ISO 16127:2014

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













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©  International Organization for Standardization, 2012

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ISO/DIS 16127

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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
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ISO 16127   (N617) Version: March 2012

Foreward

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International Standards are drafted in accordance with the rules given in the
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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.


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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.




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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
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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
...