Space systems -- General test requirements for launch vehicles

This document establishes general test requirements for launch vehicles equipped with liquid-propellant engines, launched from stationary ground-, sea- and air-based launchers, in all phases of their development.

Systèmes spatiaux -- Exigences générales d'essai pour véhicules lanceurs

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INTERNATIONAL ISO
STANDARD 24917
Second edition
2020-07
Space systems — General test
requirements for launch vehicles
Systèmes spatiaux — Exigences générales d'essai pour véhicules
lanceurs
Reference number
ISO 24917:2020(E)
ISO 2020
---------------------- Page: 1 ----------------------
ISO 24917:2020(E)
COPYRIGHT PROTECTED DOCUMENT
© ISO 2020

All rights reserved. Unless otherwise specified, or required in the context of its implementation, no part of this publication may

be reproduced or utilized otherwise in any form or by any means, electronic or mechanical, including photocopying, or posting

on the internet or an intranet, without prior written permission. Permission can be requested from either ISO at the address

below or ISO’s member body in the country of the requester.
ISO copyright office
CP 401 • Ch. de Blandonnet 8
CH-1214 Vernier, Geneva
Phone: +41 22 749 01 11
Email: copyright@iso.org
Website: www.iso.org
Published in Switzerland
ii © ISO 2020 – All rights reserved
---------------------- Page: 2 ----------------------
ISO 24917:2020(E)
Contents Page

Foreword ..........................................................................................................................................................................................................................................v

Introduction ................................................................................................................................................................................................................................vi

1 Scope ................................................................................................................................................................................................................................. 1

2 Normative references ...................................................................................................................................................................................... 1

3 Terms and definitions ..................................................................................................................................................................................... 1

4 Abbreviated terms .............................................................................................................................................................................................. 4

5 Testing philosophy ............................................................................................................................................................................................. 5

5.1 Objectives, tasks and principles of development test for launch vehicle and its units ............. 5

5.1.1 Development test............................................................................................................................................................. 5

5.1.2 Objectives ............................................................................................................................................................................... 5

5.1.3 Test planning ....................................................................................................................................................................... 6

5.1.4 Organization and test sequence .......................................................................................................................... 6

5.1.5 Development test programme plan ................................................................................................................. 6

5.1.6 Effects of implementation of principles ....................................................................................................... 9

5.2 LV and rocket unit test types during their development .................................................................................10

5.2.1 Tests in development phase ................................................................................................................................10

5.2.2 Test in routine production phase ...................................................................................................................11

5.2.3 Test for units .....................................................................................................................................................................12

6 Test type and programme requirements .................................................................................................................................12

6.1 Test object and type requirements .....................................................................................................................................12

6.1.1 Engineering and engineering-technological breadboarding ..................................................12

6.1.2 Integration/check-out mock-up test ............................................................................................................13

6.1.3 Electrical mock-up test ............................................................................................................................................14

6.1.4 Fuelling mock-up test ...............................................................................................................................................14

6.1.5 Antenna mock-up test ..............................................................................................................................................15

6.1.6 Static load test .................................................................................................................................................................16

6.1.7 Vibration test ...................................................................................................................................................................16

6.1.8 Acoustic test ......................................................................................................................................................................16

6.1.9 Shock load test ................................................................................................................................................................17

6.1.10 Cold test of rocket units ..........................................................................................................................................17

6.1.11 Hot firing test ...................................................................................................................................................................18

6.1.12 Electromagnetic compatibility (EMC) test .............................................................................................19

6.1.13 Climatic test .......................................................................................................................................................................20

6.1.14 Fire and explosion safety test ............................................................................................................................20

6.1.15 Lightning and statics resistance test ...........................................................................................................20

6.1.16 Transportability test ..................................................................................................................................................21

6.1.17 Lifetime test ......................................................................................................................................................................21

6.1.18 Test at integration site and launching site ..............................................................................................22

6.1.19 Flight test .............................................................................................................................................................................23

6.1.20 LV components disposal requirements .....................................................................................................24

6.1.21 Batch production test ...............................................................................................................................................24

6.2 General requirements to development test programme and individual test programme .25

6.2.1 Contents of development test programme plan ................................................................................25

6.2.2 Test programme plans for test models ......................................................................................................27

6.2.3 Requirements for test methods established by test programme plans .........................27

6.2.4 Contents of test programme plans ................................................................................................................27

6.2.5 Requirements for communications systems programme plan .............................................27

6.3 General test object requirements.........................................................................................................................................28

6.3.1 Test objects ........................................................................................................................................................................28

6.3.2 Documentation for test objects ........................................................................................................................28

7 Criteria .........................................................................................................................................................................................................................28

© ISO 2020 – All rights reserved iii
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ISO 24917:2020(E)

8 Reporting ...................................................................................................................................................................................................................29

Annex A (informative) Manufacturing stage, item categories and test categories ............................................30

Annex B (informative) Requirements applicability matrix .......................................................................................................31

Annex C (informative) Typical test report contents ..........................................................................................................................33

Annex D (informative) Typical test programme plan contents..............................................................................................34

Bibliography .............................................................................................................................................................................................................................37

iv © ISO 2020 – All rights reserved
---------------------- Page: 4 ----------------------
ISO 24917:2020(E)
Foreword

ISO (the International Organization for Standardization) is a worldwide federation of national standards

bodies (ISO member bodies). The work of preparing International Standards is normally carried out

through ISO technical committees. Each member body interested in a subject for which a technical

committee has been established has the right to be represented on that committee. International

organizations, governmental and non-governmental, in liaison with ISO, also take part in the work.

ISO collaborates closely with the International Electrotechnical Commission (IEC) on all matters of

electrotechnical standardization.

The procedures used to develop this document and those intended for its further maintenance are

described in the ISO/IEC Directives, Part 1. In particular, the different approval criteria needed for the

different types of ISO documents should be noted. This document was drafted in accordance with the

editorial rules of the ISO/IEC Directives, Part 2 (see www .iso .org/ directives).

Attention is drawn to the possibility that some of the elements of this document may be the subject of

patent rights. ISO shall not be held responsible for identifying any or all such patent rights. Details of

any patent rights identified during the development of the document will be in the Introduction and/or

on the ISO list of patent declarations received (see www .iso .org/ patents).

Any trade name used in this document is information given for the convenience of users and does not

constitute an endorsement.

For an explanation of the voluntary nature of standards, the meaning of ISO specific terms and

expressions related to conformity assessment, as well as information about ISO's adherence to the

World Trade Organization (WTO) principles in the Technical Barriers to Trade (TBT), see www .iso .org/

iso/ foreword .html.

This document was prepared by Technical Committee ISO/TC 20, Aircraft and space vehicles,

Subcommittee SC 14, Space systems and operations.

This second edition cancels and replaces the first edition (ISO 24917:2010), which has been technically

revised. The main changes compared to the previous edition are as follows:
— correction of terms and definitions according to other existing standards;
— modification of the “Flight vehicle development test structure” (Figure 1);
— modification of the “Requirements applicability matrix” (Annex B).

Any feedback or questions on this document should be directed to the user’s national standards body. A

complete listing of these bodies can be found at www .iso .org/ members .html.
© ISO 2020 – All rights reserved v
---------------------- Page: 5 ----------------------
ISO 24917:2020(E)
Introduction

This document provides space launch vehicle customers, contractors and manufacturers with general

requirements for test types and programmes for space launch vehicles and rocket units (modules) for

use in the documentation associated with their test activity.

This document is intended to help reduce the development time and cost of space launch vehicles and

rocket units, and to enhance their quality and reliability through the use of common, optimized and

approved requirements in the space launch vehicle test scope and organization.
vi © ISO 2020 – All rights reserved
---------------------- Page: 6 ----------------------
INTERNATIONAL STANDARD ISO 24917:2020(E)
Space systems — General test requirements for launch
vehicles
1 Scope

This document establishes general test requirements for launch vehicles equipped with liquid-

propellant engines, launched from stationary ground-, sea- and air-based launchers, in all phases of

their development.
2 Normative references

The following documents are referred to in the text in such a way that some or all of their content

constitutes requirements of this document. For dated references, only the edition cited applies. For

undated references, the latest edition of the referenced document (including any amendments) applies.

ISO 14302, Space systems — Electromagnetic compatibility requirements
ISO 14303, Space systems — Launch-vehicle-to-spacecraft interfaces
3 Terms and definitions
For the purposes of this document, the following terms and definitions apply.

ISO and IEC maintain terminological databases for use in standardization at the following addresses:

— ISO Online browsing platform: available at https:// www .iso .org/ obp
— IEC Electropedia: available at http:// www .electropedia .org/
3.1
space-rocket complex

set of flight vehicles (3.2) with functionally relative technical facilities intended for transportation,

storage, maintenance service, preparation, launching and flight control of flight vehicles with payload

3.2
flight vehicle
launch vehicle (3.3) including space nose section (3.6)
3.3
launch vehicle
vehicle designed to transport payloads to space

[SOURCE: ISO 10795:2019, 3.139, modified — The preferred term "launcher" has been removed.]

3.4
unit

lowest level of hardware assembly for which acceptance (3.26) and qualification tests (3.25) are required

[SOURCE: ISO 15864:2004, 3.1.13]
3.5
orbital stage

stage of flight vehicle (3.2) capable of injecting payloads into their planned orbit from the sub-orbital

trajectory that resulted from operation of lower stages
© ISO 2020 – All rights reserved 1
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ISO 24917:2020(E)
3.6
nose section
set of a fairing (3.7) and fairing adapter
3.7
fairing

technical device intended to protect a spacecraft or a space nose section (3.6) from external influences

during transportation on a launcher, and to keep it on trajectory when launching into orbit

3.8
integration site

equipment and facility designed for launch vehicle (3.3) storage, assembly, testing, preparation,

maintenance, servicing and preparation for transportation to the launch pad (3.9)

[SOURCE: ISO/TR 17400:2003, 3.1]
3.9
launch pad

equipment and facility designed to provide for the pre-launch and launch operations of spacecraft

[SOURCE: ISO/TR 17400:2003, 3.3]
3.10
statement of work

contractual document prepared during project initiation and planning that describes what the project

needs to deliver and outlines all work required to complete the project
[SOURCE: ISO 10795:2019, 3.229]
3.11
technical specification

specification expressing technical requirements for designing and developing the solution to be

implemented

Note 1 to entry: The technical specification evolves from the functional specification and defines the technical

requirements for the selected solution as part of a business agreement.
[SOURCE: ISO 10795:2019, 3.238]
3.12
test metrological support

establishment and application of scientific and organizational foundations, technical facilities, rules and

standards necessary to achieve the measurement traceability, precision, completeness, operativeness

and the reliability of parameters control and technical performance characteristics of items

3.13
development test programme plan

obligate organizational and methodological document which specifies the test object (3.23) and

objectives, types, sequence and scope of experiments, order, conditions, place, time, support of test, test

reporting and responsibilities for test support and performance
3.14
reliability assurance programme plan

document specifying a set of requirements and measures aimed at providing and controlling the

satisfaction of requirements established in the statement of work (3.10) for a space launch vehicle (3.3)

and its components’ reliability during their development
2 © ISO 2020 – All rights reserved
---------------------- Page: 8 ----------------------
ISO 24917:2020(E)
3.15
development test

test to provide information that can be used to check the validity of analytic techniques and assumed

design parameters, uncover unexpected system response characteristics, evaluate design changes,

determine interface compatibility, prove qualification and acceptance procedures and techniques,

check manufacturing technology, or establish accept/reject criteria
[SOURCE: ISO 10786:2011, 3.17]
3.16
safety assurance programme plan

document which establishes a set of requirements and measures aimed at assuring that all safety

risks associated with the space launch vehicle (3.3) design, development, manufacture and use are

accordingly identified, assessed, minimized, controlled and accepted
3.17
communications systems programme plan

document establishing the structure of communication systems (including telemetry measurement,

command and tracking communication lines, etc.) hardware born set on launch vehicle (3.3), launch pad

(3.9) and positioned along the flight route necessary for performance the measurement requirements,

location and orientation of sensors and their characteristics, frequency bands, minimal frequency of

sensor scanning
3.18
flight test
test in real conditions of the functioning and performance of target tasks
3.19
prototype model

item produced in the research and development process applying the newly developed working

engineering and technological documentation for test verification of the conformity of its parameters

and characteristics with the requirements specified in statement of work (3.10) to research and

development and correctness of adopted technical solutions
3.20
model
test mock-up

structurally, or physically, or structurally and physically similar item presenting a simplified

reproduction of a test object (3.23) or its part intended for testing
3.21
structural model
model (3.20) representing the structural flight characteristics
3.22
electrical model
model (3.20) representing the electrical flight characteristics
3.23
test object
item under test
3.24
test type
classified test grouping identified according to a certain attribute
© ISO 2020 – All rights reserved 3
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ISO 24917:2020(E)
3.25
qualification test

required formal contractual test used to demonstrate that the design, manufacturing, and assembly

have resulted in hardware designs conforming to specification requirements

[SOURCE: ISO 14623:2003, 2.52, modified — The term has been changed to singular form.]

3.26
acceptance test

required formal test conducted on flight hardware to ascertain that the materials, manufacturing

processes and workmanship meet specifications and that the hardware is acceptable for intended usage

[SOURCE: ISO 14623:2003, 2.2, modified — The term has been changed to singular form.]

3.27
operational test

test conducted at the launch vehicle (3.3) site in an operational environment, with the equipment in its

operational configuration
3.28
critical unit

unit (3.4) whose failure can affect the system operation sufficiently to cause the failure of the stated

vehicle objectives or a partial loss of the mission, or whose proper performance is essential from a

safety standpoint
3.29
pyrotechnic device

device or assembly containing, or actuated by, propellants or explosives, with the exception of large

rocket motors

EXAMPLE Initiators, ignitors, detonators, squibs, safe and arm devices, booster cartridges, pressure

cartridges, separation bolts and nuts, pin pullers, linear separation systems, shaped charges, explosive

guillotines, pyrovalves, detonation transfer assemblies (mild detonating fuse, confined detonating cord, confined

detonating fuse, shielded mild detonating cord, etc.), through-bulkhead initiators, mortars, thrusters, explosive

circuit interrupters, and other similar items.
[SOURCE: ISO 26871:2012, 3.1.31]
4 Abbreviated terms
CSP communications systems programme plan
CTS control and test station
DTP development test programme plan
EMC electromagnetic compatibility
FTP flight test programme plan
FV flight vehicle
IS integration site
LPRE liquid-propellant engine
LS launching site
LV launch vehicle
4 © ISO 2020 – All rights reserved
---------------------- Page: 10 ----------------------
ISO 24917:2020(E)
OCN on-board cable network
OS orbital stage
PHS pneumatic/hydraulic system
RAP reliability assurance programme plan
SAP safety assurance programme plan
SC spacecraft
SNS space nose section
SOW statement of work
SRC space-rocket complex
5 Testing philosophy

5.1 Objectives, tasks and principles of development test for launch vehicle and its units

5.1.1 Development test

A development test is one of the methods of verification which guarantees that all characteristics of the

FV meet the requirements of the SOW. The FV is tested in the SRC during the launch preparation for

test flight.

The development test of an FV and units of an LV includes ground development test phases and a

flight test. The complete test programme for launch vehicles, upper stage, encompasses development,

qualification, acceptance, pre-launch validation and follow-on operational test and evaluations. The

test programme encompasses the testing of progressively more complex assemblies of hardware and

computer software. Generally, the FV development test structure may be represented as a scheme in

compliance with ISO 14300-1 (see Figure 1).
5.1.2 Objectives
5.1.2.1 Objectives of ground development test

The main objective of a ground development test is to verify the FV preparation technology for launch

and launch itself, preliminarily to verify and evaluate the implementation of the specified parameters

and characteristics, operation and interaction of the FV and its components when the operation

conditions are being simulated (or under effect of these conditions).
5.1.2.2 Objectives of flight test

The main objective of a flight test is to comprehensively check the FV serviceability and confirm the

SOW-specified requirements for the space rocket complex under real operation conditions.

5.1.2.3 Objectives for reliability and safety programmes

One of the main objectives of the LV (OS) ground development test is to achieve the SOW-assigned levels

of reliability and safety indexes before flight test commencement and confirm these during the flight

test. The reliability and safety index levels are normalized in the RAP and SAP, the latter including an

environmental safety guarantee.
© ISO 2020 – All rights reserved 5
---------------------- Page: 11 ----------------------
ISO 24917:2020(E)
5.1.2.4 Objectives of test for launch vehicle and its units

The main objectives of the development test of an FV, LV and its units are as follows:

a) verification of unit structure strength, rigidity, confirmation of rocket module parameters,

verification of equipment mechanical loading regimes;
b) breadboarding;
c) test of technological cycle of preparing FV for launch and launch itself;

d) comprehensive verification of units functioning during launch and propulsion systems operation in

the assigned regimes;
e) verification of the ground technical means/launch vehicle compatibility;
f) test of FV interfaces [LV, upper stage vehicle, spacecraft (SC)];
g) confirmation of the correctness of adopted engineering solutions;

h) verification of the sufficiency of measuring aids and telemetry data processing techniques;

i) individual tests of all FV components;
j) verification of operation convenience;
k) personnel training.
5.1.3 Test planning

The tasks to be solved during LVs testing are identified according to the design, assigned characteristics,

LV test maturity, design (modernization) novelty, dedicated operation conditions change and are

presented in the test programmes.
5.1.4 Organization and test sequence

The organization and order for conducting the development test are determined by the comprehensive

development test programme plan.
5.1.5 Development test programme plan
5.1.5.1 Planning

In order to meet the assigned LV (OS) characteristics requirements, the supplier plans a development test.

5.1.5.2 Initiation of the programme

The comprehensive development test programme plan is developed in accordance with the LV (OS)

hierarchical structure. The main starting documents for developing the FV development test programme

are the statement of work, the preliminary project and the reliability assurance programme.

6 © ISO 2020 – All rights reserved
---------------------- Page: 12 ----------------------
ISO 24917:2020(E)
Figure 1 — Flight vehicle development test structure
5.1.5.3 Contents of development test programme plan

The FV comprehensive development test programme is a common system of independent, particular

programme-technical documents, identifying the individual test objectives and scope, establishing the

criteria of OS or LV completeness and readiness for transferring to higher test levels.

The test sequence, scope and object, controlled characteristics, types of test and test phasing in the

course of LV (rocket unit) development are assigned by the LV (rocket unit) manufacturers-contractors

in the comprehensive development test programme, other test programmes.
5.1.5.4 Principles of development test programme plan

The LV (OS) development test programme plan (DTP) is based on the following principles:

a) system approach to the test planning with a detailed coordination of all types and phases of test;

absolute assurance and confirmation of the assigned characteristics of the SRC items during

ground test; use of results of optimizing the complex systems functioning as a component of other

complexes;

b) fulfilment of the main test work scope applying test facilities (stands, rigs, models, etc.) before

starting ready-made (standard) LV (OS) test under real operation conditions (full-scale test);

c) confirmation of all-round interaction of all FV components and demonstration of their functioning

reliability under full-scale conditions, as well as conduct of that part of test applying test means

which cannot be technically performed or are economically inexpedient within the assigned time

during the flight test, and on the basis of the following provisions:

1) determination of nomenclature and characteristics of modified and newly developed test stands

(rigs) on condition that they would assure fulfilment of the planned test types and scopes;

2) use (if necessary with updating) of test facilities, stands and technological fittings developed

for previous items;
© ISO 2020 – All rights reserved 7
---------------------- Page: 13 ----------------------
ISO 24917:2020(E)

3) assessment of the sufficiency and correctness of selecting equipment, control-measuring aids,

mathematical software for test;

4) planning of each experiment with the aim of obtaining a maximal data volume necessary for

evaluating the operation reliability; use of the capability of starting repeatedly the systems

and units under the conditions for conducting multiple tests (including different test typ

...

FINAL
INTERNATIONAL ISO/FDIS
DRAFT
STANDARD 24917
ISO/TC 20/SC 14
Space systems — General test
Secretariat: ANSI
requirements for launch vehicles
Voting begins on:
2020­04­23
Systèmes spatiaux — Exigences générales d'essai pour véhicules
lanceurs
Voting terminates on:
2020­06­18
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 SUPPOR TING
DOCUMENTATION.
IN ADDITION TO THEIR EVALUATION AS
Reference number
BEING ACCEPTABLE FOR INDUSTRIAL, TECHNO­
ISO/FDIS 24917:2020(E)
LOGICAL, COMMERCIAL AND USER PURPOSES,
DRAFT INTERNATIONAL STANDARDS MAY ON
OCCASION HAVE TO BE CONSIDERED IN THE
LIGHT OF THEIR POTENTIAL TO BECOME STAN­
DARDS TO WHICH REFERENCE MAY BE MADE IN
NATIONAL REGULATIONS. ISO 2020
---------------------- Page: 1 ----------------------
ISO/FDIS 24917:2020(E)
COPYRIGHT PROTECTED DOCUMENT
© ISO 2020

All rights reserved. Unless otherwise specified, or required in the context of its implementation, no part of this publication may

be reproduced or utilized otherwise in any form or by any means, electronic or mechanical, including photocopying, or posting

on the internet or an intranet, without prior written permission. Permission can be requested from either ISO at the address

below or ISO’s member body in the country of the requester.
ISO copyright office
CP 401 • Ch. de Blandonnet 8
CH­1214 Vernier, Geneva
Phone: +41 22 749 01 11
Fax: +41 22 749 09 47
Email: copyright@iso.org
Website: www.iso.org
Published in Switzerland
ii © ISO 2020 – All rights reserved
---------------------- Page: 2 ----------------------
ISO/FDIS 24917:2020(E)
Contents Page

Foreword ..........................................................................................................................................................................................................................................v

Introduction ................................................................................................................................................................................................................................vi

1 Scope ................................................................................................................................................................................................................................. 1

2 Normative references ...................................................................................................................................................................................... 1

3 Terms and definitions ..................................................................................................................................................................................... 1

4 Abbreviated terms .............................................................................................................................................................................................. 4

5 Testing philosophy ............................................................................................................................................................................................. 5

5.1 Objectives, tasks and principles of development test for launch vehicle and its units ............. 5

5.1.1 Development test............................................................................................................................................................. 5

5.1.2 Objectives ............................................................................................................................................................................... 5

5.1.3 Test planning ....................................................................................................................................................................... 6

5.1.4 Organization and test sequence .......................................................................................................................... 6

5.1.5 Development test programme plan ................................................................................................................. 6

5.1.6 Effects of implementation of principles ....................................................................................................... 9

5.2 LV and rocket unit test types during their development .................................................................................10

5.2.1 Tests in development phase ................................................................................................................................10

5.2.2 Test in routine production phase ...................................................................................................................11

5.2.3 Test for units .....................................................................................................................................................................12

6 Test type and programme requirements .................................................................................................................................12

6.1 Test object and type requirements .....................................................................................................................................12

6.1.1 Engineering and engineering­technological breadboarding ..................................................12

6.1.2 Integration/check­out mock­up test ............................................................................................................13

6.1.3 Electrical mock­up test ............................................................................................................................................14

6.1.4 Fuelling mock­up test ...............................................................................................................................................14

6.1.5 Antenna mock­up test ..............................................................................................................................................15

6.1.6 Static load test .................................................................................................................................................................16

6.1.7 Vibration test ...................................................................................................................................................................16

6.1.8 Acoustic test ......................................................................................................................................................................16

6.1.9 Shock load test ................................................................................................................................................................17

6.1.10 Cold test of rocket units ..........................................................................................................................................17

6.1.11 Hot firing test ...................................................................................................................................................................18

6.1.12 Electromagnetic compatibility (EMC) test .............................................................................................19

6.1.13 Climatic test .......................................................................................................................................................................20

6.1.14 Fire and explosion safety test ............................................................................................................................20

6.1.15 Lightning and statics resistance test ...........................................................................................................20

6.1.16 Transportability test ..................................................................................................................................................21

6.1.17 Lifetime test ......................................................................................................................................................................21

6.1.18 Test at integration site and launching site ..............................................................................................22

6.1.19 Flight test .............................................................................................................................................................................23

6.1.20 LV components disposal requirements .....................................................................................................24

6.1.21 Batch production test ...............................................................................................................................................24

6.2 General requirements to development test programme and individual test programme .25

6.2.1 Contents of development test programme plan ................................................................................25

6.2.2 Test programme plans for test models ......................................................................................................27

6.2.3 Requirements for test methods established by test programme plans .........................27

6.2.4 Contents of test programme plans ................................................................................................................27

6.2.5 Requirements for communications systems programme plan .............................................27

6.3 General test object requirements.........................................................................................................................................28

6.3.1 Test objects ........................................................................................................................................................................28

6.3.2 Documentation for test objects ........................................................................................................................28

7 Criteria .........................................................................................................................................................................................................................28

© ISO 2020 – All rights reserved iii
---------------------- Page: 3 ----------------------
ISO/FDIS 24917:2020(E)

8 Reporting ...................................................................................................................................................................................................................29

Annex A (informative) Manufacturing stage, item categories and test categories ............................................30

Annex B (informative) Requirements applicability matrix .......................................................................................................31

Annex C (informative) Typical test report contents ..........................................................................................................................33

Annex D (informative) Typical test programme plan contents..............................................................................................34

Bibliography .............................................................................................................................................................................................................................37

iv © ISO 2020 – All rights reserved
---------------------- Page: 4 ----------------------
ISO/FDIS 24917:2020(E)
Foreword

ISO (the International Organization for Standardization) is a worldwide federation of national standards

bodies (ISO member bodies). The work of preparing International Standards is normally carried out

through ISO technical committees. Each member body interested in a subject for which a technical

committee has been established has the right to be represented on that committee. International

organizations, governmental and non­governmental, in liaison with ISO, also take part in the work.

ISO collaborates closely with the International Electrotechnical Commission (IEC) on all matters of

electrotechnical standardization.

The procedures used to develop this document and those intended for its further maintenance are

described in the ISO/IEC Directives, Part 1. In particular, the different approval criteria needed for the

different types of ISO documents should be noted. This document was drafted in accordance with the

editorial rules of the ISO/IEC Directives, Part 2 (see www .iso .org/ directives).

Attention is drawn to the possibility that some of the elements of this document may be the subject of

patent rights. ISO shall not be held responsible for identifying any or all such patent rights. Details of

any patent rights identified during the development of the document will be in the Introduction and/or

on the ISO list of patent declarations received (see www .iso .org/ patents).

Any trade name used in this document is information given for the convenience of users and does not

constitute an endorsement.

For an explanation of the voluntary nature of standards, the meaning of ISO specific terms and

expressions related to conformity assessment, as well as information about ISO's adherence to the

World Trade Organization (WTO) principles in the Technical Barriers to Trade (TBT), see www .iso .org/

iso/ foreword .html.

This document was prepared by Technical Committee ISO/TC 20, Aircraft and space vehicles,

Subcommittee SC 14, Space systems and operations.

This second edition cancels and replaces the first edition (ISO 24917:2010), which has been technically

revised. The main changes compared to the previous edition are as follows:
— correction of terms and definitions according to other existing standards;
— modification of the “Flight vehicle development test structure” (Figure 1);
— modification of the “Requirements applicability matrix” (Annex B).

Any feedback or questions on this document should be directed to the user’s national standards body. A

complete listing of these bodies can be found at www .iso .org/ members .html.
© ISO 2020 – All rights reserved v
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ISO/FDIS 24917:2020(E)
Introduction

This document provides space launch vehicle customers, contractors and manufacturers with general

requirements for test types and programmes for space launch vehicles and rocket units (modules) for

use in the documentation associated with their test activity.

This document is intended to help reduce the development time and cost of space launch vehicles and

rocket units, and to enhance their quality and reliability through the use of common, optimized and

approved requirements in the space launch vehicle test scope and organization.
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FINAL DRAFT INTERNATIONAL STANDARD ISO/FDIS 24917:2020(E)
Space systems — General test requirements for launch
vehicles
1 Scope

This document establishes general test requirements for launch vehicles equipped with liquid-

propellant engines, launched from stationary ground-, sea- and air-based launchers, in all phases of

their development.
2 Normative references

The following documents are referred to in the text in such a way that some or all of their content

constitutes requirements of this document. For dated references, only the edition cited applies. For

undated references, the latest edition of the referenced document (including any amendments) applies.

ISO 14302, Space systems — Electromagnetic compatibility requirements
ISO 14303, Space systems — Launch-vehicle-to-spacecraft interfaces
3 Terms and definitions
For the purposes of this document, the following terms and definitions apply.

ISO and IEC maintain terminological databases for use in standardization at the following addresses:

— ISO Online browsing platform: available at https:// www .iso .org/ obp
— IEC Electropedia: available at http:// www .electropedia .org/
3.1
space-rocket complex

set of flight vehicles (3.2) with functionally relative technical facilities intended for transportation,

storage, maintenance service, preparation, launching and flight control of flight vehicles with payload

3.2
flight vehicle
launch vehicle (3.3) including space nose section (3.6)
3.3
launch vehicle
vehicle designed to transport payloads to space

[SOURCE: ISO 10795:2019, 3.139, modified — The preferred term "launcher" has been removed.]

3.4
unit

lowest level of hardware assembly for which acceptance (3.26) and qualification tests (3.25) are required

[SOURCE: ISO 15864:2004, 3.1.13]
3.5
orbital stage

stage of flight vehicle (3.2) capable of injecting payloads into their planned orbit from the sub-orbital

trajectory that resulted from operation of lower stages
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ISO/FDIS 24917:2020(E)
3.6
nose section
set of a fairing (3.7) and fairing adapter
3.7
fairing

technical device intended to protect a spacecraft or a space nose section (3.6) from external influences

during transportation on a launcher, and to keep it on trajectory when launching into orbit

3.8
integration site

equipment and facility designed for launch vehicle (3.3) storage, assembly, testing, preparation,

maintenance, servicing and preparation for transportation to the launch pad (3.9)

[SOURCE: ISO/TR 17400:2003, 3.1]
3.9
launch pad

equipment and facility designed to provide for the pre-launch and launch operations of spacecraft

[SOURCE: ISO/TR 17400:2003, 3.3]
3.10
statement of work

contractual document prepared during project initiation and planning that describes what the project

needs to deliver and outlines all work required to complete the project
[SOURCE: ISO 10795:2019, 3.229]
3.11
technical specification

specification expressing technical requirements for designing and developing the solution to be

implemented

Note 1 to entry: The technical specification evolves from the functional specification and defines the technical

requirements for the selected solution as part of a business agreement.
[SOURCE: ISO 10795:2019, 3.238]
3.12
test metrological support

establishment and application of scientific and organizational foundations, technical facilities, rules and

standards necessary to achieve the measurement traceability, precision, completeness, operativeness

and the reliability of parameters control and technical performance characteristics of items

3.13
development test programme plan

obligate organizational and methodological document which specifies the test object (3.23) and

objectives, types, sequence and scope of experiments, order, conditions, place, time, support of test, test

reporting and responsibilities for test support and performance
3.14
reliability assurance programme plan

document specifying a set of requirements and measures aimed at providing and controlling the

satisfaction of requirements established in the statement of work (3.10) for a space launch vehicle (3.3)

and its components’ reliability during their development
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3.15
development test

test to provide information that can be used to check the validity of analytic techniques and assumed

design parameters, uncover unexpected system response characteristics, evaluate design changes,

determine interface compatibility, prove qualification and acceptance procedures and techniques,

check manufacturing technology, or establish accept/reject criteria
[SOURCE: ISO 10786:2011, 3.17]
3.16
safety assurance programme plan

document which establishes a set of requirements and measures aimed at assuring that all safety

risks associated with the space launch vehicle (3.3) design, development, manufacture and use are

accordingly identified, assessed, minimized, controlled and accepted
3.17
communications systems programme plan

document establishing the structure of communication systems (including telemetry measurement,

command and tracking communication lines, etc.) hardware born set on launch vehicle (3.3), launch pad

(3.9) and positioned along the flight route necessary for performance the measurement requirements,

location and orientation of sensors and their characteristics, frequency bands, minimal frequency of

sensor scanning
3.18
flight test
test in real conditions of the functioning and performance of target tasks
3.19
prototype model

item produced in the research and development process applying the newly developed working

engineering and technological documentation for test verification of the conformity of its parameters

and characteristics with the requirements specified in statement of work (3.10) to research and

development and correctness of adopted technical solutions
3.20
model
test mock­up

structurally, or physically, or structurally and physically similar item presenting a simplified

reproduction of a test object (3.23) or its part intended for testing
3.21
structural model
model (3.20) representing the structural flight characteristics
3.22
electrical model
model (3.20) representing the electrical flight characteristics
3.23
test object
item under test
3.24
test type
classified test grouping identified according to a certain attribute
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3.25
qualification test

required formal contractual test used to demonstrate that the design, manufacturing, and assembly

have resulted in hardware designs conforming to specification requirements

[SOURCE: ISO 14623:2003, 2.52, modified — The term has been changed to singular form.]

3.26
acceptance test

required formal test conducted on flight hardware to ascertain that the materials, manufacturing

processes and workmanship meet specifications and that the hardware is acceptable for intended usage

[SOURCE: ISO 14623:2003, 2.2, modified — The term has been changed to singular form.]

3.27
operational test

test conducted at the launch vehicle (3.3) site in an operational environment, with the equipment in its

operational configuration
3.28
critical unit

unit (3.4) whose failure can affect the system operation sufficiently to cause the failure of the stated

vehicle objectives or a partial loss of the mission, or whose proper performance is essential from a

safety standpoint
3.29
pyrotechnic device

device or assembly containing, or actuated by, propellants or explosives, with the exception of large

rocket motors

EXAMPLE Initiators, ignitors, detonators, squibs, safe and arm devices, booster cartridges, pressure

cartridges, separation bolts and nuts, pin pullers, linear separation systems, shaped charges, explosive

guillotines, pyrovalves, detonation transfer assemblies (mild detonating fuse, confined detonating cord, confined

detonating fuse, shielded mild detonating cord, etc.), through-bulkhead initiators, mortars, thrusters, explosive

circuit interrupters, and other similar items.
[SOURCE: ISO 26871:2012, 3.1.31]
4 Abbreviated terms
CSP communications systems programme plan
CTS control and test station
DTP development test programme plan
EMC electromagnetic compatibility
FTP flight test programme plan
FV flight vehicle
IS integration site
LPRE liquid-propellant engine
LS launching site
LV launch vehicle
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OCN on­board cable network
OS orbital stage
PHS pneumatic/hydraulic system
RAP reliability assurance programme plan
SAP safety assurance programme plan
SC spacecraft
SNS space nose section
SOW statement of work
SRC space-rocket complex
5 Testing philosophy

5.1 Objectives, tasks and principles of development test for launch vehicle and its units

5.1.1 Development test

A development test is one of the methods of verification which guarantees that all characteristics of the

FV meet the requirements of the SOW. The FV is tested in the SRC during the launch preparation for

test flight.

The development test of an FV and units of an LV includes ground development test phases and a

flight test. The complete test programme for launch vehicles, upper stage, encompasses development,

qualification, acceptance, pre-launch validation and follow-on operational test and evaluations. The

test programme encompasses the testing of progressively more complex assemblies of hardware and

computer software. Generally, the FV development test structure may be represented as a scheme in

compliance with ISO 14300­1 (see Figure 1).
5.1.2 Objectives
5.1.2.1 Objectives of development test

The main objective of a ground development test is to verify the FV preparation technology for launch

and launch itself, preliminarily to verify and evaluate the implementation of the specified parameters

and characteristics, operation and interaction of the FV and its components when the operation

conditions are being simulated (or under effect of these conditions).
5.1.2.2 Objectives of flight test

The main objective of a flight test is to comprehensively check the FV serviceability and confirm the

SOW-specified requirements for the space rocket complex under real operation conditions.

5.1.2.3 Objectives for reliability and safety programmes

One of the main objectives of the LV (OS) ground development test is to achieve the SOW­assigned levels

of reliability and safety indexes before flight test commencement and confirm these during the flight

test. The reliability and safety index levels are normalized in the RAP and SAP, the latter including an

environmental safety guarantee.
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5.1.2.4 Objectives of test for launch vehicle and its units

The main objectives of the development test of an FV, LV and its units are as follows:

a) verification of unit structure strength, rigidity, confirmation of rocket module parameters,

verification of equipment mechanical loading regimes;
b) breadboarding;
c) test of technological cycle of preparing FV for launch and launch itself;

d) comprehensive verification of units functioning during launch and propulsion systems operation in

the assigned regimes;
e) verification of the ground technical means/launch vehicle compatibility;
f) test of FV interfaces [LV, upper stage vehicle, spacecraft (SC)];
g) confirmation of the correctness of adopted engineering solutions;

h) verification of the sufficiency of measuring aids and telemetry data processing techniques;

i) individual tests of all FV components;
j) verification of operation convenience;
k) personnel training.
5.1.3 Test planning

The tasks to be solved during LVs testing are identified according to the design, assigned characteristics,

LV test maturity, design (modernization) novelty, dedicated operation conditions change and are

presented in the test programmes.
5.1.4 Organization and test sequence

The organization and order for conducting the development test are determined by the comprehensive

development test programme plan.
5.1.5 Development test programme plan
5.1.5.1 Planning

In order to meet the assigned LV (OS) characteristics requirements, the supplier plans a development test.

5.1.5.2 Initiation of the programme

The comprehensive development test programme plan is developed in accordance with the LV (OS)

hierarchical structure. The main starting documents for developing the FV development test programme

are the statement of work, the preliminary project and the reliability assurance programme.

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Figure 1 — Flight vehicle development test structure
5.1.5.3 Contents of development test programme plan

The FV comprehensive development test programme is a common system of independent, particular

programme-technical documents, identifying the individual test objectives and scope, establishing the

criteria of OS or LV completeness and readiness for transferring to higher test levels.

The test sequence, scope and object, controlled characteristics, types of test and test phasing in the

course of LV (rocket unit) development are assigned by the LV (rocket unit) manufacturers-contractors

in the comprehensive development test programme, other test programmes.
5.1.5.4 Principles of development test programme plan

The LV (OS) development test programme plan (DTP) is based on the following principles:

a) system approach to the test planning with a detailed coordination of all types and phases of test;

absolute assurance and confirmation of the assigned characteristics of the SRC items during

ground test; use of results of optimizing the complex systems functioning as a component of other

complexes;

b) fulfilment of the main test work scope applying test facilities (stands, rigs, models, etc.) before

starting ready-made (standard) LV (OS) test under real operation conditions (full-scale test);

c) confirmation of all-round interaction of all FV components and demonstration of their functioning

reliability under full-scale conditions, as well as conduct of that part of test applying test means

which cannot be technically performed or are economically inexpedient within the assigned time

during the flight test, and on the basis of the following provisions:

1) determination of nomenclature and characteristics of modified and newly developed test stands

(rigs) on condition that they would assure fulfilment of the planned test
...

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