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
SIST EN 16603-10-03:2022
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
SIST EN 16603-10-03:2022 en,fr,de
2003-01.Slovenski inštitut za standardizacijo. Razmnoževanje celote ali delov tega standarda ni dovoljeno.
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SIST EN 16603-10-03:2022
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SIST EN 16603-10-03:2022
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.
CEN-CENELEC Management Centre:
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.
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SIST EN 16603-10-03:2022
EN 16603-10-03:2022 (E)
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
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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
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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
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SIST EN 16603-10-03:2022
EN 16603-10-03:2022 (E)
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,
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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.
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EN 16603-10-03:2022 (E)
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;
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EN 16603-10-03:2022 (E)
• 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.
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1
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,
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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.
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EN 16603-10-03:2022 (E)
2
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
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3
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
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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.
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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.
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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 t
...
SLOVENSKI STANDARD
oSIST prEN 16603-10-03:2021
01-september-2021
Vesoljska tehnika - Preskušanje
Space engineering - Testing
Raumfahrttechnik - Tests
Ingénierie spatiale - Vérification par essai
Ta slovenski standard je istoveten z: prEN 16603-10-03
ICS:
49.140 Vesoljski sistemi in operacije Space systems and
operations
oSIST prEN 16603-10-03:2021 en,fr,de
2003-01.Slovenski inštitut za standardizacijo. Razmnoževanje celote ali delov tega standarda ni dovoljeno.
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oSIST prEN 16603-10-03:2021
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oSIST prEN 16603-10-03:2021
EUROPEAN STANDARD
DRAFT
prEN 16603-10-03
NORME EUROPÉENNE
EUROPÄISCHE NORM
June 2021
ICS 49.140
Will supersede EN 16603-10-03:2014
English version
Space engineering - Testing
Ingénierie spatiale - Vérification par essai Raumfahrttechnik - Tests
This draft European Standard is submitted to CEN members for enquiry. It has been drawn up by the Technical Committee
CEN/CLC/JTC 5.
If this draft becomes a European Standard, 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.
This draft European Standard was established by CEN and CENELEC 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, Turkey and United Kingdom.
Recipients of this draft are invited to submit, with their comments, notification of any relevant patent rights of which they are
aware and to provide supporting documentation.Recipients of this draft are invited to submit, with their comments, notification
of any relevant patent rights of which they are aware and to provide supporting documentation.
Warning : This document is not a European Standard. It is distributed for review and comments. It is subject to change without
notice and shall not be referred to as a European Standard.
CEN-CENELEC Management Centre:
Rue de la Science 23, B-1040 Brussels
© 2021 CEN/CENELEC All rights of exploitation in any form and by any means Ref. No. prEN 16603-10-03:2021 E
reserved worldwide for CEN national Members and for
CENELEC Members.
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oSIST prEN 16603-10-03:2021
prEN 16603-10-03:2021 (E)
Table of contents
European Foreword . 5
Introduction . 6
1 Scope . 8
2 Normative references . 10
3 Terms, definitions and abbreviated terms . 11
3.1 Terms from other standards . 11
3.2 Terms specific to the present standard . 12
3.3 Abbreviated terms. 17
3.4 Nomenclature . 19
4 General requirements. 21
4.1 Test programme . 21
4.2 Development test prior qualification . 21
4.3 Test management . 22
4.3.1 General . 22
4.3.2 Test reviews . 22
4.3.3 Test documentation . 26
4.3.4 Anomaly or failure during testing . 27
4.3.5 Test data . 27
4.4 Test conditions, input tolerances, and measurement uncertainties . 27
4.4.1 Test conditions . 27
4.4.2 Test input tolerances . 28
4.4.3 Measurement uncertainties . 30
4.5 Test objectives . 32
4.5.1 General requirements . 32
4.5.2 Qualification testing . 32
4.5.3 Acceptance testing . 32
4.5.4 Protoflight testing . 33
4.6 Retesting . 34
4.6.1 Overview . 34
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4.6.2 Implementation of a design modification after completion of qualification . 34
4.6.3 Storage after protoflight or acceptance testing . 34
4.6.4 Space segment element or equipment to be re-flown . 35
4.6.5 Flight use of qualification Space segment element or equipment . 35
5 Space segment equipment test requirements . 36
5.1 General requirements . 36
5.2 Qualification tests requirements . 38
5.3 Acceptance test requirements . 48
5.4 Protoflight test requirements . 54
5.5 Space segment equipment test programme implementation requirements . 60
5.5.1 General tests . 60
5.5.2 Mechanical tests . 63
5.5.3 Structural integrity tests . 67
5.5.4 Thermal tests . 68
5.5.5 Electrical/RF tests . 70
5.5.6 Mission specific test . 71
6 Space segment element test requirements . 73
6.1 General requirements . 73
6.2 Qualification test requirements . 73
6.3 Acceptance test requirements . 81
6.4 Protoflight test requirements . 88
6.5 Space segment elements test programme implementation requirements . 95
6.5.1 General tests . 95
6.5.2 Mechanical tests . 99
6.5.3 Structural integrity tests . 106
6.5.4 Thermal tests . 107
6.5.5 Electromagnetic tests . 109
6.5.6 Mission specific tests . 110
6.5.7 Crewed mission specific tests . 110
7 Pre-launch testing . 112
Annex A (normative) Assembly, integration and test plan (AIT Plan) - DRD . 114
Annex B (normative) Test specification (TSPE) - DRD . 117
Annex C (normative) Test procedure (TPRO) - DRD . 120
Annex D (informative) Guidelines for tailoring and verification of this standard
. 123
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Bibliography . 127
Figures
Figure 5-1: Space segment equipment typical sequence of tests . 38
Figure D-1 : Logic for customer tailoring and supplier answer through compliance and
verification matrix . 124
Figure D-2 : Clauses selection in First step of the tailoring . 125
Tables
Table 4-1: Allowable test input tolerances . 29
Table 4-2: Typical measurement uncertainties from test centers . 31
Table 5-1: Space segment equipment - Qualification test baseline . 39
Table 5-2: Space segment equipment - Qualification test levels and duration . 41
Table 5-3: Space segment equipment - Acceptance test baseline . 49
Table 5-4: Space segment equipment - Acceptance test levels and duration . 51
Table 5-5: Space segment equipment - Protoflight test baseline . 54
Table 5-6: Space segment equipment - Protoflight test levels and duration . 56
Table 6-1: Space segment element - Qualification test baseline . 74
Table 6-2: Space segment element - Qualification test levels and duration . 77
Table 6-3: Space segment element - Acceptance test baseline . 81
Table 6-4: Space segment element - Acceptance test levels and duration . 84
Table 6-5: Space segment element - Protoflight test baseline . 88
Table 6-6: Space segment element - Protoflight test levels and duration . 91
Table D-1 : Guideline for verification close-out . 125
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European Foreword
This document (prEN 16603-10-03:2021) has been prepared by Technical Committee
CEN/CLC/TC 5 “Space”, the secretariat of which is held by DIN (Germany).
This document (prEN 16603-10-03:2021) originates from ECSS-E-ST-10-03C Rev.1 DIR1.
This document is currently submitted to the ENQUIRY.
This document will supersede EN 16603-10-03:2014.
The main changes with respect to EN 16603-10-03:2014 are listed below:
• Implementation of Change Requests received to the ECSS equivalent standard
• xxxx --- The final Change log will be completed before publication --- xxxx
This document has been developed to cover specifically space systems and will therefore
have precedence over any EN covering the same scope but with a wider do-main of
applicability (e.g.: aerospace).
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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).
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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.
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1
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 input tolerances, and
measurement uncertainties,
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,
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NOTE 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 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.
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2
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 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 3740:2000 Acoustics - Determination of sound power levels of noise
sources - Guidelines for the use of basic standards
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3
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. flight model
2. lifetime
3. protoflight model
4. qualification model
5. space segment element
6. space segment equipment
7. space segment subsystem
8. structural model
9. system
b. For the purpose of this standard, the following terms and definitions from ECSS-
E-ST-10-02 apply:
1. commissioning
2. model philosophy
3. test
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. burst pressure
2. design burst pressure
3. factor of safety
4. limit load (LL)
5. maximum design pressure (MDP)
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6. proof factor
7. proof pressure
8. 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 <>
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 <>
3.2.7 crewed space segment element
space segment design to ensure the safe presence of crew onboard
3.2.8 <>
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
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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.
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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 <>
3.2.17 maximum predicted temperature
maximum value of the predicted temperature range
3.2.18 minimum predicted temperature
minimum value of the predicted temperature range
3.2.19 <>
NOTE
3.2.20 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
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3.2.21 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.
3.2.22 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.
3.2.23 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 alg
...
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