ISO 16679:2015

INTERNATIONAL ISO
STANDARD 16679
First edition
2015-09-01
Space systems — Relative motion
analysis elements after LV/SC
separation
Systèmes spatiaux — Éléments d’analyse de mouvement relatif après
séparation du LV/SC
Reference number
ISO 16679:2015(E)
©
ISO 2015

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ISO 16679:2015(E)

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© ISO 2015, Published in Switzerland
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ISO 16679:2015(E)

Contents Page
Foreword .iv
Introduction .v
1 Scope . 1
2 Normative reference . 1
3 Terms and definitions . 1
4 Abbreviated terms . 1
5 Input for analysis . 2
6 General process . 2
7 Analysis principle . 2
8 Analysis method . 3
8.1 General . 3
8.2 Astrodynamics modelling . 3
8.3 Deviation analysis and identification . 3
8.4 Relative motion simulation . 3
8.4.1 Relative motion analysis period . 3
8.4.2 Deviation . 3
8.4.3 Relative position calculation . 4
8.4.4 Deviation margin of relative position . 4
8.5 Safety evaluation . 4
9 Analysis output . 4
Annex A (informative) Relative motion analysis model . 5
Annex B (informative) Typical combination of deviations . 6
Annex C (informative) Coordinate reference frames and variables . 7
Annex D (informative) **/***-***Preliminary (Final) relative motion analysis report
after separation . 8
Bibliography .10
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ISO 16679:2015(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
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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
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The committee responsible for this document is ISO/TC 20, Aircraft and space vehicles, Subcommittee
SC 14, Space systems and operations.
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ISO 16679:2015(E)

Introduction
Relative motion analysis predicts the relative distance after launch vehicle (LV) and spacecraft (SC)
separation. The analysis result offers support to the mission design and operation.
This International Standard provides LV and SC operators and manufacturers with specific elements
and procedures for performing relative motion analysis after LV and SC separation. The intent is to
regulate a common basis and offer a direction.
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INTERNATIONAL STANDARD ISO 16679:2015(E)
Space systems — Relative motion analysis elements after
LV/SC separation
1 Scope
This International Standard provides relative motion analysis elements after LV/SC separation,
including analysis input, analysis principle, analysis method and analysis output. It is applicable to the
mission design and verification for the prediction of relative motion after LV/SC separation.
This International Standard focuses on the relative motion between the objects involved in one launch
mission. It does not cover the issues about the collision avoidance between newly launched objects and
on-orbit ones.
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 14303, Space systems — Launch-vehicle-to-spacecraft interfaces
3 Terms and definitions
For the purposes of this document, the terms and definitions given in ISO 14303 and the following apply.
3.1
LV/SC separation
event of disconnection between LV/SC under the control of LV
3.2
relative motion analysis
analysis to predict the relative distance of spacecraft(s) to objects (end stage of LV and others generated
during the separation) after the LV/SC separation
3.3
separation velocity
relative speed to LV when separation is completed instantly
4 Abbreviated terms
LV launch vehicle
SC spacecraft
ICD interface control document
RMS root mean square
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ISO 16679:2015(E)

5 Input for analysis
The following information shall be included as analysis input.
a) Theoretical velocity, position, attitude of LV and (each) spacecraft at the separation moment, which
shall be presented in pre-determined coordinate system. Velocity and position vectors shall be
offered in the format as Vx, Vy, Vz, X, Y, Z. The potential reference frames are offered in Annex C.
b) Separation velocity, mass and inertia characteristics of separation bodies.
c) Deviations of LV and separation parts [mass, thrust, impulse, moment-inertial characteristics
(optional), tailed-effect, etc.].
d) Manoeuvres or other operations which shall affect LV end-stage orbit, related parameters and
sequences.
e) Manoeuvres or other operations which shall affect SC orbit, related parameters and sequences
(optio
...