews and approve the proposed
solutions. All management shall be done in accordance with ISO:24113.

When producing the break-up prevention plan, a system level risk assessment approach shall
be used. Each source of stored energy shall be considered, what potential failure modes
could result in an on orbit break-up of the spacecraft (including post disposal phase), and
what can be performed to mitigate the risk, in the design, operational and disposal phases of
the mission, as well as after the end of life. Annex A provides further details regarding
producing the plan.

The plan shall be developed by considering each item containing stored energy. Industry best
practice shall be used when considering each source. The design shall take into account the
following influences: -

• The environmental extremes expected to be encountered during the operational life
and following passivation, but excluding re-entry phase.
• Mechanical degradation during the mission and following passivation
• Chemical decomposition
 2

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ISO 16127   (N617) Version: March 2012

• The effect of potential failure modes of the spacecraft during the mission, and what
effect they would have on the ability to passivate the spacecraft

The robustness of the design shall be confirmed during the design review process, to ensure
that adequate reliability and quality control has been performed to inhibit any failure that could
lead to a break-up event with a probability as defined in ISO24113.

5.2 Verification
Throughout the ground ph
...

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