EN 16603-10-03:2014

SLOVENSKI STANDARD
01-november-2014
1DGRPHãþD
SIST EN 14824:2004
Vesoljska tehnika - Preskušanje
Space engineering - Testing
Raumfahrttechnik - Tests
Ingénerie spatiale - Tests
Ta slovenski standard je istoveten z: EN 16603-10-03:2014
ICS:
49.140 Vesoljski sistemi in operacije Space systems and
operations
2003-01.Slovenski inštitut za standardizacijo. Razmnoževanje celote ali delov tega standarda ni dovoljeno.

EUROPEAN STANDARD
EN 16603-10-03
NORME EUROPÉENNE
EUROPÄISCHE NORM
August 2014
ICS 49.140 Supersedes EN 14824:2003
English version
Space engineering - Testing
Ingénerie spatiale - Tests Raumfahrttechnik - Tests
This European Standard was approved by CEN on 28 December 2013.

CEN and CENELEC members are bound to comply with the CEN/CENELEC Internal Regulations which stipulate the conditions for giving
this European Standard the status of a national standard without any alteration. Up-to-date lists and bibliographical references concerning
such national standards may be obtained on application to the CEN-CENELEC Management Centre or to any CEN and CENELEC
member.
This European Standard exists in three official versions (English, French, German). A version in any other language made by translation
under the responsibility of a CEN and CENELEC member into its own language and notified to the CEN-CENELEC Management Centre
has the same status as the official versions.

CEN and CENELEC members are the national standards bodies and national electrotechnical committees of Austria, Belgium, Bulgaria,
Croatia, Cyprus, Czech Republic, Denmark, Estonia, Finland, Former Yugoslav Republic of Macedonia, France, Germany, Greece,
Hungary, Iceland, Ireland, Italy, Latvia, Lithuania, Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Romania, Slovakia,
Slovenia, Spain, Sweden, Switzerland, Turkey and United Kingdom.

CEN-CENELEC Management Centre:
Avenue Marnix 17, B-1000 Brussels
© 2014 CEN/CENELEC All rights of exploitation in any form and by any means reserved Ref. No. EN 16603-10-03:2014 E
worldwide for CEN national Members and for CENELEC
Members.
Table of contents
Foreword . 5
Introduction . 6
1 Scope . 8
2 Normative references . 10
3 Terms, definitions and abbreviated terms . 12
3.1 Terms from other standards . 12
3.2 Terms specific to the present standard . 18
3.3 Abbreviated terms. 24
4 General requirements. 27
4.1 Test programme . 27
4.2 Development test prior qualification . 27
4.3 Test management . 28
4.3.1 General . 28
4.3.2 Test reviews . 28
4.3.3 Test documentation . 32
4.3.4 Anomaly or failure during testing . 33
4.3.5 Test data . 33
4.4 Test conditions, tolerances, and accuracies. 33
4.4.1 Test conditions . 33
4.4.2 Test tolerances . 34
4.4.3 Test accuracies . 36
4.5 Test objectives . 38
4.5.1 General requirements . 38
4.5.2 Qualification testing . 38
4.5.3 Acceptance testing . 39
4.5.4 Protoflight testing . 39
4.6 Retesting . 40
4.6.1 Overview . 40
4.6.2 Implementation of a design modification after completion of
qualification . 40
4.6.3 Storage after protoflight or acceptance testing . 40
4.6.4 Space segment element or equipment to be re-flown . 41
4.6.5 Flight use of qualification Space segment element or equipment . 42
5 Space segment equipment test requirements . 43
5.1 General requirements . 43
5.2 Qualification tests requirements . 45
5.3 Acceptance test requirements . 53
5.4 Protoflight test requirements . 59
5.5 Space segment equipment test programme implementation requirements . 66
5.5.1 General tests . 66
5.5.2 Mechanical tests . 69
5.5.3 Structural integrity tests . 72
5.5.4 Thermal tests . 73
5.5.5 Electrical/RF tests . 75
5.5.6 Mission specific test . 76
6 Space segment element test requirements . 78
6.1 General requirements . 78
6.2 Qualification test requirements . 79
6.3 Acceptance test requirements . 86
6.4 Protoflight test requirements . 91
6.5 Space segment elements test programme implementation requirements . 98
6.5.1 General tests . 98
6.5.2 Mechanical tests . 102
6.5.3 Structural integrity tests . 107
6.5.4 Thermal tests . 108
6.5.5 Electromagnetic tests . 110
6.5.6 Mission specific tests . 111
6.5.7 Crewed mission specific tests . 111
7 Pre-launch testing . 113
Annex A (normative) Assembly, integration and test plan (AITP) - DRD . 115
Annex B (normative) Test specification (TSPE) - DRD . 118
Annex C (normative) Test procedure (TPRO) - DRD . 121
Annex D (informative) Guidelines for tailoring and verification of this
standard . 124
Bibliography . 128

Figures
Figure 3-1: Space system breakdown . 13
Figure 3-2: Space segment examples . 17
Figure 5-1: Space segment equipment test sequence . 45
Figure D-1 : Logic for customer tailoring and supplier answer through compliance and
verification matrix . 126
Figure D-2 : Clauses selection in First step of the tailoring . 126

Tables
Table 4-1: Allowable tolerances . 35
Table 4-2: Test accuracies . 37
Table 5-1: Space segment equipment - Qualification test baseline . 46
Table 5-2: Space segment equipment - Qualification test levels and duration . 48
Table 5-3: Space segment equipment - Acceptance test baseline . 54
Table 5-4: Space segment equipment - Acceptance test levels and duration . 56
Table 5-5: Space segment equipment - Protoflight test baseline . 60
Table 5-6: Space segment equipment - Protoflight test levels and duration . 62
Table 6-1: Space segment element - Qualification test baseline . 80
Table 6-2: Space segment element - Qualification test levels and duration . 82
Table 6-3: Space segment element - Acceptance test baseline . 86
Table 6-4: Space segment element - Acceptance test levels and duration . 88
Table 6-5: Space segment element - Protoflight test baseline . 92
Table 6-6: Space segment element - Protoflight test levels and duration . 94
Table D-1 : Guideline for verification close-out . 127

Foreword
This document (EN 16603-10-03:2014) has been prepared by Technical
Committee CEN/CLC/TC 5 “Space”, the secretariat of which is held by DIN.
This standard (EN 16603-10-03:2014) originates from ECSS-E-ST-10-03C.
This European Standard shall be given the status of a national standard, either
by publication of an identical text or by endorsement, at the latest by February
2015, and conflicting national standards shall be withdrawn at the latest by
February 2015.
Attention is drawn to the possibility that some of the elements of this document
may be the subject of patent rights. CEN [and/or CENELEC] shall not be held
responsible for identifying any or all such patent rights.
This document will supersede EN 14824:2003.
This document has been developed to cover specifically space systems and has
therefore precedence over any EN covering the same scope but with a wider
domain of applicability (e.g. : aerospace).
According to the CEN-CENELEC Internal Regulations, the national standards
organizations of the following countries are bound to implement this European
Standard: Austria, Belgium, Bulgaria, Croatia, Cyprus, Czech Republic,
Denmark, Estonia, Finland, Former Yugoslav Republic of Macedonia, France,
Germany, Greece, Hungary, Iceland, Ireland, Italy, Latvia, Lithuania,
Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Romania,
Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey and the United
Kingdom.
Introduction
The requirements on the systems engineering process are gathered in ECSS-E-
ST-10; while specific aspects are further elaborated in dedicated standards, in
particular: ECSS-E-ST-10-06, ECSS-E-ST-10-02 and the present standard (ECSS-
E-ST-10-03)
In the System Engineering branch (ECSS-E-10) this standard aims at a
consistent application of on ground testing requirements to allow proper
qualification and acceptance of space products
Experience has demonstrated that incomplete or improper on ground testing
approach significantly increase project risks leading to late discovery of design
or workmanship problem(s) or in-orbit failure(s).
Testing is part of the system engineering process as defined in ECSS-E-ST-10.
This starts at the early phase of the mission when defining verification process
in terms of the model philosophy and test sequence and ends at the last testing
phase prior launch.
In the level of decomposition of a space system, this standard addresses the
requirements for space segment element and space segment equipment.

The document is organised such that:
• clause 4 provides requirements for overall test programme, test
management and test conditions, tolerances and accuracy;
• clause 5 provides requirements for Space segment equipment;
• clause 6 provides requirements for Space segment element;
• clause 7 provides requirements for Pre-launch testing.

Clauses 5 and 6 are organised as follows:
• general requirements for the products under test applicable to all models
(clause 5.1 or 6.1);
• requirements applicable to qualification model (clause 5.2 or 6.2);
• requirements applicable to acceptance model (clause 5.3 or 6.3);
• requirements applicable to protoflight model (clause 5.4 or 6.4);
• detailed implementation requirements (clause 5.5 or 6.5);

In the clause providing requirements for each model (i.e. clauses 5.2, 5.3, 5.4,
6.2, 6.3 and 6.4), the first table of the clause:
• lists all types of test and defines their applicability and conditions;
• links to the second table of the clause that defines tests level and
duration;
• provides reference to the clause defining the detailed implementation
requirements for the given test (clause 5.5 or 6.5).

For space segment equipment, the required sequence of test, for each model, is
defined after the two tables in clause 5.2, 5.3 or 5.4.
Since testing activities are part of the overall verification activities, test
documentation to be produced (DRD’s) are either specified in the ECSS-E-ST-
10-02 (case of the test report) or in this document.
Annex D gives guidelines for performing the tailoring of this standard as well
as the generation of the compliance and verification matrices.
Scope
This standard addresses the requirements for performing verification by testing
of space segment elements and space segment equipment on ground prior to
launch. The document is applicable for tests performed on qualification models,
flight models (tested at acceptance level) and protoflight models.
The standard provides:
• Requirements for test programme and test management,
• Requirements for retesting,
• Requirements for redundancy testing,
• Requirements for environmental tests,
• General requirements for functional and performance tests,
NOTE Specific requirements for functional and
performance tests are not part of this standard
since they are defined in the specific project
documentation.
• Requirements for qualification, acceptance, and protoflight testing
including qualification, acceptance, and proto-fight models’ test margins
and duration,
• Requirements for test factors, test condition, test tolerances, and test
accuracies,
• General requirements for development tests pertinent to the start of the
qualification test programme,
NOTE Development tests are specific and are
addressed in various engineering discipline
standards.
• Content of the necessary documentation for testing activities (e.g. DRD).

Due to the specific aspects of the following types of test, this Standard does not
address:
• Space system testing (i.e. testing above space segment element), in
particular the system validation test,
• In-orbit testing,
• Testing of space segment subsystems,
NOTE Tests of space segment subsystems are often
limited to functional tests that, in some case, are
run on dedicated models. If relevant,
qualification tests for space segment
subsystems are assumed to be covered in the
relevant discipline standards.
• Testing of hardware below space segment equipment levels (including
assembly, parts, and components),
• Testing of stand-alone software,
NOTE For verification of flight or ground software,
ECSS-E-ST-40 and ECSS-Q-ST-80 apply.
• Qualification testing of two-phase heat transport equipment,
NOTE For qualification testing of two-phase heat
transport equipment, ECSS-E-ST-31-02 applies.
• Tests of launcher segment, subsystem and equipment, and launch
facilities,
• Tests of facilities and ground support equipment,
• Tests of ground segment.
This standard may be tailored for the specific characteristic and constrains of a
space project in conformance with ECSS-S-ST-00. Annex D gives guidelines for
performing this tailoring.
Normative references
The following normative documents contain provisions which, through
reference in this text, constitute provisions of this ECSS Standard. For dated
references, subsequent amendments to, or revision of any of these publications
do not apply. However, parties to agreements based on this ECSS Standard are
encouraged to investigate the possibility of applying the more recent editions of
the normative documents indicated below. For undated references, the latest
edition of the publication referred to applies.
EN reference Reference in text Title
EN 16601-00-01 ECSS-S-ST-00-01 ECSS system - Glossary of terms
EN 16603-10-02 ECSS-E-ST-10-02 Space engineering - Verification
EN 16603-20 ECSS-E-ST-20 Space engineering - Electrical and electronic
EN 16003-20-01 ECSS-E-20-01 Space engineering - Multipaction design and test
EN 16603-20-06 ECSS-E-ST-20-06 Space engineering - Spacecraft charging
EN 16603-20-07 ECSS-E-ST-20-07 Space engineering - Electromagnetic compatibility
EN 16603-20-08 ECSS-E-ST-20-08 Space engineering - Photovoltaic assemblies and
components
EN 16603-31 ECSS-E-ST-31 Space engineering - Thermal control general
requirements
EN 16603-32 ECSS-E-ST-32 Space engineering - Structural general requirements
EN 16603-32-02 ECSS-E-ST-32-02 Space engineering - Structural design and verification
of pressurized hardware
EN 16603-32-10 ECSS-E-ST-32-10 Space engineering - Structural factors of safety for
spaceflight hardware
EN 16603-32-11 ECSS-E-ST-32-11 Space engineering - Modal survey assessment
EN 16603-33-01 ECSS-E-ST-33-01 Space engineering - Mechanisms
EN 16601-40 ECSS-M-ST-40 Space project management - Configuration and
information management
EN 16602-10-09 ECSS-Q-ST-10-09 Space product assurance - Nonconformance control
system
EN 16602-20-07 ECSS-Q-ST-20-07 Space product assurance - Quality assurance for test
centres
EN 16602-40 ECSS-Q-ST-40 Space product assurance - Safety
EN 16602-70-01 ECSS-Q-ST-70-01 Space product assurance - Cleanliness and
contamination control
ISO 3740:2000 Acoustics - Determination of sound power levels of
noise sources - Guidelines for the use of basic
standards
Terms, definitions and abbreviated terms
3.1 Terms from other standards
For the purpose of this standard, since ECSS-S-ST-00-01 has not been published
at the time of the publication of this standard, the introduction part of the ECSS
Glossary has been copied here.
For the purpose of this standard; the terms and definitions from ECSS-S-ST-00-01
apply, and in particular the following:
flight model
lifetime
protoflight model
qualification model
space segment element
space segment equipment
space segment subsystem
structural model
system
ECSS-S-ST-00-01C defines the highest-level system within a space project - i.e.
the one at the mission-level - as the “Space System”. The breakdown of a typical
space system and the definition of standard terms for the constituent levels
within the breakdown are given below (see Figure 3-1 and subsequent
definitions).
For this standard only, the terms for the Space Segment are defined in 3.1.
Since any definition always includes some ambiguity and in order to allow the
user of the testing standard to clearly classify the item under test in the right
category (i.e. Space segment Element, or equipment the table below give a list of
example (see Figure 3-2). This table, however, is not exhaustive

Space System Users
Support Segment
Space Segment Ground Segment Launch Segment
Space Ground Launch
Segment Segment Segment
System System System
Space Ground Launch
Segment Segment Segment
Element Element Element
Space Ground Launch
Segment Segment Segment
Subsystem Subsystem Subsystem
Space Segment Ground Segment Launch Segment
Equipment/Unit Equipment/Unit Equipment/Unit
Legend:
Components ( = Parts)
Functional view
Physical view
Materials
Note 1: Since software can belong to Note 2: A subsystem can be split across two segments Space segment Ground segment Space system
+ =
subsystem subsystem subsystem
any level it is not apparent in this chart e.g. TT&C subsystem split across Space and Ground segments

Figure 3-1: Space system breakdown
The following terms are copied from ECSS-S-ST-00-01C Draft 1.1. Cross-references in
these terms are within ECSS-S-ST-00-01C Draft 1.1.
3.1.1 system
set of interrelated or interacting functions constituted to achieve a specified objective
3.1.2 space system
system that contains at least a space, a ground or a launch segment
NOTE Generally a space system is composed of all three
segments and is supported by a support segment.
3.1.3 space segment
part of a space system, placed in space, to fulfil the space mission objectives
3.1.4 space segment system
system within a space segment
NOTE Examples are given in Annex B.1.
3.1.5 space segment element
element within a space segment
NOTE 1 A space segment element can be composed of several
embedded space segment elements, e.g. a spacecraft is
composed of instruments, a payload module and a
service module.
NOTE 2 Examples are given in Annex B.1.
3.1.6 stand-alone space segment element
space segment element that performs its mission autonomously
NOTE For example: satellite, rover, lander.
3.1.7 embedded space segment element
space segment element that performs its mission as part of another space segment
element
NOTE For example: platform, module, instrument, payload.
3.1.8 space segment subsystem
subsystem within a space segment
NOTE Examples are given in Annex B.1.
3.1.9 space segment equipment
equipment within a space segment
NOTE Examples are given in Annex B.1.
3.1.10 component
set of materials, assembled according to defined and controlled processes, which
cannot be disassembled without destroying its capability and which performs a
simple function that can be evaluated against expected performance requirements
NOTE 1 The term "part" is synonymous.
NOTE 2 The term "part" is preferred when referring to purely
mechanical devices.
NOTE 3 The term "component" is preferred for EEE devices.
3.1.11 part
see “component”
3.1.12 material
raw, semi-finished or finished substance (gaseous, liquid, solid) of given
characteristics from which processing into a component or part is undertaken
3.1.13 flight model (FM)
end product that is intended for flight
NOTE 1 The flight model is subjected to formal functional and
environmental acceptance testing.
NOTE 2 More detailed information on the build standard and the
use of this model is given in ECSS-E-HB-10-02.
3.1.14 lifetime
period, or number of cycles, over which a product is required to perform according
to its specification
3.1.15 protoflight model (PFM)
flight model on which a partial or complete protoflight qualification test campaign
is performed before flight
NOTE More detailed information on the build standard and the
use of this model is given in ECSS-E-HB-10-02.
3.1.16 qualification model (QM)
model, which fully reflects all aspects of the flight model design, used for complete
functional and environmental qualification testing
NOTE 1 A qualification model is only necessary for newly-
designed hardware or when a delta qualification is
performed for adaptation to the project.
NOTE 2 The qualification model is not intended to be used for
flight, since it is overtested.
NOTE 3 More detailed information on the build standard and the
use of this model is given in ECSS-E-HB-10-02.
3.1.17 structural model (SM)
structurally representative model of the flight model used for qualification of the
structural design and for correlation with structural mathematical models
NOTE 1 The system structural model usually consists of a
representative structure, with structural dummies of the
flight equipment, and also includes representative
mechanical parts of other subsystems (e.g. mechanisms
and solar panels).
NOTE 2 The system structural model is also used for final
validation of test facilities, GSE, and associated
procedures.
NOTE 3 More detailed information on the build standard and the
use of this model is given in ECSS-E-HB-10-02.

space segment
space segment system space segment element
space segment subsystem
space segment equipment (=unit)
component (=part)
material
product or item
examples
Data Relay Satellite spacecraft (physical view) power electronic unit (e.g. DHU, PCSU, PDU, ASIC Alumiunium
System ICU)
Navigation Satellite satellite (physical view) propulsion thruster hybrid to be taken from Q60 & Q70
System
spacecraft (functional
view) payload data handling valve integrated circuit
satellite (functional view)
platform thermal battery heat-pipe
instrument structure reflector MLI
orbiter AOCS mechanism (when fully assembled) structural panel
lander Tm&Tc vessel/tank optical array
bay optical mirror/lenses/filters (assembly) pyro components
module RF solar array (assembly) - see note PCB
communication antenna (assembly) mirror
focal plane assembly solar cell
telescope (assembly) insert
solar panel (equipped) - see note resistor
pressure vessels diode
optical bench transistor
RF filters capacitor
LNA thermistor
IMUX/OMUX heater
OMT propulsion fluidic
feeds
2 phases heat transport equipment

NOTE A deployable solar array is an equipment composed of one or several solar panels (panel substrate and photovoltaic assembly),
deployment mechanism including hinges, restrain and release mechanism, and yoke.
Figure 3-2: Space segment examples
For the purpose of this standard, the following terms and definitions from
ECSS-E-ST-10-02 apply:
commissioning
model philosophy
test
For the purpose of this Standard, the following terms and definitions from
ECSS-E-ST-31 apply:
acceptance temperature range
minimum switch ON temperature
predicted temperature range
qualification temperature range
temperature reference point
For the purpose of this Standard, the following terms and definitions from
ECSS-E-ST-32 apply:
burst pressure
design burst pressure
factor of safety
limit load (LL)
maximum design pressure (MDP)
proof factor
proof pressure
proof test
3.2 Terms specific to the present standard
3.2.1 24-hour equivalent noise exposure level
equivalent sound pressure level (Leq) to which the crew members are exposed over
a 24-hour period; expressed in dBA
NOTE 0 dBA corresponds to 20 µPa.
3.2.2 a-weighting
adjustments typically made to acoustic measurements to approximate the response
of the human ear
3.2.3 abbreviated functional test (AFT)
See "reduced functional test (RFT)"
3.2.4 acceptance level
test level reflecting the maximum level expected to be encountered during the
flight product lifetime increased by acceptance margins
3.2.5 acceptance margin
increase of the environmental, mechanical, thermal, electrical, EMC, or operational
extremes above the worst case levels predicted over the specified product lifetime
for the purpose of workmanship verification
NOTE 1 Margins can include an increase in level or range,
an increase in duration or cycles of exposure, as
well as any other appropriate increase in severity.
NOTE 2 For thermal acceptance margin refer also to ECSS-
E-ST-31.
3.2.6 accuracy of measurement
degree of closeness between a measured quantity value and its true value
NOTE The accuracy depends from the measurement
process (e.g. instrument or machine, operator,
procedure; environmental conditions).
3.2.7 crewed space segment element
space segment design to ensure the safe presence of crew onboard
3.2.8 development test prior qualification
test to support the design feasibility and to assist in the evolution of the design
3.2.9 dwell time
duration necessary to ensure that internal parts or subassembly of a space segment
equipment have achieved thermal equilibrium, from the start of temperature
stabilisation phase, i.e. when the temperature reaches the targeted test temperature
plus or minus the test tolerance
3.2.10 environmental tests
tests applied to a product simulating (together or separately) environmental
conditions as encountered during its operational life cycle
NOTE Environmental tests cover natural and induced
environments.
3.2.11 full functional test (FFT)
comprehensive test that demonstrates the integrity of all functions of the item
under test, in all operational modes, including back-up modes and all foreseen
transitions
NOTE 1 The main objectives of this test is to demonstrate
absence of design manufacturing and integration
error.
NOTE 2 FFT exists at the different level of decomposition of
a space segment element. For satellite they also
called system functional test (SFT) or integrated
system test (IST).
3.2.12 maximum expected acceleration
acceleration value determined from the combined effects of the steady state
acceleration and the transient response of the item as it will experience during its
life time
NOTE 1 This term is equivalent to limit load (as defined in
E-ST-32).
NOTE 2 Examples of events during life time are
transportation, handling, engine ignition, engine
burnout, and stage separation.
3.2.13 maximum expected acoustic spectrum
maximum value of the time average root-mean-square (r.m.s.) sound pressure level
(SPL) in each frequency band occurring inside the payload fairing, orbiter, or cargo
bay, which occurs during flight events
NOTE 1 E.g. lift-off, powered flight or re-entry.
NOTE 2 The maximum expected acoustic environment test
spectrum is specified in octave or 1/3 octave bands
over a frequency range of 31,5 Hz to 10 kHz. The
duration of the maximum environment is the total
period when the overall amplitude is within 6 dB
of the maximum overall amplitude.
3.2.14 maximum expected shock
worst cases of the collection of the shock at their mounting interface due to every
possible cause
NOTE 1 For example: causes of shocks are stage, shroud or
satellite separation pyro elements, non-explosive
actuators, mechanisms with energy release,
appendage latching, and fuel valves.
NOTE 2 Shocks can be characterized by their time histories,
shock response spectrum, or impulse geometry.
NOTE 3 Refer to ECSS-E-HB-32-25 for additional
information.
3.2.15 maximum expected random vibration spectrum
maximum expected environment imposed on the space segment element and space
segment equipment due to broad band random forcing functions within the launch
element or space segment element during flight or from ground transportation and
handling
NOTE 1 E.g. lift-off acoustic field, aerodynamic excitations,
and transmitted structure-borne vibration.
NOTE 2 A different spectrum can exist for different space
segment equipment zones or for different axis. The
space segment equipment vibration levels are
based on vibration response measurements or
model prediction made at the space segment
equipment attachment points during ground
acoustic tests or during flight. The duration of the
maximum environment is the total period during
flight when the overall level is within 6 dB of the
maximum overall level.
NOTE 3 The power spectral density is based on a frequency
resolution of 1/6 octave (or narrower) bandwidth
analysis, over a frequency range of 20 Hz to 2000 Hz.
3.2.16 maximum expected sinusoidal vibration environment
maximum expected environment imposed on the space segment element and space
segment equipment due to sinusoidal and narrow band random forcing functions
within the launch element or space segment element during flight or from ground
transportation and handling
NOTE In flight, sinusoidal excitations are caused by
unstable combustion, by coupling of structural
resonant frequencies (POGO), or by imbalances in
rotating space segment equipment in the launch
element or space segment element. Sinusoidal
excitations occur also during ground
transportation and handling due to resonant
responses of tires and suspension systems of the
transporters.
3.2.17 multipaction
resonant back and forth flow of secondary electrons in a vacuum between two
surfaces separated by a distance such that the electron transit time is an odd
integral multiple of one half the period of the alternating voltage impressed on the
surface
NOTE The effects of multipaction can be loss of output
power up to reaching the multipaction breakdown
voltage leading to the generation of spark.
3.2.18 notching
reduction of the input level or spectrum to limit structural responses at resonant
frequencies according to qualification or acceptance loads during a vibration test
NOTE Notching is a general accepted practice in vibration
testing to avoid over testing of the item under test.
Implementation of notching is subject to customer
approval and when relevant to Launcher authority
approval
3.2.19 operational modes
combination of operational configurations or conditions that can occur during the
product lifetime for space segment equipment or space segment element
NOTE For example: Power-on or power-off, command
modes, readout modes, attitude control modes,
antenna stowed or deployed, and spinning or de-
spun.
3.2.20 performance test
test to verify that the item under test performs according to its specifications while
respecting its operational requirements
NOTE Performance tests are mission specific therefore
their details are not specified under this standard.
3.2.21 polarity test
test to verify the correct polarity of the functional chains (mainly AOCS) or
equipment of the space segment element from sensors to actuators, through a
number of interfaces and processing.
NOTE 1 A polarity error can be generated throughout the
development process: interface documentation,
design, H/W manufacturing, S/W development,
satellite AIT, satellite database.
NOTE 2 A polarity error can be generated by any element
of the functional chain: sensor or actuator design,
sensor or actuator mounting, harness, interface
units, software algorithms.
NOTE 3 Polarity inversion on Safe Mode control loops can
cause a satellite loss.
NOTE 4 This term "sign test" is synonymous.
3.2.22 qualification level
test level reflecting the maximum level expected to be encountered during the
flight product lifetime increased by qualification margins
NOTE For thermal the qualification margin applies on top
of the acceptance margin.
3.2.23 qualification margin
increase of the environmental, mechanical, electrical, EMC, or operational extremes
above the worst case levels predicted over the specified product lifetime for the
purpose of design margin demonstration
NOTE 1 Margins can include an increase in level or range,
an increase in duration or cycles of exposure, as
well as any other appropriate increase in severity.
NOTE 2 This definition is not applicable for thermal
aspects. Refer to ECSS-E-ST-31 for "qualification
margin".
3.2.24 reduced functional test (RFT)
sub-set of the full functional test to verify the integrity of the major functions of
the item under test, with a sufficiently high degree of confidence, in a relatively
short time
NOTE The term "abbreviated functional test (AFT)" is
synonymous.
3.2.25 residual life
time left before a product is no longer able to achieve minimum acceptable
performance requirements, including availability
NOTE Criteria can be estimated in terms of serviceability
or structural strength for example.
3.2.26 resolution
minimum readable value of a quantity on a measurement system
NOTE The resolution is accounted for in the accuracy.
3.2.27 resonance search
frequency sweep of low level sinusoidal vibrations to characterise main resonant
modes for preparing the higher level runs, and to show possible deficiencies in
workmanship, as a consequence of high level runs
NOTE Resonance search is also known as “signature test”,
“low level sinusoidal vibration test”, “low level
sine sweep”, “low level sweep” or “low level test”.
3.2.28 reverberation time (T60)
duration necessary for the sound level to decrease by 60 dB after the switch off of
the sound source
3.2.29 shock response spectrum (SRS)
graphical representation of a transient waveform determined by the response of a
set of single degree of freedom oscillators using a defined amplification factor Q
NOTE 1 The Shock Response Spectrum can be defined for
any input or response parameters of interest
(displacement, velocity, or acceleration). For
aerospace structures it is common to define the
input transient in terms of acceleration.
NOTE 2 The acceleration amplification factor Q is
conventionally chosen equal to 10, corresponding
to a factor of critical damping equal to 5 %. In
situations when damping is known, Q can be
chosen accordingly.
NOTE 3 The Shock Response Spectrum allows
characterizing the shock effect in order to estimate
its severity or its damaging potential.
NOTE 4 There are several representations of Shock
Response Spectrum, including positive, negative,
primary, residual and maximax. The latter SRS
envelopes the previous four and is the most
commonly used for shock testing.
3.2.30 sign test
see “polarity test”
3.2.31 temperature cycle
transition from an initial temperature to the same temperature, with excursion
within a specified range
3.2.32 test block
aggregation of several tests grouped by discipline
3.2.33 tolerance
limiting or permitted range of values of a specified test level without affecting the
test objectives
NOTE The tolerance is typically specified as deviation
from a specified value, or as an explicit range of
allowed values. Tolerance can be symmetrical, as
in 40 ±0,1, or asymmetrical, such as 40 -0,2/+0,1.
3.3 Abbreviated terms
For the purposes of this Standard the following abbreviated terms apply.
Abbreviation Meaning
abbreviated functional test
AFT
assembly, integration and test
AIT
assembly, integration and test plan
AITP
assembly, integration and verification
AIV
acceptance vibration test
AVT
configuration control board
CCB
centre of gravity
CoG
document requirements definition
DRD
European Commission
EC
electrical ground support equipment
EGSE
engineering model
EM
electromagnetic compatibility
EMC
electromagnetic compatibility control plan
EMCCP
engineering qualification model
EQM
electrostatic discharge
ESD
full functional test
FFT
flight model
FM
flight operation plan
FOP
ground support equipment
GSE
human factors engineering
HFE
human-machine interface
HMI
Abbreviation Meaning
interface control document
ICD
key inspection point
KIP
launcher coupled dynamic analysis
LCDA
launch and early orbit phase
LEOP
maximum design pressure
MDP
mandatory inspection point
MIP
moment of inertia
MoI
noise criterion
NC
nonconformance report
NCR
nonconformance review board
NRB
overall sound pressure level
OSPL
protoflight model
PFM
passive intermodulation
PIM
power spectral density
PSD
performance test
PT
post test review
PTR
qualification model
QM
root-mean-square
r.m.s.
radio frequency
RF
reduced functional test
RFT
system engineering plan
SEP
system functional test
SFT
sound pressure level
SPL
shock response spectrum
SRS
system validation test
SVT
thermal balance
TB
telecommand
TC
thermal control system
TCS
telemetry
TM
test pro
...