SIST EN 16603-10-03:2022
(Main)Space engineering - Testing
Space engineering - Testing
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 protofight 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 follow ing 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 softw are, EN 16603-40 (ECSS-E-ST-40) and EN 16602-80 (ECSS-Q-ST-80) apply.
• Qualification testing of tw o-phase heat transport equipment,
NOTE For qualification testing of tw o-phase heat transport equipment, EN 16603-31-02 (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 activity will be the update of EN16603-10-03:2014
NOTE: Parallel development of update of EN Standard and the new European TR17603-10-03.
Raumfahrttechnik - Tests
Ingénierie spatiale - Vérification par essai
Vesoljska tehnika - Preskušanje
General Information
Relations
Standards Content (Sample)
SLOVENSKI STANDARD
01-december-2022
Nadomešča:
SIST EN 16603-10-03:2014
Vesoljska tehnika - Preskušanje
Space engineering - Testing
Raumfahrttechnik - Tests
Ingénierie spatiale - Vérification par essai
Ta slovenski standard je istoveten z: EN 16603-10-03:2022
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
October 2022
ICS 49.140
Supersedes EN 16603-10-03:2014
English version
Space engineering - Testing
Ingénierie spatiale - Vérification par essai Raumfahrttechnik - Tests
This European Standard was approved by CEN on 29 May 2022.
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, France, Germany, Greece, Hungary, Iceland, Ireland, Italy,
Latvia, Lithuania, Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Republic of North Macedonia, Romania, Serbia,
Slovakia, Slovenia, Spain, Sweden, Switzerland, Türkiye and United Kingdom.
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Rue de la Science 23, B-1040 Brussels
© 2022 CEN/CENELEC All rights of exploitation in any form and by any means
Ref. No. EN 16603-10-03:2022 E
reserved worldwide for CEN national Members and for
CENELEC Members.
Table of contents
European Foreword . 5
Introduction . 7
1 Scope . 9
2 Normative references . 11
3 Terms, definitions and abbreviated terms . 12
3.1 Terms from other standards .12
3.2 Terms specific to the present standard .13
3.3 Abbreviated terms. 19
3.4 Nomenclature .22
4 General requirements. 23
4.1 Test programme . 23
4.2 Development test prior qualification .23
4.3 Test management . 24
4.3.1 General . 24
4.3.2 Test reviews .24
4.3.3 Test documentation .28
4.3.4 Anomaly or failure during testing . 29
4.3.5 Test data .29
4.4 Test conditions, input tolerances, and measurement uncertainties . 29
4.4.1 Test conditions .29
4.4.2 Test input tolerances .30
4.4.3 Measurement uncertainties .32
4.5 Test objectives .34
4.5.1 General requirements .34
4.5.2 Qualification testing .34
4.5.3 Acceptance testing .35
4.5.4 Protoflight testing .35
4.6 Retesting .36
4.6.1 Overview .36
4.6.2 Implementation of a design modification after completion of
qualification .36
4.6.3 Storage after protoflight or acceptance testing . 36
4.6.4 Space segment element or equipment to be re-flown . 37
4.6.5 Flight use of qualification Space segment element or equipment . 38
5 Space segment equipment test requirements . 39
5.1 General requirements .39
5.2 Qualification tests requirements . 42
5.3 Acceptance test requirements .51
5.4 Protoflight test requirements .58
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 under pressure tests . 73
5.5.4 Thermal tests .74
5.5.5 Electrical/RF tests .77
5.5.6 Mission specific test .78
6 Space segment element test requirements . 79
6.1 General requirements .79
6.2 Qualification test requirements .79
6.3 Acceptance test requirements .87
6.4 Protoflight test requirements .94
6.5 Space segment elements test programme implementation requirements . 101
6.5.1 General tests . 101
6.5.2 Mechanical tests . 105
6.5.3 Structural integrity under pressure tests . 111
6.5.4 Thermal tests . 112
6.5.5 Electromagnetic tests . 114
6.5.6 Mission specific tests . 115
6.5.7 Crewed mission specific tests . 115
7 Pre-launch testing . 117
Annex A (normative) Assembly, integration and test plan (AIT Plan) - DRD
................................................................................................................... 119
Annex B (normative) Test specification (TSPE) - DRD . 122
Annex C (normative) Test procedure (TPRO) - DRD . 125
Annex D (informative) Guidelines for tailoring and verification of this
standard . 128
Bibliography . 132
Figures
Figure 5-1: Space segment equipment sequence of tests . 41
Figure D-1 : Logic for customer tailoring and supplier answer through compliance and
verification matrix . 129
Figure D-2 : Clauses selection in First step of the tailoring . 130
Tables
Table 4-1: Allowable test input tolerances . 31
Table 4-2: Typical measurement uncertainties from test centers . 33
Table 5-1: Space segment equipment - Qualification test baseline . 43
Table 5-2: Space segment equipment - Qualification test levels and duration . 46
Table 5-3: Space segment equipment - Acceptance test baseline . 52
Table 5-4: Space segment equipment - Acceptance test levels and duration . 55
Table 5-5: Space segment equipment - Protoflight test baseline . 59
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 . 83
Table 6-3: Space segment element - Acceptance test baseline . 87
Table 6-4: Space segment element - Acceptance test levels and duration . 90
Table 6-5: Space segment element - Protoflight test baseline . 94
Table 6-6: Space segment element - Protoflight test levels and duration . 97
Table D-1 : Guideline for verification close-out . 130
European Foreword
This document (EN 16603-10-03:2022) has been prepared by Technical
Committee CEN/CLC/JTC 5 “Space”, the secretariat of which is held by DIN.
This standard (EN 16603-10-03:2022) originates from ECSS-E-ST-10-03C Rev.1.
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 April 2023,
and conflicting national standards shall be withdrawn at the latest by April 2023.
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 supersedes EN 16603-10-03:2014.
The main changes with respect to EN 16603-10-03:2014 are listed below:
• Scope: Clarification on applicability perimeter, including not covering space
vehicle constellation
• Thermal Tests:
o New and more clear definitions, (thermal vacuum test, thermal test at
room pressure and thermal test at mission pressure, they are no more in the
Glossary),
o Thermal Ambient Test not used and substituted by Thermal Test at
mission pressure,
o Alternative methods are addressed as reference to the Handbook
o “thermal” word in thermal parameters (cycles, levels, gradient and so
on) changed as “temperature”,
o Test for switch on capability at equipment level was updated to cover
test at maximum and minimum temperature,
o New requirement on power status during thermal tests at equipment
level and parameter monitoring.
• Test on solar arrays and panel:
o overall align of the Testing Standard with the new version of ECSS-E-
ST-20-08,
o new requirements for solar array performance tests in addition to
flasher test,
o additional requirement for after storage phase,
o functional tests requirements at equipment level during thermal tests
for solar arrays are now expanded.
• Pressure test:
o Overall alignment with new version of ECSS-E-ST-32-02,
o requirements on proof pressure test rephrased to enlarge the objective
of the test.
• Input test Tolerance and measurement uncertainties:
o “tolerance” definition was substituted by “test input tolerance”
whereas “accuracy of measurement” was deleted and substituted by
“measurement uncertainty” to be in accordance with actual International
Standards,
o some requirements rephrased to avoid confusion between
"uncertainty" (quantitative evaluation) and "error" (quantitative, but
unknown),
o Table 4-2 now addresses typical values for test centres and no more
requirements.
• Sine burst test replaced Transient test at space segment equipment level,
because rarely used, and it is merged with Transient at space segment
element level.
• Microvibration and Audible noise:
o new requirements for microvibration in particular to cover signal
measurement and background noise measurement and background noise
mitigation actions,
o requirements on Audible noise were changed, and some deleted, at
equipment level to account for the tight dependence on the mounting
structure.
• Polarity test: new requirement for polarity test of non-critical modes.
This document has been prepared under a standardization request given to CEN
by the European Commission and the European Free Trade Association.
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, Serbia,
Slovakia, Slovenia, Spain, Sweden, Switzerland, Türkiye 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 sequences of tests 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 test conditions, test input tolerances and measurement
uncertainties;
• 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 tests, for each model, is
defined by tailoring 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 1 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 input tolerances, and
measurement uncertainties,
• General requirements for development tests pertinent to the start of the
qualification test programme,
NOTE 2 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,
• Testing peculiarities of space vehicles constellations,
• In-orbit testing,
• Testing of space segment subsystems,
NOTE 3 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 4 For verification of flight or ground software,
ECSS-E-ST-40 and ECSS-Q-ST-80 apply.
• Testing of two-phase heat transport equipment,
NOTE 5 For acceptance and 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 16603-20-01 ECSS-E-ST-20-01 Space engineering - Multipactor 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 3740:2019 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
a. For the purpose of this standard; the terms and definitions from ECSS-S-
ST-00-01 apply, and in particular the following:
1. commissioning
2. flight model
3. lifetime
4. protoflight model
5. qualification model
6. space segment element
7. space segment equipment
8. space segment subsystem
9. structural model
10. system
11. test
b. For the purpose of this standard, the following terms and definitions from
ECSS-E-ST-10-02 apply:
1. model philosophy
c. For the purpose of this Standard, the following terms and definitions from
ECSS-E-ST-31 apply:
1. acceptance temperature range
2. design temperature range
3. minimum switch ON temperature
4. predicted temperature range
5. qualification temperature range
6. temperature reference point (TRP)
d. For the purpose of this Standard, the following terms and definitions from
ECSS-E-ST-32 apply:
1. factor of safety (FOS)
2. limit load (LL)
3. maximum design pressure (MDP)
4. proof test
e. For the purpose of this Standard, the following terms and definitions from
ECSS E ST-32-02 apply:
1. burst pressure
2. design burst pressure
3. proof factor
4. proof pressure
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 1 to entry: 0 dBA corresponds to 20 µPa.
3.2.2 abbreviated functional test (AFT)
See "reduced functional test (RFT)"
3.2.3 acceptance level
test level required by increasing the severity of an extreme level expected to be
encountered during the specified product lifetime for the purpose of
workmanship verification.
3.2.4 acceptance margin
increase in severity of the environmental, mechanical, electrical, EMC, or
operational extreme levels expected to be encountered during the specified
product lifetime for the purpose of workmanship verification
Note 1 to entry: This margin can include an increase in
level, an extension of range, an increase
in duration or cycles of exposure, as well
as any other appropriate increase in
severity.
3.2.5 crewed space segment element
space segment design to ensure the safe presence of crew onboard
3.2.6 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
3.2.7 environmental tests
tests applied to a product simulating (together or separately) environmental
conditions as encountered during its operational life cycle
Note 1 to entry: Environmental tests cover natural and
induced environments.
3.2.8 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 to entry: The main objectives of this test is to
demonstrate absence of design
manufacturing and integration error.
Note 2 to entry: 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).
3.2.9 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 to entry: This term is equivalent to limit load (as
defined in E-ST-32).
Note 2 to entry: Examples of events during life time are
transportation, handling, engine
ignition, engine burnout, and stage
separation.
3.2.10 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 to entry: E.g. lift-off, powered flight or re-entry.
Note 2 to entry: 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.
3.2.11 maximum expected shock
worst cases of the collection of the shock at their mounting interface due to every
possible cause
Note 1 to entry: For example: causes of shocks are stage,
shroud or satellite separation pyro
devices, non-explosive actuators,
mechanisms with energy release,
appendage latching, and fuel valves.
Note 2 to entry: Shocks can be characterized by their
time histories, shock response
spectrum, or impulse geometry.
Note 3 to entry: Refer to ECSS-E-HB-32-25 for
additional information.
3.2.12 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 to entry: E.g. lift-off acoustic field, aerodynamic
excitations, and transmitted structure-
borne vibration.
Note 2 to entry: 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 to entry: 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.
3.2.13 maximum predicted temperature
maximum value of the predicted temperature range
3.2.14 minimum predicted temperature
minimum value of the predicted temperature range
3.2.15 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 1 to entry: 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
3.2.16 operational modes
combination of operational configurations or conditions that can occur during
the product lifetime for space segment equipment or space segment element
Note 1 to entry: For example: Power-on or power-off,
command modes, readout modes,
attitude control modes, antenna stowed
or deployed, and spinning or de-spun.
3.2.17 performance test
test to verify that the item under test performs according to its specifications
while respecting its operational requirements
Note 1 to entry: Performance tests are mission specific
therefore their details are not specified
under this standard.
3.2.18 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 to entry: 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 to entry: A polarity error can be generated by
any component of the functional chain:
sensor or actuator design, sensor or
actuator mounting, harness, interface
units, software algorithms.
Note 3 to entry: Polarity inversion on Safe Mode control
loops can cause a satellite loss.
Note 4 to entry: This term "sign test" is synonymous.
3.2.19 qualification level
test level required by increasing the severity of an acceptance level for the
purpose of design margin demonstration
3.2.20 qualification margin
increase in severity of the environmental, mechanical, electrical, EMC, or
operational extreme levels expected to be encountered during the specified
product lifetime for the purpose of design margin demonstration
Note 1 to entry: This margin can include an increase in
level, an extension of range, an increase
in duration or cycles of exposure, as
well as any other appropriate increase
in severity.
3.2.21 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 1 to entry: The term "abbreviated functional test
(AFT)" is synonymous.
3.2.22 residual life
time left before a product is no longer able to achieve minimum acceptable
performance requirements, including availability
Note 1 to entry: Criteria can be estimated in terms of
serviceability or structural strength for
example.
3.2.23 resolution
minimum readable value of a quantity on a measurement system
Note 1 to entry: The resolution is accounted for in the
overall uncertainty evaluation.
3.2.24 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 1 to entry: Resonance search is also known as
“signature test”, “low level sinusoidal
vibration test”, “low level sine sweep”,
“low level sweep” or “low level test”.
3.2.25 reverberation time (T60)
duration necessary for the sound level to decrease by 60 dB after the switch off
of the sound source
3.2.26 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 to entry: 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 to entry: 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 to entry: The Shock Response Spectrum allows
characterizing the shock effect in order
to estimate its severity or its damaging
potential.
Note 4 to entry: 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.
3.2.27 sign test
see “polarity test”
3.2.28 temperature cycle
transition from an initial temperature to the same temperature, with excursion
within a specified range
3.2.29 temperature plateau
time, during specified steps of an environmental test, with fulfilment of specified
stabilization criteria applicable to a temperature level.
Note 1 to entry: Specified criteria cover the instants of
entry and exit of the temperature
plateau, and its total duration.
3.2.30 test block
aggregation of several tests grouped by discipline
3.2.31 test input tolerance
limiting or permitted specified range of values of a specified test level or of a
specified test duration without affecting the test objectives
Note 1 to entry: This range is typically specified as
deviation from a specified value, or as
an explicit range of allowed values. It
can be symmetrical, as in 40 ±0,1, or
asymmetrical, such as 40 -0,2/+0,1.
3.2.32 thermal test at room pressure
test conducted at room pressure and under predefined temperature conditions
to demonstrate the capability of the test specimen to operate according to
requirements
Note 1 to entry: Temperature conditions can be
expressed as temperature level,
gradient, difference and variation.
Note 2 to entry: The room pressure is the pressure at
Earth surface level (about 1013 hPa).
Note 3 to entry: The terms "temperature cycling test at
room pressure" and "room pressure
temperature cycling test" are
synonymous.
Note 4 to entry: The "temperature cycling test at room
pressure" is also called "thermal
cycling" (e.g., US standards).
3.2.33 thermal test at mission pressure
test conducted at mission pressure and under predefined temperature conditions
to demonstrate the capability of the test specimen to operate according to
requirements
Note 1 to entry: Temperature conditions can be
expressed as temperature level,
gradient, difference and variation.
Note 2 to entry: The pressure is representative of the
mission dependent pressure. For
example, Mars or Venus atmospheric
pressure, pressure in a lander or during
a balloon ascent/descent, a space station
pressurized module.
Note 3 to entry: The terms "temperature cycling test at
mission pressure" and "mission
pressure temperature cycling test" are
synonymous.
3.2.34 thermal vacuum
test conducted in vacuum under predefined temperature conditions to
demonstrate the capability of the test item to operate according to requirements
Note 1 to entry: Temperature conditions can be
expressed as temperature level,
gradient, difference and variation.
Note 2 to entry: The terms "temperature cycling test in
vacuum" and "vacuum temperature
cycling test" are synonymous.
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 verification
AIV
acceptance vibration test
AVT
configuration control board
CCB
centre of gravity
CoG
document requirements definition
DRD
Abbreviation Meaning
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
interface control document
ICD
key inspection point
KIP
launcher coupled dynamic analysis
LCDA
latching current limiter
LCL
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
Abbreviation Meaning
sound pressure level
SPL
shock response spectrum
SRS
system validation test
SVT
thermal balance
TB
telecommand
TC
thermal control system
TCS
telemetry
TM
test procedure
TPRO
test review
TR
test review board
TRB
temperature reference point
TRP
test report
TRPT
test readiness review
TRR
thermal vacuum
TV
𝐀𝐀
𝐓𝐓
𝐦𝐦𝐦𝐦𝐦𝐦 maximum value of the acceptance temperature range
required at a unit TRP
𝐀𝐀
𝐓𝐓
𝐦𝐦𝐦𝐦𝐦𝐦 minimum value of the acceptance temperature range
required at a unit TRP
𝐃𝐃
𝐓𝐓
𝐦𝐦𝐦𝐦𝐦𝐦 maximum value of the design temperature range
required at a unit TRP
𝐃𝐃
𝐓𝐓
minimum value of the design temperature range
𝐦𝐦𝐦𝐦𝐦𝐦
required at a unit TRP
𝐐𝐐
𝐓𝐓
𝐦𝐦𝐦𝐦𝐦𝐦 maximum value of the qualification temperature
range required at a unit TRP
𝐐𝐐
𝐓𝐓
minimum value of the qualification temperature
𝐦𝐦𝐦𝐦𝐦𝐦
range required at a unit TRP
non-operating temperature
TNop
operating temperature
TOp
test specification
TSPE
telemetry, tracking and command
TT&C
travelling wave tube
TWT
verification control document
VCD
verification plan
VP
3.4 Nomenclature
The following nomenclature applies throughout this document:
a. The word “shall” is used in this Standard to express requirements. All the
requirements are expressed with the word “shall”.
b. The word “should” is used in this Standard to express recommendations.
All the recommendations are expressed with the word “should”.
NOTE It is expected that, during tailoring,
recommendations in this document are either
converted into requirements or tailored out.
c. The words “may” and “need not” are used in this Standard to express
positive and negative permissions, respectively. All the positive
permissions are expressed with the word “may”. All the negative
permissions are expressed with the words “need not”.
d. The word “can” is used in this Standard to express capabilities or
possibilities, and therefore, if not accompanied by one of the previous
words, it implies descriptive text.
NOTE In ECSS “may” and “can” have completely
different meanings: “may” is normative
(permission), and “can” is descriptive.
e. The present and past tenses are used in this Standard to express statements
of fact, and therefore they imply descriptive text.
General requirements
4.1 Test programme
a. A coherent test programme shall be established, encompassing each
verification stage and level to implement the verification by testing.
NOTE 1 The testing programme is performed
incrementally at different product
decomposition levels.
NOTE 2 Refer to clause 3.1 for determining the type of
item for which the test programme is defined
(i.e. space segment equipment or space segment
element) and to ECSS-S-ST-00-01 Glossary of
terms.
NOTE 3 The number and type of testing levels depends
upon the complexity of the project and on its
characteristics in accordance with the
Verification programme (see ECSS-E-ST-10-02).
NOTE 4 The test programme documentation is defined
in 4.3.3.
b. The customer and the supplier shall agree the need to treat a space segment
element as a space segment equipment.
This is typically the case for small instrument.
c. AIT Plan and test specifications shall be derived from the product
requirements, verification plan and verification control document (VCD).
Verification plan and VCD are defined in ECSS-
E-ST-10-02.
d. Test procedures shall be derived from test specifications and AIT Plan.
e. Test programme and its implementation shall be in conformance with
safety requirements of ECSS-Q-ST-40 and ECSS-Q-ST-20-07.
4.2 Development test prior qualification
a. Development test of a product shall be completed prior to the start of its
formal qualification testing.
NOTE Development tests are conducted over a range of
operating conditions that can exceed the design
range.
b. Development tests shall not be conducted on qualification or flight models
or parts of it.
c. Records of test configuration, test results and other pertinent data shall be
maintained.
This kind of information can be used for
investigation when failure occurs during the
qualification and acceptance, or for other
investigations.
4.3 Test management
4.3.1 Gen
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