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ISO 16164:2015

Withdrawn

Withdrawn

A Withdrawn Standard is one, which is removed from sale, and its unique number can no longer be used. The Standard can be withdrawn and not replaced, or it can be withdrawn and replaced by a Standard with a different number.

View Superseded by

Space systems — Disposal of satellites operating in or crossing Low Earth Orbit

Available format(s)

Hardcopy , PDF , PDF 3 Users , PDF 5 Users , PDF 9 Users

Withdrawn date

14-07-2022

Superseded by

ISO 23312:2022

Language(s)

English

Published date

09-07-2015

€60.00
Excluding VAT

ISO 16164:2015 focuses on the post-mission disposal of spacecraft operating in, or crossing, Low Earth Orbit (LEO). The disposal of orbital launch stages operating in, or crossing, LEO is not dealt with in this International Standard.

Post-mission disposal of an Earth-orbiting spacecraft broadly means removing the spacecraft from its operational orbit after the end of mission, manoeuvring it to a region of space where it is less likely to interfere or collide with other operational spacecraft or with orbital debris and passivating.

For a spacecraft operating in, or crossing LEO, there are six disposal options that might be used to ensure its compliance with orbital debris mitigation requirements (as stated in ISO 24113). In order of preference, these are the following:

a) retrieving it and performing a controlled re-entry to recover it safely on the Earth;

b) manoeuvring it in a controlled manner into a targeted re-entry with a well-defined impact footprint on the surface of the Earth to limit the possibility of human casualty;

c) manoeuvring it in a controlled manner to an orbit that has a decay lifetime short enough to meet all orbital debris mitigation requirements;

d) augmenting its orbital decay by deploying a device so that the remaining orbital lifetime is short enough to meet all orbital debris mitigation requirements;

e) allowing its orbit to decay naturally, given that all orbital debris mitigation requirements will be met without the need for a disposal manoeuvre or other action;

f) manoeuvring it in a controlled manner to an orbit with a perigee altitude sufficiently above the LEO protected region (i.e. a graveyard orbit) that long-term perturbation forces do not cause it to re-enter the LEO protected region within 100 years.

ISO 16164:2015 specifies requirements for the following:

a) planning for disposal and passivation of spacecraft operating in LEO to ensure that final disposal is sufficiently characterized and that adequate propellant will be reserved for any propulsive manoeuvre required,

b) selecting a disposal orbit where the spacecraft will re-enter the Earth's atmosphere within the next 25-years, or where the spacecraft will not re-enter the protected region within the next 100-years, and

c) estimating, prior to launch, a 90 % or better probability of successfully executing the disposal manoeuvre.

Techniques for planning and executing space hardware disposal are provided that reflect current internationally accepted guidelines and consider current operational procedures and best practices.

DevelopmentNote
Supersedes ISO/DIS 16164. (07/2015)
DocumentType
Standard
Pages
11
PublisherName
International Organization for Standardization
Status
Withdrawn
SupersededBy

Standards Relationship
BS ISO 16164:2015 Identical

ISO/TR 20590:2017 Space systems - Debris mitigation design and operation manual for launch vehicle orbital stages
PD ISO/TR 18146:2015 Space systems. Space debris mitigation design and operation guidelines for spacecraft
ISO/TR 18146:2015 Space systems Space debris mitigation design and operation guidelines for spacecraft
PD ISO/TR 20590:2017 Space systems. Debris mitigation design and operation manual for launch vehicle orbital stages

ISO 27875:2010 Space systems Re-entry risk management for unmanned spacecraft and launch vehicle orbital stages
ISO 16127:2014 Space systems — Prevention of break-up of unmanned spacecraft
ISO 24113:2011 Space systems Space debris mitigation requirements
ISO 27852:2016 Space systems — Estimation of orbit lifetime
ISO 23339:2010 Space systems — Unmanned spacecraft — Estimating the mass of remaining usable propellant

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