ISO 19683:2026

• Abstract:

  This document provides test methods and test requirements for design either qualification or acceptance, or both of small spacecraft or units. It provides the minimum test requirements and test methods to qualify the design and manufacturing methods of commercial small spacecraft and their units and to accept the final products. This document is applicable to satellites whose development methods are different from the ones used for traditional satellites that have little room for risk tolerance. The scope of this document encompasses different categories of small spacecraft, so-called mini-, micro-, nano-, pico- and femto spacecraft. This document includes CubeSat, as long as it is developed with the untraditional processes. This document does not cover satellite deployment mechanisms, such as picosatellite orbital deployer (POD), as the verification requirements are defined in the interface control document (ICD) with the launcher, such as ISO 26869[1]. This document does not cover software testing, although some tests such as functional test, mission test and end-to-end test are inherently used to test the software installed in the hardware being tested. General requirements and processes of satellite software testing can be found in various references, such as ECSS-E-ST40[2]. This document does not cover requirements regarding safety nor debris mitigation. Appropriate documents such as ISO 14620-1[3] or ISO 24113[4] can be referred to. Other common requirements for small spacecraft can be found in ISO 20991[5].

• Status: Published
• Publication Date: 21-May-2026
• ICS: 49.140 - Space systems and operations
• Technical Committee: ISO/TC 20/SC 14 - Space systems and operations
• Drafting Committee: ISO/TC 20/SC 14 - Space systems and operations
• Current Stage: 6060 - International Standard published
• Start Date: 22-May-2026
• Due Date: 15-Feb-2026
• Completion Date: 22-May-2026

• Revises: ISO 19683:2017 - Space systems — Design qualification and acceptance tests of small spacecraft and units
• Effective Date: 18-Feb-2023

ISO 19683:2026 is an International Standard published by ISO for the design qualification and acceptance testing of small spacecraft and their units. It sets minimum test methods and test requirements for commercial small spacecraft built with non-traditional development approaches and extensive use of commercial-off-the-shelf (COTS) parts. The document is for satellite developers, unit suppliers, integrators, and launch-related teams that need a clear test basis for qualification, acceptance, or proto-flight testing.

What does ISO 19683:2026 specify?

ISO 19683:2026 specifies how to test small spacecraft and units for design qualification, acceptance, or both. It covers the minimum test requirements needed to qualify the design and manufacturing methods and to accept final products.

The scope includes mini-, micro-, nano-, pico- and femto spacecraft, and it includes CubeSat when it is developed with the untraditional processes described in the document. It does not cover satellite deployment mechanisms such as picosatellite orbital deployer (POD) verification, software testing, or safety and debris mitigation requirements.

Annex	What it covers
Annex A	Tailoring and waiver guides
Annex B	Basis of test levels and duration
Annex C	Design, verification and testing philosophy for small spacecraft
Annex D	Test selection logic flow
Annex E	Environment stress screening and burn-in
Annex F	Thermal vacuum or thermal cycle?

What are the key requirements of ISO 19683:2026?

ISO 19683:2026 is built around tailored test selection, defined test purposes, and documented evidence. The main practical message is that small spacecraft testing is not one fixed recipe - the test set depends on the mission, the launcher interface, the orbit, and whether the design is new or already flight-proven.

Tailoring, QT, AT and PFT

Clause 5.1 allows tailoring by agreement between the customer, the manufacturer and the launch provider, and Annex A gives the waiver and tailoring guides. In practice, this means the program can adjust test scope instead of applying every test automatically.

Clause 5.2 explains qualification test (QT), Clause 5.3 acceptance test (AT), and Clause 5.4 proto-flight test (PFT). QT is used to show the design meets requirements with margin, AT is for accepting the final product, and PFT uses the flight model in a combined qualification-and-acceptance approach. Clause 5.2 also makes clear that unit QT in this document is intended to provide minimum durability assurance for a unit sold as a satellite unit, while the developer decides how to obtain any extra margin needed for the mission.

Clause 5.7 says test conditions, tolerances and accuracies follow ISO 15864:2021, and Clause 5.8 requires complete functional tests at the beginning and end of the sequence, with partial functional tests before and after each environmental exposure. That matters because the satellite must still work after each test step, not only at the end of the campaign.

Test documentation and test philosophy

Clause 5.6 requires a test plan, specification and procedure, a test report, and a datasheet for unit test results. For a buyer or integrator, this is the evidence trail that shows what was tested, how it was tested, and what the outcomes were.

Clause 5.9 points to Annex C for the design, verification and testing philosophy for small spacecraft. Clause 5.10 then explains how constellation programs change the test approach when the design becomes flight-proven, including pathfinder missions, batch production, delta-qualification for changes, and possible reduction of some acceptance test items in later batches.

Test selection by level and environment

Clauses 6 and 7 split the work into satellite system tests and unit tests, and Tables 1 to 5 show which tests apply to QT, AT and PFT. Clause 6.2 says system test level and duration depend on the satellite environment and mission objectives, while mechanical and thermal AT must cover the maximum predicted range and acceleration. For QT or PFT, margin is added.

Clause 7.2 and Table 5 define the default unit QT levels and durations for radiation, EMC, vibration, shock, thermal vacuum, thermal cycle functional test, thermal cycle endurance, cold/hot start and related checks. In practice, this gives unit suppliers and satellite developers a common baseline for screening units before integration, while AT and PFT levels are agreed between the developer and the unit manufacturer.

Detailed test methods

Clause 9 gives the detailed requirements for each test, including purpose, facilities and setup, test article configuration, monitoring, levels and duration, and test conditions and guidelines. It covers electrical interface, functional, mission, TID, SEE, spacecraft charging induced ESD, EMC, deployment, magnetic field, antenna pattern, alignment, physical property, launcher/spacecraft interface, quasi-static load, modal survey, sinusoidal vibration, random vibration, acoustic, shock, thermal balance, thermal vacuum, functional test in vacuum, cold/hot start, thermal cycle functional, thermal cycle endurance, pressure, leakage, microvibration, burn-in and wear-in, end-to-end mission simulation, and bake out and outgas.

Several of those detailed clauses defer to ISO 15864:2021 for the base method, while ISO 19683:2026 adds the small-spacecraft selection logic and tailoring rules. That helps teams reuse an established spacecraft test framework without losing the small-spacecraft-specific guidance.

Constellation programs and pathfinder logic

Clause 8 applies the same idea to satellite constellation programs after pathfinder missions. The first flight-proven spacecraft carry the heavier test burden, and later batches may use reduced testing when the design is already verified in orbit. If the design changes, Clause 5.10 allows delta-qualification for the modified parts or for a new launch environment.

What terms does ISO 19683:2026 define?

• COTS - Commercial-off-the-shelf parts, units, components and technologies that are readily available and not made or qualified to military or space standards.
• CubeSat - A picosatellite with the standard CubeSat form factor, defined in the document and linked to ISO 17770 for exact external dimensions.
• flight model - The spacecraft, subsystem or unit model intended to be launched and operated in orbit and then subjected to acceptance testing.
• pathfinder - A satellite launched before full constellation deployment to validate the mission and verify the design in orbit.
• satellite constellation - A group of satellites with mostly the same design that work together in coordination to achieve specific missions.
• test article - The spacecraft, subsystem or unit on which a test is performed.
• unit - The lowest level of hardware assembly that performs specified electrical, thermal or mechanical functions.

Who uses ISO 19683:2026?

ISO 19683:2026 is used by small spacecraft manufacturers, unit suppliers, satellite integrators, qualification and acceptance test teams, quality managers, and launch providers. It is especially relevant in commercial small-satellite programs that use COTS-based hardware and need a practical basis for deciding which tests to run on each unit, which to run on a sample, and which to run only on the first spacecraft.

It also helps constellation program managers, procurement teams and test laboratories. They use it to prepare test plans, agree tailoring, review acceptance evidence, and decide how much testing can be relaxed after pathfinder flights or after a design becomes flight-proven.

What changed in ISO 19683:2026 from the previous edition?

ISO 19683:2026 is the second edition and it cancels and replaces ISO 19683:2017. The foreword states that it has been technically revised.

The main changes stated in the document are:

• updated terms and definitions
• added 5.10 on testing of satellite constellation program
• added Clause 8 on satellite constellation tests
• updated Clause 9 on test requirements
• updated Annex C

Which standards are used with ISO 19683:2026?

Standard	What it contributes
ISO 11221:2011	Test methods for spacecraft charging induced electrostatic discharge
ISO 14302	Electromagnetic compatibility requirements
ISO 15864:2021	General test methods for spacecraft, subsystems and units, including requirements reused throughout ISO 19683:2026
ISO 26869	Launcher interface requirements used when deployment mechanisms are covered by the launcher ICD
ECSS-E-ST40	General requirements and processes for satellite software testing
ISO 14620-1	Safety-related space system requirements mentioned for excluded safety topics
ISO 24113	Debris mitigation requirements mentioned for excluded debris topics
ISO 20991	Other common requirements for small spacecraft

What does the ISO 19683:2026 document contain?

ISO 19683:2026 contains clause-by-clause test guidance plus selection logic and tailoring guidance. Tables 1 to 7 show which tests apply at system and unit level for QT, AT and PFT, including the constellation-program case.

Clause 9 breaks each test into purpose, setup, configuration, monitoring, levels and duration, and conditions and guidelines. Annex B explains the basis for the default test levels and durations, including the rationale behind radiation, thermal and mechanical choices, while Annex C compares small-spacecraft practice with traditional satellite practice. Annex D provides the logic flow for choosing tests, and Annex F helps the reader decide between thermal vacuum and thermal cycle approaches.

International
Standard
ISO 19683
Second edition
Space systems — Design
2026-05
qualification and acceptance tests of
small spacecraft and units
Systèmes spatiaux — Qualification de la conception et essais de
réception des petits véhicules spatiaux
Reference number
© ISO 2026
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
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Phone: [phone]
Email: [e-mail]
Website: www.iso.org
Published in Switzerland
ii
Contents Page
Foreword .vii
Introduction .viii
1 Scope . 1
2 Normative references . 1
3 Terms and definitions . 1
4 Abbreviated terms . 3
5 General requirements . 4
5.1 Tailoring .4
5.2 Qualification test .4
5.3 Acceptance test .5
5.4 Proto-flight test .5
5.5 Retest .5
5.6 Test documentation .5
5.6.1 General .5
5.6.2 Test plan, specification and procedure .5
5.6.3 Test report .6
5.6.4 Datasheet for unit test results .6
5.7 Test conditions, tolerances and accuracies .7
5.8 Functional test .7
5.9 Design, verification and testing philosophy .7
5.10 Testing of satellite constellation program .7
6 Satellite system tests . 8
6.1 Test items .8
6.2 Test level and duration .10
7 Unit tests .10
7.1 Test items .10
7.2 Test levels and duration . 20
8 Satellite constellation tests .23
8.1 System test items . 23
8.2 Unit test items . 25
9 Test requirements .29
9.1 Electrical interface . 29
9.1.1 Purpose of test . 29
9.1.2 Test facilities and setup as basic requirements . 29
9.1.3 Test article configuration . 29
9.1.4 Monitoring during test . 29
9.1.5 Test levels and duration . 29
9.1.6 Test conditions and guidelines. 29
9.2 Functional test . 29
9.2.1 Purpose of test . 29
9.2.2 Test facilities and setup as basic requirements . 29
9.2.3 Test article configuration . 29
9.2.4 Monitoring during test . 30
9.2.5 Test levels and duration . 30
9.2.6 Test conditions and guidelines. 30
9.3 Mission test . 30
9.3.1 Purpose of test . 30
9.3.2 Test facilities and setup as basic requirements . 30
9.3.3 Test article configuration . 30
9.3.4 Monitoring during test . 30
9.3.5 Test levels and duration . 30

iii
9.3.6 Test conditions and guidelines. 30
9.4 Total Ionization Dose (TID) test .31
9.4.1 Purpose of test .31
9.4.2 Test facilities and setup as basic requirements .31
9.4.3 Test article configuration .31
9.4.4 Monitoring during test .31
9.4.5 Test levels and duration .31
9.4.6 Test conditions and guidelines.31
9.5 Single Event Effect (SEE) test .32
9.5.1 Purpose of test .32
9.5.2 Test facilities and setup as basic requirements .32
9.5.3 Test article configuration .32
9.5.4 Monitoring during test .32
9.5.5 Test levels and duration .32
9.5.6 Test conditions and guidelines.32
9.6 Spacecraft Charging Induced Electrostatic Discharge (ESD) test . 33
9.6.1 Purpose of test . 33
9.6.2 Test facilities and setup as basic requirements . 33
9.6.3 Test article configuration . 33
9.6.4 Monitoring during test . 33
9.6.5 Test levels and duration . 33
9.6.6 Test conditions and guidelines. 33
9.7 Electromagnetic Compatibility (EMC) test . 33
9.7.1 Purpose of test . 33
9.7.2 Test facilities and setup as basic requirements . 33
9.7.3 Test article configuration . 34
9.7.4 Monitoring during test . 34
9.7.5 Test levels and duration . 34
9.7.6 Test conditions and guidelines. 34
9.8 Deployment test. 34
9.8.1 Purpose of test . 34
9.8.2 Test facilities and setup as basic requirements . 34
9.8.3 Test article configuration . 34
9.8.4 Monitoring during test . 34
9.8.5 Test levels and duration . 35
9.8.6 Test conditions and guidelines. 35
9.9 Magnetic field test . 35
9.10 Antenna pattern test . 35
9.11 Alignment measurement . 35
9.12 Physical property measurement . 35
9.13 Launcher/Spacecraft interface test . 35
9.14 Quasi-static load test . . 35
9.14.1 Purpose of test . 35
9.14.2 Test facilities and setup as basic requirements . 35
9.14.3 Test article configuration . 35
9.14.4 Monitoring during test . 36
9.14.5 Test levels and duration . 36
9.14.6 Test conditions and guidelines. 36
9.15 Modal survey . 36
9.15.1 Purpose of test . 36
9.15.2 Test facilities and setup as basic requirements . 36
9.15.3 Test article configuration . 36
9.15.4 Monitoring during test . 36
9.15.5 Test levels and duration . 36
9.15.6 Test conditions and guidelines. 36
9.16 Sinusoidal vibration test .37
9.16.1 Purpose of test .37
9.16.2 Test facilities and setup as basic requirements .37
9.16.3 Test article configuration .37

iv
9.16.4 Monitoring during test .37
9.16.5 Test levels and duration .37
9.16.6 Test conditions and guidelines.37
9.17 Random vibration test .37
9.17.1 Purpose of test .37
9.17.2 Test facilities and setup as basic requirements .37
9.17.3 Test article configuration .37
9.17.4 Monitoring during test .37
9.17.5 Test levels and duration . 38
9.17.6 Test conditions and guidelines. 38
9.18 Acoustic test . . 38
9.18.1 Purpose of test . 38
9.18.2 Test facilities and setup as basic requirements . 38
9.18.3 Test article configuration . 38
9.18.4 Monitoring during test . 38
9.18.5 Test levels and duration . 38
9.18.6 Test conditions and guidelines. 38
9.19 Shock test . 38
9.19.1 Purpose of test . 38
9.19.2 Test facilities and setup as basic requirements . 38
9.19.3 Test article configuration . 39
9.19.4 Monitoring during test . 39
9.19.5 Test levels and duration . 39
9.19.6 Test conditions and guidelines. 39
9.20 Thermal balance test . 39
9.20.1 Purpose of test . 39
9.20.2 Test facilities and setup as basic requirements . 39
9.20.3 Test article configuration . 39
9.20.4 Monitoring during test . 39
9.20.5 Test levels and duration . 39
9.20.6 Test conditions and guidelines. 40
9.21 Thermal vacuum test . 40
9.21.1 Purpose of test . 40
9.21.2 Test facilities and setup as basic requirements . 40
9.21.3 Test article configuration . 40
9.21.4 Monitoring during test . 40
9.21.5 Test levels and duration . 40
9.21.6 Test conditions and guidelines.41
9.22 Functional test in vacuum .41
9.22.1 Purpose of test .41
9.22.2 Test facilities and setup as basic requirements .41
9.22.3 Test article configuration .41
9.22.4 Monitoring during test .41
9.22.5 Test levels and duration .41
9.22.6 Test conditions and guidelines.42
9.23 Cold/Hot start test .42
9.23.1 Purpose of test .42
9.23.2 Test facilities and setup as basic requirements .42
9.23.3 Test article configuration .42
9.23.4 Monitoring during test .42
9.23.5 Test levels and duration .42
9.23.6 Test conditions and guidelines.42
9.24 Thermal cycle functional test.43
9.24.1 Purpose of test .43
9.24.2 Test facilities and setup as basic requirements .43
9.24.3 Test article configuration .43
9.24.4 Monitoring during test .43
9.24.5 Test levels and duration .43
9.24.6 Test conditions and guidelines.43

v
9.25 Thermal cycle endurance test . 44
9.25.1 Purpose of test . 44
9.25.2 Test facilities and setup as basic requirements . 44
9.25.3 Test article configuration . 44
9.25.4 Monitoring during test . 44
9.25.5 Test levels and duration . 44
9.25.6 Test conditions and guidelines. 44
9.26 Pressure test . . 44
9.27 Leakage test . 44
9.28 Microvibration test . 44
9.28.1 Purpose of test . 44
9.28.2 Test facilities and setup as basic requirements .45
9.28.3 Test article configuration .45
9.28.4 Monitoring during test .45
9.28.5 Test levels and duration .45
9.28.6 Test conditions and guidelines.45
9.29 Burn-in and wear-in test .45
9.30 End-to-end mission simulation .45
9.30.1 Purpose of test .45
9.30.2 Test facilities and setup as basic requirements .45
9.30.3 Test article configuration .45
9.30.4 Monitoring during test .45
9.30.5 Test levels and duration . 46
9.30.6 Test conditions and guidelines. 46
9.31 Bake out and outgas test . 46
9.31.1 Purpose of test . 46
9.31.2 Test facilities and setup as basic requirements . 46
9.31.3 Test article configuration . 46
9.31.4 Monitoring during test . 46
9.31.5 Test levels and duration . 46
9.31.6 Test conditions and guidelines. 46
9.32 Tailoring and waiver guides .47
Annex A (normative) Tailoring and waiver guides .48
Annex B (informative) Basis of test levels and duration .52
Annex C (informative) Design, verification and testing philosophy for small spacecrafts .55
Annex D (informative) Test selection logic flow . 74
Annex E (informative) Environment stress screening and burn-in .87
Annex F (informative) Thermal vacuum or thermal cycle? .88
Bibliography .91

vi
Foreword
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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 19683:2017), which has been technically
revised.
The main changes are as follows:
— updated terms and definitions;
— added 5.10 on testing of satellite constellation program;
— added Clause 8 on satellite constellation tests;
— updated Clause 9 on test requirements;
— updated Annex C.
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.

vii
Introduction
There is an increasing demand for small, micro, nano or pico satellite development and utilization worldwide;
yet, there is no clear and globally accepted definition of what is considered “small”, “micro”, “nano” or “pico”
satellites. These satellites are often built with emphasis on low cost and fast delivery. They are characterized
by extensive use of non-space-qualified commercial-off-the-shelf (COTS) units (component). For the sake of
convenience, the term “small spacecraft” is used throughout this document as a generic term to refer to
these satellites.
A small spacecraft is a satellite that utilizes non-traditional risk-taking development and management
approaches to achieve low cost and fast delivery with a small number of team. To achieve these two points,
low cost and fast delivery, satellite design relies on the use of non-space-qualified COTS units (components),
making sate
...