BS ISO 19683:2017

Foreword
Introduction
1 Scope
2 Normative references
3 Terms and definitions
4 Abbreviated terms
5 General requirements
6 Satellite system tests
7 Unit tests
8 Test requirements
Annex A (normative) - Tailoring and waiver guides
Annex B (informative) - Basis of test levels and duration
Annex C (informative) - Design, verification and testing
        philosophy for small spacecrafts
Annex D (informative) - Test selection logic flow
Annex E (informative) - Environment stress screening
        and burn-in
Annex F (informative) - Thermal vacuum or thermal cycle?
Bibliography

Gives test methods and test requirements for design qualification and/or acceptance of small spacecraft or units.

This document provides test methods and test requirements for design qualification and/or acceptance 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 places emphasis on achieving reliability against infant mortality after satellite launch to orbit while maintaining low cost and fast delivery. This document is applied to satellites whose development methods are different from the ones used for traditional satellites that have little room for risk tolerance, as shown in Figure1. The scope of this document encompasses different categories of small spacecraft, so-called mini-, micro, nano-, pico- and femto-, as well as CubeSat, spacecraft. Therefore, for the sake of convenience, the term “small spacecraft” is used throughout this document as a generic term. This document includes CubeSat, as long as it is developed with the untraditional processes. Figure1 Applicability of this document This document does not cover satellite deployment mechanisms, such as POD, as the verification requirements are defined in the Interface Control Document (ICD) with the launcher, such as ISO26869 . 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 . This document does not cover requirements regarding safety nor debris mitigation. Appropriate documents such as ISO14620‑1 or ISO24113 can be referred to. Other common requirements for small spacecraft can be found in Reference[14].