ISO 19683:2026

Space systems — Design qualification and acceptance tests of small spacecraft and units

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].

Systèmes spatiaux — Qualification de la conception et essais de réception des petits véhicules spatiaux

General Information

• 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

Relations

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

Overview

ISO 19683:2017

ISO 19683 provides international standards for the design qualification and acceptance testing of small spacecraft and their units. Developed by the International Organization for Standardization (ISO), this standard addresses the unique requirements and challenges associated with small, commercial satellites-including mini-, micro-, nano-, pico-, and femto-satellites, as well as CubeSats. The aim is to ensure a minimum level of product reliability and quality, particularly in the face of risk-tolerant, fast-paced satellite development cycles. By offering standardized test methods and requirements, ISO 19683 helps organizations achieve mission success, maintain low costs, and deliver small spacecraft swiftly for commercial and research purposes.

Key Topics

• Scope of Application:
  • Applies to commercial small spacecraft developed using non-traditional approaches that prioritize low cost and rapid delivery.
  • Encompasses design qualification and acceptance tests at both system and unit levels.
  • Covers all types of small spacecraft, including CubeSats, mini-, micro-, nano-, pico-, and femto-satellites.
• Testing Approach:
  • Focuses on reliability against early failures (“infant mortality”) post-launch.
  • Includes qualification, acceptance, and proto-flight tests tailored for small spacecraft.
  • Emphasizes flexibility through tailored test requirements agreed upon by customers, manufacturers, and launch providers.
• Key Test Methods:
  • Electrical interface and functional testing.
  • Mechanical testing: vibration (sinusoidal, random), acoustic, shock, and modal surveys.
  • Environmental testing: thermal cycle, thermal vacuum, thermal balance, pressure, leakage, outgassing, and microvibration.
  • Electromagnetic compatibility (EMC) and spacecraft charging induced electrostatic discharge (ESD) testing.
  • Mission simulation and end-to-end validation.
• Documentation and Reporting:
  • Simplified documentation requirements suited for small teams without compromising traceability.
  • Comprehensive test plans and reports to ensure transparency and reproducibility.

Applications

• Satellite Manufacturing and Integration:
  • Standardizes testing procedures for manufacturers of small spacecraft, enabling streamlined production with consistent quality.
  • Facilitates the use of commercial-off-the-shelf (COTS) components by specifying minimum environmental and functional test requirements.
• Academic and Research Missions:
  • Valuable for universities and research organizations developing CubeSats and small satellites for technology demonstration or scientific research.
• Commercial Satellite Operations:
  • Assures end-users and stakeholders of the reliability of small spacecraft for Earth observation, telecommunications, and IoT constellations.
• Satellite Constellations and Swarm Deployments:
  • Offers tailored guidelines for batch production, delta-qualification, and acceptance testing across multiple spacecraft with shared designs.
• Regulatory Compliance:
  • Supports manufacturers in meeting international trade, safety, and mission assurance expectations for small spacecraft markets.

Related Standards

To ensure comprehensive testing and compatibility, ISO 19683 references several related standards, including:

• ISO 11221 – Test methods for spacecraft charging induced electrostatic discharge.
• ISO 14302 – Electromagnetic compatibility requirements for space systems.
• ISO 15864 – General test methods for spacecraft, subsystems, and units.
• ISO 17566 – Requirements for spacecraft test documentation.
• ISO 24411 – Micro-vibration testing for space systems.
• ISO 14620-1 – General requirements for space systems safety.
• ISO 24113 – Space debris mitigation requirements.
• ISO TS 20991 – Common requirements for small spacecraft.

Practical Value

Implementing ISO 19683 ensures that small spacecraft meet industry-recognized minimum testing standards without imposing the prohibitive cost and time burdens associated with traditional satellite testing. This supports innovation in the commercial space sector, enhances global trade of spacecraft products, and encourages participation from new players in the space industry by offering clear, scalable, and practical test guidelines for reliability and mission success.

Keywords: small spacecraft, CubeSat, satellite qualification, acceptance testing, space systems standards, commercial satellites, satellite constellations, ISO 19683, environmental testing, satellite reliability.

Standards Content (Sample)

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
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
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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 document 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).
ISO draws attention to the possibility that the implementation of this document may involve the use of (a)
patent(s). ISO takes no position concerning the evidence, validity or applicability of any claimed patent
rights in respect thereof. As of the date of publication of this document, ISO had not received notice of (a)
patent(s) which may be required to implement this document. However, implementers are cautioned that
this may not represent the latest information, which may be obtained from the patent database available at
www.iso.org/patents. ISO shall not be held responsible for identifying any or all such patent rights.
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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 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
...