M00001194
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ISO 11227 1st Edition, September 15, 2012 Space systems - Test procedure to evaluate spacecraft material ejecta upon hypervelocity impact
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Availability date: 07/13/2021
Description / Abstract:
This International Standard describes an experimental procedure
for assessing the behavior, under orbital debris or meteoroid
impacts, of materials that are intended to be used on the external
surfaces of spacecraft and launch vehicle orbital stages. This
International Standard provides a unified method by which to rank
materials. The ejecta production characteristics of different
materials are compared under standardized conditions in which test
parameters are fixed to one number. Optional tests with different
parameters are also useful for the proper selection of materials in
other conditions, and they could be performed as research
items.
This International Standard establishes the requirements to be
satisfied for the test methods in order to characterize the amount
of ejecta produced when a surface material is impacted by a
hypervelocity projectile. Its purpose is to evaluate the ratio of
ejecta total mass to projectile mass, and the size distribution of
the fragments. These are the necessary inputs for modeling the
amount of impact ejecta that as surface material might release
during its orbital lifetime, thereby helping to assess its
suitability for space use while mitigating the production of small
space debris.
The purpose of this International Standard is to provide data
that need to be taken into account in the selection of outer
spacecraft materials, thought selection is not based on these
criteria alone.
The experimental procedure defines
- the type of facility to be used,
- the size, velocity and type of projectile to be used,
- the evaluation of impact ejecta released,
- the reporting of test results, and
- the quality requirements to be used.
It is anticipated that this International Standard will be the
first of several test procedure standards aimed at characterizing
the release of small debris from external surfaces of spacecraft
and launch vehicle orbital stages as the result of interaction with
the space environment. It is applicable to spacecraft and launch
vehicles operating in all types of Earth orbits.