ISO 23339:2010
(Main)Space systems — Unmanned spacecraft — Estimating the mass of remaining usable propellant
Space systems — Unmanned spacecraft — Estimating the mass of remaining usable propellant
ISO 23339:2010 gives requirements for estimating the mass of the remaining usable propellant of an unmanned spacecraft in low Earth orbit (LEO) or geostationary Earth orbit (GEO), and for designing propellant measurement systems. It is applicable to spacecraft with either mono- or bi-propellant propulsion systems using liquid or gaseous chemical propellants, and is limited to such systems because they are the most common for spacecraft in LEOs and GEOs.
Systèmes spatiaux — Véhicules spatiaux non habités — Estimation de la masse d'ergols résiduels utilisable
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Standards Content (Sample)
INTERNATIONAL ISO
STANDARD 23339
First edition
2010-12-01
Space systems — Unmanned
spacecraft — Estimating the mass of
remaining usable propellant
Systèmes spatiaux — Véhicules spatiaux non habités — Estimation de
la masse d'ergols résiduels utilisable
Reference number
ISO 23339:2010(E)
©
ISO 2010
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ISO 23339:2010(E)
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ISO 23339:2010(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.
International Standards are drafted in accordance with the rules given in the ISO/IEC Directives, Part 2.
The main task of technical committees is to prepare International Standards. Draft International Standards
adopted by the technical committees are circulated to the member bodies for voting. Publication as an
International Standard requires approval by at least 75 % of the member bodies casting a vote.
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.
ISO 23339 was prepared by Technical Committee ISO/TC 20, Aircraft and space vehicles, Subcommittee
SC 14, Space systems and operations.
© ISO 2010 – All rights reserved iii
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ISO 23339:2010(E)
Introduction
This International Standard acts as one of the supporting technical standards for orbital debris mitigation.
For spacecraft disposal manoeuvres to be performed as planned, the estimation of available propellant mass
is essential. The aim of this International Standard is, through requirements for the estimation of remaining
propellant, to improve spacecraft disposal techniques and thereby mitigate orbital debris.
iv © ISO 2010 – All rights reserved
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INTERNATIONAL STANDARD ISO 23339:2010(E)
Space systems — Unmanned spacecraft — Estimating the
mass of remaining usable propellant
1 Scope
This International Standard gives requirements for estimating the mass of the remaining usable propellant of
an unmanned spacecraft in low Earth orbit (LEO) or geostationary Earth orbit (GEO), and for designing
propellant measurement systems. It is applicable to spacecraft with either mono- or bi-propellant propulsion
systems using liquid or gaseous chemical propellants, and is limited to such systems because they are the
most common for spacecraft in LEOs and GEOs.
2 Normative references
The following referenced documents are indispensable for the application of this document. For dated
references, only the edition cited applies. For undated references, the latest edition of the referenced
document (including any amendments) applies.
ISO 24113, Space systems — Space debris mitigation requirements
3 Terms and definitions
For the purposes of this document, the terms and definitions given in ISO 24113 and the following apply.
3.1
book-keeping method
method for determining fluid consumption by monitoring flow rates and the duration of propellant expenditure
periods
3.2
disposal manoeuvre
orbital manoeuvre that disposes of a spacecraft from the protected regions by either decreasing or increasing
the altitude of the spacecraft
3.3
PVT method
method for determining the remaining mass of gas by deriving density in a known volume from pressure and
temperature measurements
NOTE PVT: pressure, volume, temperature.
3.4
remaining usable propellant
propellant that remains in the propellant system and that is effective for attitude and orbit control manoeuvres
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ISO 23339:2010(E)
3.5
orbital debris
space debris
all man-made objects, including fragments and elements thereof, in Earth orbit or re-entering the atmosphere,
that are non-functional
3.6
spacecraft
system designed to perform specific tasks or functions in space
NOTE A spacecraft that can no longer fulfil its intended mission is considered non-functional. Spacecraft in reserve
or standby modes awaiting possible reactivation are considered functional.
4 Objectives
4.1 General
Orbital debris could cause substantial damage to other spacecraft, space stations, shuttles, etc. Orbital debris
include non-functioning payloads or used launch vehicle upper stages. The steady increase in orbital debris
increases the risk of collision, which creates more debris in orbit. Disposing of spacecraft at EOL (end of life)
reduces the risk of collision and increases safety. For the active disposal manoeuvre of a spacecraft at the
end of mission, there usually has to be enough propellant for the manoeuvre. The amount of propellant is
typically a key design parameter that determines the on-orbit lifetime.
In order to reserve enough usable propellant to ensure the success of disposal manoeuvres, the propellant
used over life shall be estimated with stated uncertainty and the remaining usable propellant shall be regularly
monitored with quantified uncertainty.
4.2 Objectives in estimating mass of remaining usable propellant
The prime objectives in estimating the mass of remaining usable propellant are
a) to ensure the successful disposal of the spacecraft, and
b) to drain the propellant system in order to remove a potential source of energy for creating additional
secondary debris caused by any primary debris impact.
For debris mitigation, successful venting of residual propellant is often required at end of life and tends to be
favoured by minimizing the amount of remaining propellant.
5 Requirements
5.1 Selection of estimation method
The estimation method (and allowances for estimation error) that best meets the objectives outlined in
Clause 4 shall be selected at an early stage of the spacecraft design phase and mission development. The
use of multiple estimation methods is recommended for redundancy and higher certainty. Annex A lists
estimation methods suitable for applicable spacecraf
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