ISO 15862:2009
(Main)Space systems — Launch-vehicle-to-spacecraft flight environments telemetry data processing
Space systems — Launch-vehicle-to-spacecraft flight environments telemetry data processing
ISO 15862:2009 provides basic requirements for the measurement of the spacecraft flight environments generated by the launch vehicle, telemetry data processing and formats of analysis reports. ISO 15862:2009 defines the field and number of measurement parameters, the principles of data processing, the format of delivered data and the content and the form of the flight environment analysis report. Flight telemetry data are used to verify if flight environment conditions exceed pre-flight analyses and environmental test results. In the event of a launch failure, adequate flight environment data can assist in investigating and analysing failure causes. ISO 15862:2009 is applicable to commercial launch vehicles and related ground processing, no matter which launch vehicle agencies are selected.
Systèmes spatiaux — Traitement des données télémétriques des environnements de vol entre le lanceur spatial et le véhicule spatial
General Information
Standards Content (Sample)
INTERNATIONAL ISO
STANDARD 15862
First edition
2009-02-01
Space systems — Launch-vehicle-to-
spacecraft flight environments telemetry
data processing
Systèmes spatiaux — Traitement des données télémétriques des
environnements de vol entre le lanceur spatial et le véhicule spatial
Reference number
ISO 15862:2009(E)
©
ISO 2009
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ISO 15862:2009(E)
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ISO 15862:2009(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
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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 15862 was prepared by Technical Committee ISO/TC 20, Aircraft and space vehicles, Subcommittee
SC 14, Space systems and operations.
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ISO 15862:2009(E)
Introduction
This International Standard addresses flight environment measurements, data processing and analysis, and
reports of analysis results. If launch vehicle (LV) environmental specifications are exceeded, the LV and
spacecraft (SC) agencies can perform an analysis to determine the cause of the problem.
Flight environments describe different types of flight mechanical and thermal environments. Measurement
fields include parameters characterizing such environments as loads, vibration, shock, acoustics, steady-state
pressure and temperature. Requirements include number, location, range and frequency of measurement
devices.
Data processing and analysis include data pre-processing, data processing and formats of delivered data.
Flight measurement plan formats are provided.
The report on flight environment analysis results records all the above information.
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INTERNATIONAL STANDARD ISO 15862:2009(E)
Space systems — Launch-vehicle-to-spacecraft flight
environments telemetry data processing
1 Scope
This International Standard provides basic requirements for the measurement of the spacecraft flight
environments generated by the launch vehicle, telemetry data processing and formats of analysis reports.
This International Standard defines the field and number of measurement parameters, the principles of data
processing, the format of delivered data and the content and the form of the flight environment analysis report.
Flight telemetry data are used to verify if flight environment conditions exceed pre-flight analyses and
environmental test results. In the event of a launch failure, adequate flight environment data can assist in
investigating and analysing failure causes.
This International Standard is applicable to commercial launch vehicles and related ground processing, no
matter which launch vehicle agencies are selected.
2 Terms and definitions
For the purposes of this document, the following terms and definitions apply.
2.1
cut-off
load case when the engine thrust begins to decrease from current value to zero
2.2
ground transportation
spacecraft transportation at launch site
2.3
lift-off
launch vehicle motion when the vehicle's contact is terminated with launch pad or other support devices
NOTE This is commonly called “first motion” of the vehicle. Possible abnormal cut-off is also included.
2.4
load case
event in spacecraft service life during which essential mechanical environments are expected
2.5
maximum dynamic pressure phase
flight phase when dynamic pressure reaches its maximum value
2.6
minimum sampling frequency
minimum number of data points of measurement fields collected per second
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ISO 15862:2009(E)
2.7
spacecraft-to-launch-vehicle interface
SC/LV interface
mechanical interface that connects spacecraft (or spacecraft-provided adapter) to launch-vehicle-provided
adapter
2.8
separation
separations of launch vehicle stages, boosters and other structural elements (e.g. fairing jettison)
2.9
steady-state acceleration
constant acceleration that generates static loads.
2.10
transonic phase
flight phase when the Mach number is in the range of 0,8 to 1,2
3 Abbreviated terms
LV launch vehicle
PSD power spectral density
SC spacecraft
SPL sound pressure level
SRS shock response spectrum
RMS root mean square
4 Flight environments, measurement fields and measurement requirements
4.1 Flight environments
4.1.1 General
Different types of mechanical environments and thermal environments are described in 4.1.2 to 4.1.8 below.
4.1.2 Quasi-static load
The quasi-static load is the resultant of all external forces with the exception of gravity applied on the LV
centre of gravity.
4.1.3 Low-frequency vibration
Low-frequency vibration is the structural response generated mainly by thrust variation of the LV engines at
ignition and cut-off, by fluctuation of the pressure during the transonic phase, and by transient loads at stage
separation(s).
4.1.4 High-frequency vibration
High-frequency vibration is the structural response generated mainly by the LV engine noise and by the
aerodynamic noise. High-frequency vibration reaches the maximum during lift-off, ascent phase and transonic
flight.
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ISO 15862:2009(E)
4.1.5 Acoustic noise
Acoustic noise is the sound pressure generated mainly by the LV engine noise and by aerodynamics. The
maximum fairing internal noise occurs during lift-off, ascent phase and transonic flight.
4.1.6 Shock
Shock environment consists of the transient response generated by the LV fairing jettison, stage separation(s)
and SC/LV separation(s).
4.1.7 Steady-state pressure
The steady-state pressure field consists of the instantaneous pressure of air outside the LV and inside the
fairing. The fairing internal pressure of air decreases gradually during the LV ascent phase due to air escape.
The fairing internal pressure of air is related to the flight trajectory, the shape of the fairing and the vent
configurations.
4.1.8 Thermal
The launch phase thermal environment is dependent on the fairing aerodynamic heating, the radiation of the
sun and the earth, and the space conditions.
4.2 Measurement fields
Measurement fields shall be determined by common agreement between the LV service provider and the SC
customer. Unless otherwise specified, the following measurement fields shall be planned and corresponding
measurements shall be conducted:
⎯ steady-state acceleration,
⎯ low-frequency vibration,
⎯ high-frequency vibration,
⎯ acoustic noise,
⎯ shock acceleration,
⎯ steady-state pressure, and
⎯ temperature.
4.3 Measurement requirements
4.3.1 Number and location of measurements
4.3.1.1 Steady-state acceleration
As a minimum, steady-state acceleration shall be measured at one location in the LV longitudinal axis and the
two lateral orthogonal axes. The measurement location shall be close to the SC/LV interface.
NOTE In general, this practice is recommended for developmental flights, but is often not required for operational
systems.
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ISO 15862:2009(E)
4.3.1.2 Low-frequency vibration
As a minimum, low-frequency vibration shall be measured at one location in the LV longitudinal axis and the
two lateral orthogonal axes. The measurement location shall be close to the SC/LV interface.
4.3.1.3 High-frequency vibration
As a minimum, high-frequency vibration shall be measured at one location in the LV longitudinal axis and the
two lateral orthogonal axes. The measurement location shall be close to the SC/LV interface.
NOTE In general, this practice is recommended for developmental flights, but is often not required for operational
systems.
4.3.1.4 Acoustic noise
As a minimum, acoustic sound pressure shall be measured at two points. The measurement location shall be
representative of the acoustic field inside the fairing.
4.3.1.5 Shock acceleration
As a minimum, shock acceleration shall be measured at one location in the LV longitudinal axis and in one
orthogonal axis. The measurement location shall be close to the SC/LV interface.
NOTE In general, this practice is recommended for developmental flights, but is often not required for operational
systems.
4.3.1.6 Steady-state pressure
As a minimum, steady-state pressure shall be measured at one location. The measurement location shall be
chosen inside the fairing to indicate the ambient pressure.
NOTE In general, this practice is recommended for developmental flights, but is often not requir
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