ISO/TR 19473:2015

Space systems — Best practices for orbit elements at payload — LV separation

ISO/TR 19473:2015 provides the best practices for orbit elements at payload-LV separation. It includes orbit elements and calculation conditions, calculation method of orbit elements and their errors at elliptical orbit insertion of various payloads. The fit between the actual and expected values of orbit elements can be used as a criterion of commercial launch. There are many different sets of orbit elements. Each is best suited for a particular application. The traditionally used set of orbital elements is called the set of Keplerian elements. ISO/TR 19473:2015 gives the calculation method of Keplerian elements and the transformation method of all the other orbit elements, in order to satisfy different user's need. Affected by terrestrial gravitational perturbation, lunisolar gravitation perturbation and other factors, orbit elements change slowly after orbit injection. Orbit elements calculation methods after separation are not included in this Technical Report. The technical communication and specific progress for orbit elements is relatively easy to be agreed on by applying this ISO/TR 19473:2015, which can contribute to avoiding possible disputes.

Systèmes spatiaux — Meilleures pratiques pour les éléments en orbite à charge utile — Séparation LV

General Information

• Status: Published
• Publication Date: 01-Sep-2015
• 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: 6060 - International Standard published
• Completion Date: 02-Sep-2015

Relations

• Consolidated By: ISO 11127-2:2020 - Preparation of steel substrates before application of paints and related products — Test methods for non-metallic blast-cleaning abrasives — Part 2: Determination of particle size distribution
• Effective Date: 06-Jun-2022

Standards Content (Sample)

TECHNICAL ISO/TR
REPORT 19473
First edition
2015-09-01
Space systems — Best practices
for orbit elements at payload — LV
separation
Systèmes spatiaux — Meilleures pratiques pour les éléments en orbite
à charge utile — Séparation LV
Reference number
ISO/TR 19473:2015(E)
©
ISO 2015

---------------------- Page: 1 ----------------------
ISO/TR 19473:2015(E)

COPYRIGHT PROTECTED DOCUMENT
© ISO 2015, Published in Switzerland
All rights reserved. Unless otherwise specified, 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
Ch. de Blandonnet 8 • CP 401
CH-1214 Vernier, Geneva, Switzerland
Tel. [phone]
Fax [phone]
[e-mail]
www.iso.org
ii © ISO 2015 – All rights reserved

---------------------- Page: 2 ----------------------
ISO/TR 19473:2015(E)

Contents Page
Foreword .iv
Introduction .v
1 Scope . 1
2 Symbols and abbreviated terms . 1
2.1 Abbreviated terms . 1
2.2 Symbols . 2
3 Orbit elements and calculation conditions . 3
3.1 Orbit elements . 3
3.2 Data source . 5
3.2.1 General. 5
3.2.2 Guideline of correction about the external measurements . 5
3.2.3 External measurement data accuracy . 5
3.3 Coordinate systems and time systems . 5
3.3.1 Coordinate systems . 5
3.3.2 Time systems . 7
4 Calculation method of Keplerian elements . 7
4.1 Calculation method of orbit elements . 7
4.2 Transformation of other orbit elements . 9
4.2.1 Parameters of orbit size and shape . . 9
4.2.2 Parameters of orbit orientation .10
4.2.3 Parameters of satellite location .10
5 Calculation method of orbit elements error .10
Bibliography .12
© ISO 2015 – All rights reserved iii

---------------------- Page: 3 ----------------------
ISO/TR 19473:2015(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
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 on the meaning of ISO specific terms and expressions related to conformity
assessment, as well as information about ISO’s adherence to the WTO principles in the Technical
Barriers to Trade (TBT) see the following URL: Foreword - Supplementary information.
The committee responsible for this document is ISO/TC 20, Aircraft and space vehicles, Subcommittee
SC 14, Space systems and operations.
iv © ISO 2015 – All rights reserved

---------------------- Page: 4 ----------------------
ISO/TR 19473:2015(E)

Introduction
This Technical Report will provide a recommendatory method for post-launch assessment of the orbit
elements precision at separation, which is conductive to improving international communication effect
and reducing the risks from errors resulting from miscommunication. It can estimate the orbit elements
precision at separation, provide the reference for fuel capacity design of launch vehicle and spacecraft,
and then help to reduce the manufactory costs of rocket and payload.
© ISO 2015 – All rights reserved v

---------------------- Page: 5 ----------------------
TECHNICAL REPORT ISO/TR 19473:2015(E)
Space systems — Best practices for orbit elements at
payload — LV separation
1 Scope
This Technical Report provides the best practices for orbit elements at payload-LV separation. It
includes orbit elements and calculation conditions, calculation method of orbit elements and their
errors at elliptical orbit insertion of various payloads. The fit between the actual and expected values of
orbit elements can be used as a criterion of commercial launch.
There are many different sets of orbit elements. Each is best suited for a particular application. The
traditionally used set of orbital elements is called the set of Keplerian elements. This Technical Report
gives the calculation method of Keplerian elements and the transformation method of all the other orbit
elements, in order to satisfy different user’s need.
Affected by terrestrial gravitational perturbation, lunisolar gravitation perturbation and other factors,
orbit elements change slowly after orbit injection. Orbit elements calculation methods after separation
are not included in this Technical Report.
The technical communication and specific progress for orbit elements is relatively easy to be agreed on
by applying this Technical Report, which can contribute to avoiding possible disputes.
2 Symbols and abbreviated terms
2.1 Abbreviated terms
BIPM Bureau International des Poids et Mesures
CTP Conventional Terrestrial Pole
GAST Greenwich Apparent Sidereal Time
GMST Greenwich Mean Sidereal Time
GCRF Geocentric Celestial Reference Frame
GPS Global Positioning System
IERS International Earth Rotation and Reference System Service
IRM International Reference Meridian
ITRF International Terrestrial Reference Frame
ITRS International Terrestrial Reference System
LGEIF Launch Geocentric Equatorial Inertial Frame
LV Launch Vehicle
PZ90 Acronym of Russian Parametry Zemli 1990
SI International System of Units
© ISO 2015 – All rights reserved 1

---------------------- Page: 6 ----------------------
ISO/TR 19473:2015(E)

TAI International Atomic Time
TCG Geocentric Coordinate Time
TDT Terrestrial Dynamical Time
THF Topocentric Horizon Frame
UT1 Universal Time
UTC Coordinated Universal Time
WGS84 World Geodetic System, 1984
2.2 Symbols
a semimajor axis
a earth semimajor axis of terrestrial ellipsoid IERS used in ITRS
e
b semiminor axis
E eccentric anomaly
e eccentricity
GM earth gravitational parameter used in ITRS
e
h apogee altitude
a
h perigee altitude
p
i inclination
M mean anomaly
n mean motion of satellite
p semilatus rectum
r apogee radius
a
r perigee radius
p
S GAST at the time of payload – LV separation
0
T period
t time interval between the launch moment and the perigee passing
p
t time interval between the launch moment and the payload – LV separation
SEP
u argument of latitude
V velocity
V , V , V projection of velocity in LGEIF
x y z
x, y, z projection of position in LGEIF
α flattening of the earth
e
2 © ISO 2015 – All rights reserved

---------------------- Page: 7 ----------------------
ISO/TR 19473:2015(E)

θ true anomaly
φ geocentric latitude at launch point
e0
λ longitude at launch point
0
λ longitude of the ascending node in LGEIF
N
ω argument of perigee
ω angular velocity of the earth
e
Ω right ascension of the ascending node
3 Orbit elements and calculation conditions
3.1 Orbit elements
Six independent orbit elements describe the orbit of a satellite. Two elements describe orbit size and
shape, three elements describe orbit orientation, and one element describes orbit location.
Orbit size and shape parameters include the following:
a) semimajor axis;
b) eccentricity;
c) semiminor axis;
d) semilatus rectum;
e) perigee radius;
f) apogee radius;
g) perigee altitude;
h) apogee altitude;
i) period;
j) mean motion.
Orbit orientation parameters include the following:
a) inclination;
b) right ascension of the ascending node;
c) argument of perigee;
d) longitude of the ascending node.
Satellite location parameters include the following:
a) true anomaly;
b) eccentric anomaly;
c) mean anomaly;
d) time past perigee;
© ISO 2015 – All rights reserved 3

---------------------- Page: 8 ----------------------
ISO/TR 19473:2015(E)

e) time past ascending node;
f) argument of latitude.
The orbit elements are shown in Figure 1.
Figure 1 — Orbit elements
The orbit ellipse geometry is shown in Figure 2.
Satellite
Semilatus rectum
r
Semiminor axis
b
Radius
p
True anomaly
θ
Apogee
C P
Perigee
Empty focus
A
Geometric center
Focus
ae
r
a
r
p
Apogee radius
Perigee radius
a
Semimajor axis
Figure 2 — Ellipse geometry
4 © ISO 2015 – All rights reserved

---------------------- Page: 9 ----------------------
ISO/TR 19473:2015(E)

...