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ISO DIS 16164 2014 Edition, May 14, 2014 SPACE SYSTEMS - DISPOSAL OF SATELLITES OPERATING IN OR CROSSING LOW EARTH ORBIT
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Availability date: 07/14/2021
Description / Abstract:
This International Standard 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
dealt with in a separate, dedicated standard (see ISO 16699:-).
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:
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.
This International Standard specifies requirements for:
a) planning for disposal and passivation of spacecraft operating
in LEO to ensure that final disposal is sufficiently characterised
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.