ISO/TR 20590:2021
(Main)Space systems — Space debris mitigation design and operation manual for launch vehicle orbital stages
Space systems — Space debris mitigation design and operation manual for launch vehicle orbital stages
This document contains information on the design and operational practices for launch vehicle orbital stages for mitigating space debris. This document provides information to engineers on the requirements and recommendations in the space debris mitigation standards to reduce the growth of space debris by ensuring that launch vehicle orbital stages are designed, operated, and disposed of in a manner that prevents them from generating debris throughout their orbital lifetime.
Systèmes spatiaux — Lignes directrices de conception et de manœuvre des étages orbitaux de lanceurs pour réduire les débris spatiaux
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TECHNICAL ISO/TR
REPORT 20590
Second edition
2021-04
Space systems — Space debris
mitigation design and operation
manual for launch vehicle orbital
stages
Systèmes spatiaux — Lignes directrices de conception et de
manœuvre des étages orbitaux de lanceurs pour réduire les débris
spatiaux
Reference number
ISO/TR 20590:2021(E)
©
ISO 2021
---------------------- Page: 1 ----------------------
ISO/TR 20590:2021(E)
COPYRIGHT PROTECTED DOCUMENT
© ISO 2021
All rights reserved. Unless otherwise specified, or required in the context of its implementation, 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
CP 401 • Ch. de Blandonnet 8
CH-1214 Vernier, Geneva
Phone: +41 22 749 01 11
Email: copyright@iso.org
Website: www.iso.org
Published in Switzerland
ii © ISO 2021 – All rights reserved
---------------------- Page: 2 ----------------------
ISO/TR 20590:2021(E)
Contents Page
Foreword .v
Introduction .vi
1 Scope . 1
2 Normative references . 1
3 Terms and definitions . 1
4 Symbols and abbreviated terms . 1
5 System-level activities . 2
5.1 General . 2
5.2 Design for limiting the release of objects . 3
5.2.1 Intents of requirements in ISO 24113 . 3
5.2.2 Work breakdown . 3
5.2.3 Identification of released objects and design measures . 4
5.2.4 Monitoring during operation . 5
5.2.5 Preventing failure . 5
5.3 Break-up prevention . 5
5.3.1 Break-up caused by intentional behaviour, or stored energy . 5
5.3.2 Avoidance of collision . 7
5.4 Disposal manoeuvres at the end of operation . 7
5.4.1 Intents of requirements in ISO 24113 . 7
5.4.2 Work breakdown . 8
5.4.3 LEO mission . 8
5.4.4 GEO missions and other high-elliptical orbit missions . 9
5.5 Ground safety from re-entering objects .10
5.5.1 Intents of requirements in ISO 24113 .10
5.5.2 Work breakdown .10
5.5.3 Preventive measures .11
5.5.4 Risk detection: notification .13
5.5.5 Countermeasures: controlled re-entry and monitoring .13
5.6 Reliability and QA .13
6 Debris-related work in the development life cycle .13
6.1 General .13
6.2 Concept of debris-related work in each phase .13
6.3 Mission requirements analysis phase (pre-phase A) .18
6.3.1 General.18
6.3.2 Debris-related works .18
6.4 Feasibility phase (phase A) .18
6.5 Definition phase (phase B) .18
6.5.1 Work in phase B .18
6.5.2 Work procedure .19
6.6 Development phase (phase C) .19
6.7 Production phase (phase D) .20
6.7.1 Work in phase D .20
6.7.2 Qualification review .20
6.7.3 Launch service .20
6.8 Utilization phase (phase E) .20
6.9 Disposal phase (phase F) .20
7 System-level information.21
7.1 System design.21
7.2 Mission analysis for each launch mission .21
8 Subsystem/Component design and operation .22
8.1 General .22
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ISO/TR 20590:2021(E)
8.1.1 Scope .22
8.1.2 Debris-mitigation measures and subsystem-level actions for realizing them .22
8.2 Propulsion subsystem .23
8.2.1 Debris-related design .23
8.2.2 Information of propulsion subsystems .23
8.2.3 Information of component design .25
8.3 Guidance and control subsystem .26
8.3.1 Debris-related designs .26
8.3.2 Information of the guidance and control subsystem .27
8.4 Electric power-supply subsystem .27
8.4.1 Debris related design .27
8.4.2 Information of power subsystems .27
8.4.3 Information of component design .28
8.5 Communication subsystem .28
8.5.1 Debris-related designs .28
8.5.2 Design of communication subsystem .28
8.5.3 Information of component design .29
8.6 Structure subsystem .29
8.6.1 Design measures .29
8.6.2 Practices for structure subsystem .29
8.6.3 Information of component design .30
8.7 Range safety subsystem (self-destruct subsystem) .30
8.7.1 Debris-related designs .30
8.7.2 Information of command destruction subsystem .30
8.7.3 Information of component design .30
Bibliography .31
iv © ISO 2021 – All rights reserved
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ISO/TR 20590:2021(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 of the voluntary nature of standards, the meaning of ISO specific terms and
expressions related to conformity assessment, as well as information about ISO's adherence to the
World Trade Organization (WTO) principles in the Technical Barriers to Trade (TBT), see www .iso .org/
iso/ foreword .html.
This document was prepared by Technical Committee ISO/TC 20, Aircraft and space vehicles,
Subcommittee SC 14, Space systems and operations.
This second edition cancels and replaces the first edition (ISO/TR 20590:2017), which has been
technically revised.
The main changes compared to the previous edition are as follows:
— text has been updated to be aligned with ISO 24113:2019;
— information has been added that the total number of structural elements and orbital stages is
limited according to the number of payloads;
— information has been added that the ejection of slag debris from solid rocket motors is limited newly
in low Earth orbit in addition to GEO previously;
— information relating to collision avoidance against catalogued space objects has been improved;
— corresponding to the new requirement limiting the total probability of successful disposal to be at
least 0,9, the state of the art to confirm the compliance with that taken in the world space industries
and national agencies has been added;
— other information relating to the changes in ISO 24113 has been added.
Any feedback or questions on this document should be directed to the user’s national standards body. A
complete listing of these bodies can be found at www .iso .org/ members .html.
© ISO 2021 – All rights reserved v
---------------------- Page: 5 ----------------------
ISO/TR 20590:2021(E)
Introduction
Coping with debris is essential to preventing the deterioration of the orbital environment and ensuring
the sustainability of space activities. Effective actions can also be taken to ensure the safety of those on
the ground from re-entering objects that were disposed of from Earth orbit.
Recently, the orbital environment has become so deteriorated by debris that it is necessary to take
actions to mitigate the generation of orbital debris in design and operation of both spacecraft and the
launch vehicle orbital stages.
ISO 24113 and other ISO documents, introduced in Bibliography, were developed to encourage debris
mitigation activities.
In Clause 5, information about the major space debris mitigation requirements is provided.
In Clause 6, information about life-cycle implementation of space-debris-mitigation-related activities is
provided.
In Clause 7, the system level aspects stemming from the space debris mitigation requirements are
highlighted; while in Clause 8, the impacts at subsystem and component levels are detailed.
This document provides comprehensive information on the requirements and recommendations from
ISO documents for the design and operation of the launch vehicles.
vi © ISO 2021 – All rights reserved
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TECHNICAL REPORT ISO/TR 20590:2021(E)
Space systems — Space debris mitigation design and
operation manual for launch vehicle orbital stages
1 Scope
This document contains information on the design and operational practices for launch vehicle orbital
stages for mitigating space debris.
This document provides information to engineers on the requirements and recommendations in the
space debris mitigation standards to reduce the growth of space debris by ensuring that launch vehicle
orbital stages are designed, operated, and disposed of in a manner that prevents them from generating
debris throughout their orbital lifetime.
2 Normative references
The following documents are referred to in the text in such a way that some or all of their content
constitutes requirements 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 24113:2019, Space systems — Space debris mitigation requirements
3 Terms and definitions
For the purposes of this document, the terms and definitions given in ISO 24113 apply.
ISO and IEC maintain terminological databases for use in standardization at the following addresses:
— ISO Online browsing platform: available at https:// www .iso .org/ obp
— IEC Electropedia: available at http:// www .electropedia .org/
4 Symbols and abbreviated terms
CDR critical design review
CNES Centre National d'Études Spatiales
COPUOS Committee on the Peaceful Uses of Outer Space
CSpOC Combined Space Operations Center (USA)
DAS debris assessment software (NASA)
DRAMA debris risk assessment and mitigation analysis (ESA)
E expected number of casualties
c
EOMDP end-of-mission (operation) disposal plan
EOL end-of-life
ESA European Space Agency
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ISO/TR 20590:2021(E)
FDIR failure detection, isolation and recovery
FMEA failure mode and effect analysis
GEO geostationary Earth orbit
GTO geosynchronous transfer orbit
IADC Inter-Agency Space Debris Coordination Committee
JAXA Japan Aerospace Exploration Agency
LEO low Earth orbit
LV launch vehicle
NOTAM notice to airmen and notice to mariners
NM notice to mariners
PDR preliminary design review
QA quality assurance
QR qualification review
S/C spacecraft
SDMP space-debris-mitigation plan
SRR system requirement definition review
STELA semi-analytic tool for end of life analysis (CNES)
UN United Nations
5 System-level activities
5.1 General
To accomplish comprehensive activities for debris mitigation work, the following steps are considered:
a) Identifying debris related requirements, recommendations, and best practices.
b) Determining how to comply with requirements, recommendations, and best practices.
c) Applying debris mitigation measures early and throughout development and manufacturing to
assure sound debris mitigation capability in the final product.
d) Applying appropriate QA and qualification programs to ensure compliance with debris mitigation
requirements.
e) Applying appropriate procedures during operation/utilisation and disposal to implement proper
space debris mitigation.
This clause provides information useful for taking comprehensive action at the system level. More
detailed information for action at the subsystem and component levels is provided in Clause 8. The
following specific subjects are emphasized:
— limiting the release of objects into the Earth orbit;
2 © ISO 2021 – All rights reserved
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ISO/TR 20590:2021(E)
— preventing fragmentation in orbit;
— proper disposal at the end of operation;
— minimization of hazards on the ground from re-entering debris;
— collision avoidance during launch at least for inhabited systems;
— quality, safety, and reliability assurance.
5.2 Design for limiting the release of objects
5.2.1 Intents of requirements in ISO 24113
ISO 24113:2019, 6.1, requires avoiding the intentional release of space debris into Earth orbit during
normal operations, including general objects such as fasteners, fragments (larger than 1 mm) from
pyrotechnics, slag (larger than 1 mm) from solid rocket motors, etc.
The following objects are concerned:
a) objects released according to the mission requirements (not directly indicated in ISO 24113:2019,
6.1.1.1, though);
b) mission-related objects, such as yo-yo de-spinners, fasteners and other parts (ISO 24113:2019,
6.1.1.1);
c) total number of structural elements in multi-payloads launches and orbital stages. (ISO 24113:2019,
6.1.1.2);
d) fragments and combustion products from pyrotechnic devices (ISO 24113:2019, 6.1.2.1);
e) slag from solid motors (ISO 24113:2019, 6.1.2.2).
ISO 24113 implies that if objects are unavoidably released despite the requirements, the orbital lifetime
of such objects in LEO and the interference with GEO is limited as described in ISO 24113:2019, 6.1.1.3
(a typical example is the support structure utilized in a multiple payloads mission).
5.2.2 Work breakdown
Table 1 shows the work breakdown as delineated in ISO 24113 to prevent the release of debris.
Table 1 — Work breakdown for preventing the release of debris
Process Subjects Major work
Preventive measures Identification of re- a) Take preventive design to avoid releasing objects that would turn
leased objects and into space debris.
design measures
b) Minimise the total number of structural elements in multi-
payloads launches, orbital stages, etc.
c) If release is unavoidable, designers estimate the orbital lifetime
of released objects and check compliance with ISO 24113:2019,
6.1.1.3.
d) Apply pyrotechnic device which doesn’t eject fragments or
combustion product.
e) When applying the solid motors, the possibility of generation of
slag and its risk posed to environment will be assessed.
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ISO/TR 20590:2021(E)
Table 1 (continued)
Process Subjects Major work
Corrective actions Trouble shooting Reference: If an object would be released unexpectedly, it is investi-
gated and taken appropriate action to avoid repeating the release in
the following missions.
5.2.3 Identification of released objects and design measures
a) Mission-related objects
The following objects are concerned (ISO 24113:2019, 6.1.1.1):
1) nozzle closures for propulsion devices and certain types of igniters for solid motors, which are
ejected into space after ignition (particularly if their orbital lifetimes are longer than 25 years);
2) clamp bands that tie the S/C and launch vehicles;
3) structural elements used in multi-payloads launches, fragments and combustion products from
pyrotechnic devices, and slag from solid motors are excluded from ISO24113: 2019, 6.1.1.1, but
are mentioned in ISO24113: 2019, 6.1.1.2 and 6.1.2.
b) Structural elements in multi-payloads launches, orbital stages, etc. (ISO 24113:2019, 6.1.1.2)
ISO 24113:2019, 6.1.1.2 requires limiting the total number of orbital stages and “space objects” to
one for the launch of a single spacecraft and two for the launch of multiple spacecraft. Generally,
“space objects” means structural elements such as payload adaptors.
This requirement seems to prohibit to inject multiple stages in any instance. However, considering
the ultimate objective to minimize the number and mass of orbital objects, this requirement can
be understood in a slightly different way. For example, in the case that a three-stage LV is designed
to leave two stages in orbit during the launch of a single spacecraft, if the second stage has a very
short decay life, the third stage is relatively small, and that the total in-orbit collision risk and the
total re-entry casualty risk are demonstrably lower compared to the option of leaving one stage
in orbit, it is an option worth studying. Careful analysis is needed to confirm the benefit before
applying this requirement.
c) Fragments and combustion products from pyrotechnic devices (ISO 24113:2019, 6.1.2.1)
Adequately designed devices are selected to avoid the release of fragments or combustion products.
It is possible to apply parts that trap all fragments and combustion products larger than 1 mm
inside for segregation.
d) Combustion products from solid motors (ISO 24113:2019, 6.1.2.1)
1) It is preferable not to use an upper-stage with solid propulsion potentially leaving debris
in orbit (slag, throat elements), especially if the altitude of the orbit is higher than that of
inhabited systems, and if the solid propulsion system conception includes a dead-zone where
recirculating gases can concentrate some metalized slag which can be ejected in orbit.
2) It is taken into consideration that if a solid motor is fired to decrease the velocity of the orbital
object, to deorbit it for instance, as the particles velocity would increase with that of the orbital
object, leading to an increase in apogee of the particles.
e) Estimation of orbital lifetime (ISO 24113:2019, 6.1.1.3)
The orbital lifetime of released objects is assessed as specified in ISO 27852. ISO 27852 designates
acceptable analysis methodologies the user employs dependent upon the orbit regime. The available
simplified tools that are admissible to estimate the long-term orbital lifetime are introduced in
5.4.3.1.
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ISO/TR 20590:2021(E)
5.2.4 Monitoring during operation
The released objects, if they are large enough to be detected from the ground, can be confirmed by
ground-based space tracking facilities to ensure that they are released as expected and that their
orbital lifetimes are sufficiently short. The Space Situation Report provided by the US Combined Space
Operations Center (CSpOC https:// www .space -track .org/ auth/ login) provides a good reference.
5.2.5 Preventing failure
If objects are released unexpectedly, the origin of the objects can be identified to help prevent
recurrence in future missions. Because such phenomena can indicate a malfunction, the situation is
reviewed carefully, and appropriate action is taken to prevent further abnormal conditions.
5.3 Break-up prevention
5.3.1 Break-up caused by intentional behaviour, or stored energy
5.3.1.1 Intents of requirements in ISO 24113
ISO 24113:2019, 6.2 requires the prevention of break-ups caused by intentional beha
...
TECHNICAL ISO/TR
REPORT 20590
Second edition
Space systems - Space debris mitigation
design and operation manual for
launch vehicle orbital stages
PROOF/ÉPREUVE
Reference number
ISO/TR 20590:2021(E)
©
ISO 2021
---------------------- Page: 1 ----------------------
ISO/TR 20590:2021(E)
COPYRIGHT PROTECTED DOCUMENT
© ISO 2021
All rights reserved. Unless otherwise specified, or required in the context of its implementation, 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
CP 401 • Ch. de Blandonnet 8
CH-1214 Vernier, Geneva
Phone: +41 22 749 01 11
Email: copyright@iso.org
Website: www.iso.org
Published in Switzerland
ii PROOF/ÉPREUVE © ISO 2021 – All rights reserved
---------------------- Page: 2 ----------------------
ISO/TR 20590:2021(E)
Contents Page
Foreword .v
Introduction .vi
1 Scope . 1
2 Normative references . 1
3 Terms and definitions . 1
4 Symbols and abbreviated terms . 1
5 System-level activities . 2
5.1 General . 2
5.2 Design for limiting the release of objects . 3
5.2.1 Intents of requirements in ISO 24113 . 3
5.2.2 Work breakdown . 3
5.2.3 Identification of released objects and design measures . 4
5.2.4 Monitoring during operation . 5
5.2.5 Preventing failure . 5
5.3 Break-up prevention . 5
5.3.1 Break-up caused by intentional behaviour, or stored energy . 5
5.3.2 Avoidance of collision . 7
5.4 Disposal manoeuvres at the end of operation . 7
5.4.1 Intents of requirements in ISO 24113 . 7
5.4.2 Work breakdown . 8
5.4.3 LEO mission . 8
5.4.4 GEO missions and other high-elliptical orbit missions . 9
5.5 Ground safety from re-entering objects .10
5.5.1 Intents of requirements in ISO 24113 .10
5.5.2 Work breakdown .10
5.5.3 Preventive measures .11
5.5.4 Risk detection: notification .13
5.5.5 Countermeasures: controlled re-entry and monitoring .13
5.6 Reliability and QA .13
6 Debris-related work in the development life cycle .13
6.1 General .13
6.2 Concept of debris-related work in each phase .13
6.3 Mission requirements analysis phase (pre-phase A) .18
6.3.1 General.18
6.3.2 Debris-related works .18
6.4 Feasibility phase (phase A) .18
6.5 Definition phase (phase B) .18
6.5.1 Work in phase B .18
6.5.2 Work procedure .19
6.6 Development phase (phase C) .19
6.7 Production phase (phase D) .20
6.7.1 Work in phase D .20
6.7.2 Qualification review .20
6.7.3 Launch service .20
6.8 Utilization phase (phase E) .20
6.9 Disposal phase (phase F) .20
7 System-level information.21
7.1 System design.21
7.2 Mission analysis for each launch mission .21
8 Subsystem/Component design and operation .22
8.1 General .22
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ISO/TR 20590:2021(E)
8.1.1 Scope .22
8.1.2 Debris-mitigation measures and subsystem-level actions for realizing them .22
8.2 Propulsion subsystem .23
8.2.1 Debris-related design .23
8.2.2 Information of propulsion subsystems .23
8.2.3 Information of component design .25
8.3 Guidance and control subsystem .26
8.3.1 Debris-related designs .26
8.3.2 Information of the guidance and control subsystem .27
8.4 Electric power-supply subsystem .27
8.4.1 Debris related design .27
8.4.2 Information of power subsystems .27
8.4.3 Information of component design .28
8.5 Communication subsystem .28
8.5.1 Debris-related designs .28
8.5.2 Design of communication subsystem .28
8.5.3 Information of component design .29
8.6 Structure subsystem .29
8.6.1 Design measures .29
8.6.2 Practices for structure subsystem .29
8.6.3 Information of component design .30
8.7 Range safety subsystem (self-destruct subsystem) .30
8.7.1 Debris-related designs .30
8.7.2 Information of command destruction subsystem .30
8.7.3 Information of component design .30
Bibliography .31
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ISO/TR 20590:2021(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 of the voluntary nature of standards, the meaning of ISO specific terms and
expressions related to conformity assessment, as well as information about ISO's adherence to the
World Trade Organization (WTO) principles in the Technical Barriers to Trade (TBT), see www .iso .org/
iso/ foreword .html.
This document was prepared by Technical Committee ISO/TC 20, Aircraft and space vehicles,
Subcommittee SC 14, Space systems and operations.
This second edition cancels and replaces the first edition (ISO/TR 20590:2017), which has been
technically revised.
The main changes compared to the previous edition are as follows:
— text has been updated to be aligned with ISO 24113:2019;
— information has been added that the total number of structural elements and orbital stages is
limited according to the number of payloads;
— information has been added that the ejection of slag debris from solid rocket motors is limited newly
in low Earth orbit in addition to GEO previously;
— information relating to collision avoidance against catalogued space objects has been improved;
— corresponding to the new requirement limiting the total probability of successful disposal to be at
least 0,9, the state of the art to confirm the compliance with that taken in the world space industries
and national agencies has been added;
— other information relating to the changes in ISO 24113 has been added.
Any feedback or questions on this document should be directed to the user’s national standards body. A
complete listing of these bodies can be found at www .iso .org/ members .html.
© ISO 2021 – All rights reserved PROOF/ÉPREUVE v
---------------------- Page: 5 ----------------------
ISO/TR 20590:2021(E)
Introduction
Coping with debris is essential to preventing the deterioration of the orbital environment and ensuring
the sustainability of space activities. Effective actions can also be taken to ensure the safety of those on
the ground from re-entering objects that were disposed of from Earth orbit.
Recently, the orbital environment has become so deteriorated by debris that it is necessary to take
actions to mitigate the generation of orbital debris in design and operation of both spacecraft and the
launch vehicle orbital stages.
ISO 24113 and other ISO documents, introduced in Bibliography, were developed to encourage debris
mitigation activities.
In Clause 5, information about the major space debris mitigation requirements is provided.
In Clause 6, information about life-cycle implementation of space-debris-mitigation-related activities is
provided.
In Clause 7, the system level aspects stemming from the space debris mitigation requirements are
highlighted; while in Clause 8, the impacts at subsystem and component levels are detailed.
This document provides comprehensive information on the requirements and recommendations from
ISO documents for the design and operation of the launch vehicles.
vi PROOF/ÉPREUVE © ISO 2021 – All rights reserved
---------------------- Page: 6 ----------------------
TECHNICAL REPORT ISO/TR 20590:2021(E)
Space systems - Space debris mitigation design and
operation manual for launch vehicle orbital stages
1 Scope
This document contains information on the design and operational practices for launch vehicle orbital
stages for mitigating space debris.
This document provides information to engineers on the requirements and recommendations in the
space debris mitigation standards to reduce the growth of space debris by ensuring that launch vehicle
orbital stages are designed, operated, and disposed of in a manner that prevents them from generating
debris throughout their orbital lifetime.
2 Normative references
The following documents are referred to in the text in such a way that some or all of their content
constitutes requirements 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 24113:2019, Space systems — Space debris mitigation requirements
3 Terms and definitions
For the purposes of this document, the terms and definitions given in ISO 24113 apply.
ISO and IEC maintain terminological databases for use in standardization at the following addresses:
— ISO Online browsing platform: available at https:// www .iso .org/ obp
— IEC Electropedia: available at http:// www .electropedia .org/
4 Symbols and abbreviated terms
CDR critical design review
CNES Centre National d'Études Spatiales
COPUOS Committee on the Peaceful Uses of Outer Space
CSpOC Combined Space Operations Center (USA)
DAS debris assessment software (NASA)
DRAMA debris risk assessment and mitigation analysis (ESA)
E expected number of casualties
c
EOMDP end-of-mission (operation) disposal plan
EOL end-of-life
ESA European Space Agency
© ISO 2021 – All rights reserved PROOF/ÉPREUVE 1
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ISO/TR 20590:2021(E)
FDIR failure detection, isolation and recovery
FMEA failure mode and effect analysis
GEO geostationary Earth orbit
GTO geosynchronous transfer orbit
IADC Inter-Agency Space Debris Coordination Committee
JAXA Japan Aerospace Exploration Agency
LEO low Earth orbit
LV launch vehicle
NOTAM notice to airmen and notice to mariners
NM notice to mariners
PDR preliminary design review
QA quality assurance
QR qualification review
S/C spacecraft
SDMP space-debris-mitigation plan
SRR system requirement definition review
STELA semi-analytic tool for end of life analysis (CNES)
UN United Nations
5 System-level activities
5.1 General
To accomplish comprehensive activities for debris mitigation work, the following steps are considered:
a) Identifying debris related requirements, recommendations, and best practices.
b) Determining how to comply with requirements, recommendations, and best practices.
c) Applying debris mitigation measures early and throughout development and manufacturing to
assure sound debris mitigation capability in the final product.
d) Applying appropriate QA and qualification programs to ensure compliance with debris mitigation
requirements.
e) Applying appropriate procedures during operation/utilisation and disposal to implement proper
space debris mitigation.
This clause provides information useful for taking comprehensive action at the system level. More
detailed information for action at the subsystem and component levels is provided in Clause 8. The
following specific subjects are emphasized:
— limiting the release of objects into the Earth orbit;
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— preventing fragmentation in orbit;
— proper disposal at the end of operation;
— minimization of hazards on the ground from re-entering debris;
— collision avoidance during launch at least for inhabited systems;
— quality, safety, and reliability assurance.
5.2 Design for limiting the release of objects
5.2.1 Intents of requirements in ISO 24113
ISO 24113:2019, 6.1, requires avoiding the intentional release of space debris into Earth orbit during
normal operations, including general objects such as fasteners, fragments (larger than 1 mm) from
pyrotechnics, slag (larger than 1 mm) from solid rocket motors, etc.
The following objects are concerned:
a) objects released according to the mission requirements (not directly indicated in ISO 24113:2019,
6.1.1.1, though);
b) mission-related objects, such as yo-yo de-spinners, fasteners and other parts (ISO 24113:2019,
6.1.1.1);
c) total number of structural elements in multi-payloads launches and orbital stages. (ISO 24113:2019,
6.1.1.2);
d) fragments and combustion products from pyrotechnic devices (ISO 24113:2019, 6.1.2.1);
e) slag from solid motors (ISO 24113:2019, 6.1.2.2).
ISO 24113 implies that if objects are unavoidably released despite the requirements, the orbital lifetime
of such objects in LEO and the interference with GEO is limited as described in ISO 24113:2019, 6.1.1.3
(a typical example is the support structure utilized in a multiple payloads mission).
5.2.2 Work breakdown
Table 1 shows the work breakdown as delineated in ISO 24113 to prevent the release of debris.
Table 1 — Work breakdown for preventing the release of debris
Process Subjects Major work
Preventive measures Identification of re- a) Take preventive design to avoid releasing objects that would turn
leased objects and into space debris.
design measures
b) Minimise the total number of structural elements in multi-
payloads launches, orbital stages, etc.
c) If release is unavoidable, designers estimate the orbital lifetime
of released objects and check compliance with ISO 24113:2019,
6.1.1.3.
d) Apply pyrotechnic device which doesn’t eject fragments or
combustion product.
e) When applying the solid motors, the possibility of generation of
slag and its risk posed to environment will be assessed.
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Table 1 (continued)
Process Subjects Major work
Corrective actions Trouble shooting Reference: If an object would be released unexpectedly, it is investi-
gated and taken appropriate action to avoid repeating the release in
the following missions.
5.2.3 Identification of released objects and design measures
a) Mission-related objects
The following objects are concerned (ISO 24113:2019, 6.1.1.1):
1) nozzle closures for propulsion devices and certain types of igniters for solid motors, which are
ejected into space after ignition (particularly if their orbital lifetimes are longer than 25 years);
2) clamp bands that tie the S/C and launch vehicles;
3) structural elements used in multi-payloads launches, fragments and combustion products from
pyrotechnic devices, and slag from solid motors are excluded from ISO24113: 2019, 6.1.1.1, but
are mentioned in ISO24113: 2019, 6.1.1.2 and 6.1.2.
b) Structural elements in multi-payloads launches, orbital stages, etc. (ISO 24113:2019, 6.1.1.2)
ISO 24113:2019, 6.1.1.2 requires limiting the total number of orbital stages and “space objects” to
one for the launch of a single spacecraft and two for the launch of multiple spacecraft. Generally,
“space objects” means structural elements such as payload adaptors.
This requirement seems to prohibit to inject multiple stages in any instance. However, considering
the ultimate objective to minimize the number and mass of orbital objects, this requirement can
be understood in a slightly different way. For example, in the case that a three-stage LV is designed
to leave two stages in orbit during the launch of a single spacecraft, if the second stage has a very
short decay life, the third stage is relatively small, and that the total in-orbit collision risk and the
total re-entry casualty risk are demonstrably lower compared to the option of leaving one stage
in orbit, it is an option worth studying. Careful analysis is needed to confirm the benefit before
applying this requirement.
c) Fragments and combustion products from pyrotechnic devices (ISO 24113:2019, 6.1.2.1)
Adequately designed devices are selected to avoid the release of fragments or combustion products.
It is possible to apply parts that trap all fragments and combustion products larger than 1 mm
inside for segregation.
d) Combustion products from solid motors (ISO 24113:2019, 6.1.2.1)
1) It is preferable not to use an upper-stage with solid propulsion potentially leaving debris
in orbit (slag, throat elements), especially if the altitude of the orbit is higher than that of
inhabited systems, and if the solid propulsion system conception includes a dead-zone where
recirculating gases can concentrate some metalized slag which can be ejected in orbit.
2) It is taken into consideration that if a solid motor is fired to decrease the velocity of the orbital
object, to deorbit it for instance, as the particles velocity would increase with that of the orbital
object, leading to an increase in apogee of the particles.
e) Estimation of orbital lifetime (ISO 24113:2019, 6.1.1.3)
The orbital lifetime of released objects is assessed as specified in ISO 27852. ISO 27852 designates
acceptable analysis methodologies the user employs dependent upon the orbit regime. The available
simplified tools that are admissible to estimate the long-term orbital lifetime are introduced in
5.4.3.1.
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5.2.4 Monitoring during operation
The released objects, if they are large enough to be detected from the ground, can be confirmed by
ground-based space tracking facilities to ensure that they are released as expected and that their
orbital lifetimes are sufficiently short. The Space Situation Report provided by the US Combined Space
Operations Center (CSpOC https:// www .space -track .org/ auth/ login) provides a good reference.
5.2.5 Preventing failure
If objects are released unexpectedly, the origin of the objects can be identified to help prevent
recurrence in future missions. Because such phenomena can indicate a malfunction, the situation is
reviewed carefully, and appropriate action is taken to prevent further abnormal conditions.
5.3 Break-up prevention
5.3.1 Break-up caused by intentional behaviour, or stored energy
5.3.1.1 Intents of requirements in ISO 24113
ISO 24113:2019, 6.2 requires the prevention of break-ups caused by intentional behaviour, store
...
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