oSIST prEN 16604-10:2023
(Main)Space sustainability - Space debris mitigation requirements (ISO 24113:2019, modified)
Space sustainability - Space debris mitigation requirements (ISO 24113:2019, modified)
This document defines the primary space debris mitigation requirements applicable to all elements of systems launched into, or passing through, near-Earth space, including launch vehicle orbital stages, operating spacecraft and any objects released as part of normal operations or disposal actions.
The requirements contained in this document are intended to reduce the growth of space debris by ensuring that spacecraft and launch vehicle orbital stages are designed, operated and disposed of in a manner that prevents them from generating debris throughout their orbital lifetime.
This document is the top-level standard in a family of standards addressing debris mitigation. It will be the main interface for the user, bridging between the primary debris mitigation requirements and the lower-level implementation standards that will ensure compliance.
This document does not cover launch phase safety for which specific rules are defined elsewhere.
This document identifies the clauses and requirements (including notes and clarifications) modified or added with respect to the standard ISO 24113, Space systems - Space debris mitigation requirements, Third edition 2019-07 (referred to as ISO 24113:2019) for application of the European Space standard based on ECSS.
Raumfahrtsysteme - Anforderungen zur Eindämmung des Weltraummülls (ISO 24113:2019, modifiziert)
Durabilité des activités spatiales - Exigences relatives à la réduction des débris spatiaux (ISO 24113:2019, modifiée)
Vesoljska vzdržljivost - Zahteve za zmanjšanje količine vesoljskih odpadkov (ISO 24113:2019, spremenjen)
General Information
Relations
Standards Content (Sample)
SLOVENSKI STANDARD
oSIST prEN 16604-10:2023
01-julij-2023
Vesoljska vzdržljivost - Zahteve za zmanjšanje količine vesoljskih odpadkov (ISO
24113:2019, spremenjen)
Space sustainability - Space debris mitigation requirements (ISO 24113:2019, modified)
Raumfahrtsysteme - Anforderungen zur Eindämmung des Weltraummülls (ISO
24113:2019, modifiziert))
Durabilité des activités spatiales - Exigences relatives à la réduction des débris spatiaux
(ISO 24113:2019, modifiée)
Ta slovenski standard je istoveten z: prEN 16604-10
ICS:
13.030.99 Drugi standardi v zvezi z Other standards related to
odpadki wastes
49.140 Vesoljski sistemi in operacije Space systems and
operations
oSIST prEN 16604-10:2023 en,fr,de
2003-01.Slovenski inštitut za standardizacijo. Razmnoževanje celote ali delov tega standarda ni dovoljeno.
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oSIST prEN 16604-10:2023
EUROPEAN STANDARD DRAFT
prEN 16604-10
NORME EUROPÉENNE
EUROPÄISCHE NORM
May 2023
ICS 49.140
Will supersede EN 16604-10:2009
English version
Space sustainability - Space debris mitigation
requirements (ISO 24113:2019, modified)
Développement durable de l'espace - Exigences Nachhaltigkeit im Weltraum - Space debris mitigation
relatives à la réduction des débris spatiaux (derivé de requirements (modified ISO 24113:2019)
l'ISO 24113:2019)
This draft European Standard is submitted to CEN members for enquiry. It has been drawn up by the Technical Committee
CEN/CLC/JTC 5.
If this draft becomes a European Standard, CEN and CENELEC members are bound to comply with the CEN/CENELEC Internal
Regulations which stipulate the conditions for giving this European Standard the status of a national standard without any
alteration.
This draft European Standard was established by CEN and CENELEC in three official versions (English, French, German). A
version in any other language made by translation under the responsibility of a CEN and CENELEC member into its own
language and notified to the CEN-CENELEC Management Centre has the same status as the official versions.
CEN and CENELEC members are the national standards bodies and national electrotechnical committees of Austria, Belgium,
Bulgaria, Croatia, Cyprus, Czech Republic, Denmark, Estonia, Finland, France, Germany, Greece, Hungary, Iceland, Ireland, Italy,
Latvia, Lithuania, Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Republic of North Macedonia, Romania, Serbia,
Slovakia, Slovenia, Spain, Sweden, Switzerland, Türkiye and United Kingdom.
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.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.
Warning : This document is not a European Standard. It is distributed for review and comments. It is subject to change without
notice and shall not be referred to as a European Standard.
CEN-CENELEC Management Centre:
Rue de la Science 23, B-1040 Brussels
© 2023 CEN/CENELEC All rights of exploitation in any form and by any means Ref. No. prEN 16604-10:2023 E
reserved worldwide for CEN national Members and for
CENELEC Members.
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Contents Page
European foreword . 3
Introduction . 5
1 Scope . 7
2 Normative references . 7
3 Terms and definitions . 7
4 Symbols and abbreviated terms . 11
4.1 Symbols . 11
4.2 Abbreviated terms . 11
5 Protected regions . 12
5.1 General. 12
5.2 LEO protected region . 12
5.3 GEO protected region . 12
6 Technical requirements . 13
6.1 Avoiding the intentional release of space debris into Earth orbit during normal
operations . 13
6.1.1 General. 13
6.1.2 Space debris from pyrotechnics and solid rocket motors . 13
6.2 Avoiding break-ups in Earth orbit . 13
6.2.1 Intentional break-up . 13
6.2.2 Accidental break-up caused by an on-board source of energy . 13
6.2.3 Accidental break-up caused by a collision . 14
6.3 Disposal of a spacecraft or launch vehicle orbital stage after the end of mission so as to
minimize interference with the protected regions . 14
6.3.1 Provisions for successful disposal . 14
6.3.2 Disposal to minimize interference with the GEO protected region . 15
6.3.3 Disposal to minimize interference with the LEO protected region . 15
6.3.4 Re-entry . 16
7 Planning requirements . 16
7.1 General. 16
7.2 Space debris mitigation plan . 16
Annex A (informative) Post-launch life cycle phases of a launch vehicle or spacecraft . 18
Bibliography . 20
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European foreword
This document (prEN 16604-10:2023) has been prepared by Technical Committee CEN/CLC/JTC 5
“Space”, the secretariat of which is held by DIN.
This document is currently submitted to the CEN Enquiry.
This document will supersede EN 16604-10:2019.
The main changes with respect to EN 16604-10:2019 are:
Adoption of ISO 24113, Space systems — Space debris mitigation requirements, Third edition 2019-07
(referred to as ISO 24113:2019) with following additional changes from ECSS:
— Addition of “Context information” w.r.t. ECSS
— Update of “Scope” with ECSS related information
— Update of Note to definition 3.8 “Earth orbit” and definition 3.20 “probability of sucessful disposal”
— Addition of Note 1 to requirement 7.2.2
This document has been developed to cover specifically space systems and will therefore have precedence
over any EN covering the same scope but with a wider domain of applicability (e.g.: aerospace).
Context information
This document outlines the clauses and the requirements of the standard ISO 24113, Space systems —
Space debris mitigation requirements, Third edition 2019-07 (referred to as ISO 24113:2019) with
modifications, additions, notes and clarifications implemented for application in ECSS.
The standard ISO 24113, Space systems — Space debris mitigation requirements has been developed by
ISO TC20/SC14. The key space debris mitigation requirements have been thoroughly discussed at
international level, agreed by the ISO members and published as standard ISO 24113.
Aiming at the development of world wide implementation standards dealing with space debris mitigation,
ECSS has proactively contributed to the preparation of ISO 24113.
ECSS decided to adopt and apply ISO 24133 with a minimum set of modifications, identified in the present
document, to account for the reference and applicable space debris mitigation documents existing in
Europe and of the needs of the ECSS members.
In 2012, ECSS adopted ISO 24113:2011 with a minimum set of modifications (as per ECSS-U-AS-10C),
which have been mostly incorporated in ISO 24113:2019. Moreover, ISO 24113:2019 represents a
significant improvement with respect to the previous ISO 24113:2011. Therefore, ECSS decided to adopt
and apply ISO 24113:2019 as it is, without any modifications of the requirements. However, in the present
document a few clarifications with respect to ISO 24113:2019 and its application are provided to account
for the needs of the ECSS members.
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A major clarification addressed in the present document is to stress that space debris mitigation
requirements apply to space objects in any bounded Earth orbit and apply also to space objects in
unbounded Earth orbits in case there is a risk for interference with the LEO and GEO protected regions.
Moreover, the present document provides clarifications about the evaluation of the probability of
successful disposal based on reliability analyses and about verification methods to be agreed with the
approving agents, accounting for existing ECSS implementation practices.
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Introduction
Space debris comprises all objects of human origin in Earth orbit or re-entering the atmosphere, including
fragments and elements thereof, that no longer serve a useful purpose. The growing population of these
objects poses an increasing hazard to mankind’s use of space. In response to this problem, there is
international consensus that space activities need to be managed to minimize collision risks among space
objects and casualty risks associated with atmospheric re-entry. This consensus is embodied in space
debris mitigation guidelines published by organizations such as the International Telecommunication
Union (ITU) [1], the Inter-Agency Space Debris Coordination Committee (IADC) [2][3] and the United
Nations (UN) [4]. The transformation of debris mitigation guidelines into engineering practice is a key
purpose of this document.
The importance of this document can be seen within the context of four UN treaties [5] that were
established under the United Nations Committee on the Peaceful Uses of Outer Space (UNCOPUOS) to
govern the involvement of nations in space activities. These are the Outer Space Treaty, the Liability
Convention, the Registration Convention and the Rescue Agreement. Through some of these treaties, a
Launching State has total liability for damage caused by its spacecraft or launch vehicle orbital stages (or
any parts thereof) on the surface of the Earth or to aircraft in flight, as well as in outer space where fault
can be proven.
All countries are encouraged to abide by these international agreements in order not to endanger or
constrain existing and future activities in space. A Launching State can choose to appoint licensing or
regulatory authorities to administer its approach for complying with the above-mentioned UN treaties. In
several Launching States, these authorities have implemented national legislation to enforce the UN
treaties. Such legislation can include the mitigation of space debris. Some Launching States meet their
obligations by appointing non-regulatory government bodies, such as national space agencies, to provide
the necessary guidelines or requirements, including those for space debris mitigation.
The general aim of space debris mitigation is to reduce the growth of space debris by ensuring that
spacecraft and launch vehicle orbital stages are designed, operated and disposed of in a manner that
prevents them from generating debris throughout their orbit lifetime. Another aim of space debris
mitigation is to ensure that space objects re-entering the Earth’s atmosphere cause no harm. These aims
are achieved by the following actions:
a) avoiding the intentional release of space debris into Earth orbit during normal operations;
b) avoiding break-ups in Earth orbit;
c) removing spacecraft and launch vehicle orbital stages from protected orbital regions after the end of
mission;
d) performing the necessary actions to minimize the risk of collision with other space objects;
e) reducing the risks associated with re-entry, e.g. to people, property and the Earth's environment.
Such actions are especially important for a spacecraft or launch vehicle orbital stage that has one or more
of the following characteristics:
— has a large collision cross-section;
— remains in orbit for many years;
— operates near manned mission orbital regions;
— operates in highly utilized regions, such as protected regions;
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— operates in regions of high debris population.
This document transforms these objectives into a set of high-level debris mitigation requirements. Methods
and processes to enable conformance with these requirements are provided in a series of lower-level
implementation standards.
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1 Scope
This document defines the primary space debris mitigation requirements applicable to all elements of
unmanned systems launched into, or passing through, near-Earth space, including launch vehicle orbital
stages, operating spacecraft and any objects released as part of normal operations.
The requirements contained in this document are intended to reduce the growth of space debris by
ensuring that spacecraft and launch vehicle orbital stages are designed, operated and disposed of in a
manner that prevents them from generating debris throughout their orbit lifetime. The requirements are
also intended to reduce the casualty risk on ground associated with atmospheric re-entry of space objects.
This document is the top-level standard in a family of standards addressing space debris mitigation. It is
the main interface for the user, bridging between the primary space debris mitigation objectives and a set
of lower level standards and technical reports that support conformance. The lower level documents
contain detailed requirements and implementation measures associated with the high-level requirements
in this document.
2 Normative references
There are no normative references in this document.
3 Terms and definitions
For the purposes of this document, the following terms and definitions 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/
3.1
approving agent
entity from whom approval is sought for the implementation of space debris (3.23) mitigation requirements
with respect to the procurement of a spacecraft (3.25), or its launch, or its operations in outer space, or its
safe re-entry (3.22), or a combination of those activities
EXAMPLE Regulatory or licensing authorities; national or international space agencies; other delegated
organizations.
3.2
break-up
event that completely or partially destroys an object and generates space debris (3.23)
3.3
casualty risk
expected number of casualties
situation expressed by the probability that at least one person is killed or seriously injured as a
consequence of an event
Note 1 to entry: The medical profession has defined a number of different injury scoring systems to distinguish the
severity of an injury. Broadly, a serious injury is one of such severity that hospitalization is required.
Note 2 to entry: The re-entry (3.22) of a spacecraft (3.25) is an example of an event.
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3.4
controlled re-entry
type of re-entry (3.22) where the time of re-entry is sufficiently controlled so that the impact of any
surviving debris on the surface of the Earth is confined to a designated area
Note 1 to entry: The designated area is usually an uninhabited region such as an ocean.
3.5
disposal
actions performed by a spacecraft (3.25) or launch vehicle orbital stage (3.13) to permanently reduce its
chance of accidental break-up (3.2) and to achieve its required long-term clearance of the protected regions
(3.21)
Note 1 to entry: Actions can include removing stored energy and performing post-mission orbital manoeuvres.
3.6
disposal manoeuvre
action of moving a spacecraft (3.25) or launch vehicle orbital stage (3.13) to a different orbit as part of its
disposal (3.5)
3.7
disposal phase
interval during which a spacecraft (3.25) or launch vehicle orbital stage (3.13) performs its disposal (3.5)
3.8
Earth orbit
bounded or unbounded Keplerian orbit with Earth at a focal point, or Lagrange point orbit which includes
Earth as one of the two main bodies
Note 1 to entry: The requirements in this document do not apply to space objects (3.24) in an unbounded Earth orbit
if, for at least 100 years after the space objects enter the unbounded Earth orbit:
— the assessed risk of the space objects interference with the LEO and GEO (3.11) protected regions (3.21), or
— the assessed risk of the space objects re-entry (3.22)
is less or equal to the corresponding threshold set by the approving agent.
3.9
end of life
instant when a spacecraft (3.25) or launch vehicle orbital stage (3.13):
a) is permanently turned off (nominally as it completes its disposal phase (3.7)),
b) re-enters the Earth’s atmosphere, or
c) can no longer be controlled by the operator
Note 1 to entry: See Annex A.
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3.10
end of mission
instant when a spacecraft (3.25) or launch vehicle orbital stage (3.13):
a) completes the tasks or functions for which it has been designed, other than its disposal (3.5),
b) becomes non-functional as a consequence of a failure, or
c) is permanently halted through a voluntary decision
Note 1 to entry: See Annex A.
3.11
geostationary Earth orbit
GEO
Earth orbit (3.8) having zero inclination, zero eccentricity, and an orbital period equal to the Earth's
sidereal rotation period
3.12
launch vehicle
(deprecated: launcher)
system designed to transport one or more payloads into outer space
3.13
launch vehicle orbital stage
complete element of a launch vehicle (3.12) that is designed to deliver a defined thrust during a dedicated
phase of the launch
...
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