ISO 14200:2012

Space environment (natural and artificial) — Guide to process-based implementation of meteoroid and debris environmental models (orbital altitudes below GEO + 2 000 km)

This International Standard specifies the common implementation process for meteoroid and debris environment models for risk assessment of spacecraft and launch vehicle orbital stages. This International Standard gives guidelines for the selection process of models for impact risk assessment and ensures the traceability of using models throughout the design phase of a spacecraft or launch vehicle orbital stage.

Environnement spatial (naturel et artificiel) — Lignes directrices pour une mise en oeuvre fondée sur les processus des modèles environnementaux des météoroïdes et des débris (altitudes d'orbite inférieures à GEO + 2 000 km)

General Information

• Status: Withdrawn
• Publication Date: 12-Nov-2012
• Withdrawal Date: 12-Nov-2012
• ICS: 49.140 - Space systems and operations
• Technical Committee: ISO/TC 20/SC 14 - Space systems and operations
• Drafting Committee: ISO/TC 20/SC 14 - Space systems and operations
• Current Stage: 9599 - Withdrawal of International Standard
• Completion Date: 01-Jun-2021

Relations

• Revised: ISO 14200:2021 - Space environment (natural and artificial) — Process-based implementation of meteoroid and debris environment models (orbital altitudes below GEO + 2 000 km)
• Effective Date: 23-Apr-2020

Standards Content (Sample)

INTERNATIONAL ISO
STANDARD 14200
First edition
2012-11-15
Space environment (natural and
artificial) — Guide to process-based
implementation of meteoroid and
debris environmental models (orbital
altitudes below GEO + 2 000 km)
Environnement spatial (naturel et artificiel) — Lignes directrices
pour une mise en oeuvre fondée sur les processus des modèles
environnementaux des météoroïdes et des débris (altitudes d’orbite
inférieures à GEO + 2 000 km)
Reference number
ISO 14200:2012(E)
©
ISO 2012

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ISO 14200:2012(E)

COPYRIGHT PROTECTED DOCUMENT
© ISO 2012
All rights reserved. Unless otherwise specified, no part of this publication may be reproduced or utilized in any form or by any
means, electronic or mechanical, including photocopying and microfilm, without permission in writing from either ISO at the
address below or ISO’s member body in the country of the requester.
ISO copyright office
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Published in Switzerland
ii © ISO 2012 – All rights reserved

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ISO 14200:2012(E)

Contents  Page
Foreword .iv
Introduction .v
1 Scope . 1
2  Normative reference . 1
3  Terms and definitions . 1
4  Abbreviated terms . 3
5  Guidelines for the implementation of meteoroid and space debris environmental models 4
5.1 Overview of the implementation concept . 4
5.2 Impact fluxes estimation into a project . 4
5.3 Meteoroid and debris model implementation procedure . 4
5.4 Capabilities of meteoroid and space debris environment models . 5
6  Traceability assurance . 5
6.1 Overview of traceability concept. 5
6.2 Assurance of traceability in a project . 5
7 International project . 5
Annex A (informative) Capability of meteoroid environment models . 6
Annex B (informative) Capability of space debris environment models . 8
Annex C (informative) Example of Comparison of Debris Flux Values among ORDEM2000,
MASTER-2005 and MASTER2009 .12
Bibliography .15
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ISO 14200:2012(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.
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 14200 was prepared by Technical Committee ISO/TC 20, Aircraft and space vehicles, Subcommittee
SC 14, Space systems and operations.
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ISO 14200:2012(E)

Introduction
Every spacecraft or launch vehicle orbital stage in an Earth orbit is exposed to a certain flux of
micrometeoroids and man-made space debris. Collisions with these particles take place with
hypervelocity. The impact risk is evaluated in the design phases of a spacecraft or the launch vehicle
orbital stage. Many meteoroid and space debris environment models have been studied and developed
which describe populations of meteoroids and/or space debris. These models can be used as interim
solutions for impact risk assessments and shielding design purposes. However, there are different
methods in existence for reproducing the observed environment by means of mathematical and physical
models of release processes, for propagating orbits of release products, and for mapping the propagated
environment onto spatial and temporal distributions of objects densities, transient velocities, and impact
fluxes. Until a specific standard for the space debris environment is defined, a common implementation
process of models should be indicated for impact risk assessment and design of a spacecraft.
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INTERNATIONAL STANDARD  ISO 14200:2012(E)
Space environment (natural and artificial) — Guide to
process-based implementation of meteoroid and debris
environmental models (orbital altitudes below GEO + 2
000 km)
1 Scope
This International Standard specifies the common implementation process for meteoroid and debris
environment models for risk assessment of spacecraft and launch vehicle orbital stages. This International
Standard gives guidelines for the selection process of models for impact risk assessment and ensures the
traceability of using models throughout the design phase of a spacecraft or launch vehicle orbital stage.
2  Normative reference
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 17666:2003, Space systems — Risk management
3  Terms and definitions
For the purposes of this document, the terms and definitions given in ISO 17666 and the following apply.
3.1
engineering model
environment model that provides clear and concise information that engineers need
3.2
geostationary Earth orbit
Earth orbit having zero inclination and zero eccentricity; whose orbital period is equal to the Earth’s
sidereal rotation period
[SOURCE: ISO 24113:2011, definition 3.8]
3.3
geosynchronous Earth orbit
Earth orbit with an orbital period equal to the Earth’s sidereal rotation period
3.4
gravitational focusing
force of the Earth’s gravitational field that attracts meteoroids, changes their trajectories, and therefore
increases the flux
3.5
impact flux
number of impacts per unit area and per unit period
3.6
impact risk
risk of impact against meteoroids and debris on spacecraft
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ISO 14200:2012(E)

3.7
interplanetary
applicable regime of the meteoroid environment model from Earth with astronomical units (AU)
3.8
launch vehicle orbital stage
stage of a launch vehicle that is designed to achieve orbit
[SOURCE: ISO 24113:2011, definition 3.9]
3.9
low earth orbit
Earth orbit with an apogee altitude that does not exceed 2 000 km
3.10
mass density
mass per unit volume
3.11
meteoroid
particles of natural origin that result from the disintegration and fragmentation of comets and asteroids
which orbit round the sun
3.12
meteorid / (space) debris environment(al) model
tool that simulates realistic descriptions of the meteoroid and debris environment of Earth, and performs
risk assessment via flux predictions on user defined target orbit
3.13
space debris
〈orbital debris〉 man-made objects, including fragments and elements thereof, in Earth’s orbit or re-
entering the atmosphere, that are non-functional
[SOURCE: ISO 24113:2011, definition 3.17]
3.14
space system
system consisting of a space segment that includes a launch segment, spacecraft segment and a ground
segment with a tracking control segment and a mission segment
[SOURCE: ISO 23041:2007]
3.15
spacecraft
system designed to perform specific tasks or functions in space
[SOURCE: ISO 24113:2011, definition 3.18]
3.16
traceability
ability to trace the history, application or location of that which is under consideration
[SOURCE: ISO 9000:2005]
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ISO 14200:2012(E)

4  Abbreviated terms
AU Astronomical Units
CME Chemistry of Meteoroid Experiement
DISCOS Database and Information System Characterising Objects in Space
ESA European Space Agency
EuReCa EUropean REtrievable CArrier
GEO Geostationary Earth Orbit
GUI Graphical User Interface
HAX Haystack Auxiliary Radar
HST Hubble Space Telescope
HST-SA Hubble Space Telescope Solar Array
HST (SM1) Hubble Space Telescope (Service Mission 1)
HST (SM3B) Hubble Space Telescope (Service Mission 3B)
IDES Integrated Debris Evolution Suite
IMEM Interplanetary Meteoroid Engineering Model
ISO International Organization for Standardization
ISS International Space Station
LDEF Long Duration Exposure Facility
LEGEND LEO- to -GEO Environment Debris Model
LEO Low Earth Orbit
MASTER Meteoroid and Space Debris Terrestrial Environment Reference
MEM Meteoroid Engineering Model
MSFC Marshall Space Flight Center
NASA National Aeronautics and Space Administration
ORDEM Orbital Debris Engineering Model
PROOF Program for Radar and Observation Forecasting
SDMP Space Debris Mitigation Plan
SSN Space Surveillance Network
SSP Space Station Program
STS Space Transportation System
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ISO 14200:2012(E)

5  Guidelines for the implementation of meteoroid and space debris environ-
mental models
5.1  Overview of the implementation concept
5.1.1 If an impact flux assessment is required, it shall be performed in accordance with the risk
management process specified by ISO 17666.
5.1.2  The results of an impact flux assessment, the methodology used, and any assumptions made shall
be documented.
NOTE Impact flux assessments are sometimes performed in order to satisfy the requirements of a Space
Debris Mitigation Plan (SDMP). See Reference [1] for a description of the content of an SDMP.
5.2  Impact fluxes estimation into a project
When a spacecraft or launch vehicle orbital stage is designed or planned, the risk caused by impacts of
meteoroids and space debris shall be evaluated. For the risk assessment, impact fluxes of meteoroids
and space debris on the spacecraft or launch vehicle orbital stage shall be estimated.
5.3  Meteoroid and debris model implementation procedure
5.3.1  General
Impact fluxes on a spacecraft or launch vehicle orbital stage are calculated using a combination of design
data (i.e. configuration, orbit), meteoroid environment model and space debris environment model.
When the meteoroid environment model and space debris environment model applies to a spacecraft or
launch vehicle orbital stage design; the following procedure should be followed.
5.3.1.1  Step 1: Model selection agreement
The model(s) which is (are) applied to a spacecraft or launch vehicle orbital stage design is (are) selected
by mutual agreement between the customer and the supplier of the spacecraft or launch vehicle orbital
stage. Moreover, the traceability of the model(s) application shall be ensured.
5.3.1.2  Step 2: Model selection
To select a suitable environment model for the mission of a spacecraft or launch vehicle orbital stage,
the customer and the supplier should consider the capabilities of candidate models. Model capabilities
are described in 5.4.
When selecting a model, consideration should be given to the fact that environment models have
uncertainties which can lead to large differences in the flux results. It is recommended that the customer
and the supplier compare the flux results from several models.
5.3.1.3  Step 3: implementation of meteoroid and space debris environment models on a project
When implementing an environment model on a project there are several important considerations, such as
traceability of the development of the model, its maintenance, and user convenience. The following approaches
are recommended to estimate the impact fluxes on a spacecraft design and/or component design:
a) Engineering models (analysis codes) which are institutionally maintained by national agencies are
considered as candidates for applicable models for the design.
b) When a critical component is designed, the model which produces the maximum risk (the worst
case) is selected among candidate models.
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ISO 14200:2012(E)

The use of models other than those listed in 5.4 is permissible.
5.4  Capabilities of meteoroid and space debris environment models
5.4.1  Meteoroid environment models
Capabilities of meteoroid environment models are described in Annex A. Comparison of impact fluxes
among models are described in Reference [4].
5.4.2  Space debris environment models
Capabilities of space debris environment models are described in Annex B. Comparison of impact fluxes
among three engineering models, which are published by NASA and ESA, are described in References [5],
[6], [7]. An example of comparison impact flux among three models is described in Annex C for information.
6  Traceability assurance
6.1  Overview of traceability concept
Traceability of the meteoroid and space debris model application process shall be guaranteed in all
design phases of a spacecraft.
6.2  Assurance of traceability in a project
6.2.1  Risk assessments of meteoroid and space debris impacts
When risk assessments of meteoroid and space debris impacts are required, the following items shall be
recorded in each design phase of the spacecraft or launch vehicle orbital stage:
a) the justification for the selected spacecraft risk assessment model;
b) all input and output parameters and their values;
c) any assumptions made regarding the input design parameters, and the reasons for those assumptions;
d) any corrections made to output parameters, reasons for the corrections and any assumptions made,
and details of correction methods and correction results.
NOTE Output parameters can be corrected by applying a safety factor, life factor or margin of safety. Such
corrections can also take into account new information on the debris population. For example, since the publication
of space debris environment models, such as ORDEM2000 and MASTER-2005, there have been a number of
important debris generation events. These events could have a significant influence on a risk assessment.
6.2.2  Design Review
The contents of the items listed in 6.2.1, and their validity, shall be evaluated and confirmed by reviewers
during the Design Review (DR) in each phase of the design.
7 International project
For an international project, it is recommended that the following items be agreed amongst member
bodies before starting the project:
a) applied meteoroid and space debris environment model(s) to the project;
b) method of maintenance of the meteoroid and space debris environment model(s);
c) the procedure for impact risk assessment.
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ISO 14200:2012(E)

Annex A
(informative)

Capability of meteoroid environment models
A.1 Model overview
A.1.1  Grüen et al. model
[6]
The Grüen model assumes an isotropic meteoroid distribution which is based on lunar crater, zodiacal
light and in situ measurement data.
A.1.2  Divine model
[7]
The Divine model assumes a non-isotropic distribution which is based on five populations in particle
mass, inclination, eccentricity and perihelion distance.
A.1.3  Divine-Staubach model
[8]
The Divine-Staubach model is a follow-up of the Divine model, using new data from GALILEO and
ULYSSES dust detectors.
A.1.4  NASA SSP-30425 model
[9]
The SSP-30425 (Space Station Program Natural Environment Definition for Design) model describes
a space environment for ISS design.
A.1.5  IMEM model
Dikarev used an improved and controlled data set and applied refined mathematical methods in order to
describe three-dimensional distributions of o
...