ISO/TC 20/SC 14/WG 2 - System requirements, verification and validation, interfaces, integration, and test

This document provides spacecraft (SC) organizations with the general format for presenting the interface requirement document (IRD) for launch vehicle services. The IRD provides a list of the major technical requirements spacecraft agencies provide to launch vehicle (LV) agencies when submitting an application for launch services. The IRD addresses the definition of the SC mission, the mechanical and electrical interfaces, the overall environment requirements (mechanical, thermal, cleanliness, radio-electrical), the SC development and test programme and, finally, launch range facilities and support requirements. This document is applicable to all existing commercial LV and related launch facilities so as to permit SC contractors to prepare a single interface requirement document for a given SC mission, independently of the LV contractor to be selected. The IRD, as defined in this document, includes the basic SC input data needed by LV agencies to prepare the interface control document defined in ISO 15863.

This document provides methods and specifies general requirements for spacecraft level thermal balance tests (TBT) and thermal vacuum tests (TVT). It also provides basic requirements for test facilities, test procedures, test malfunction interruption emergency handling and test documentation. The methods and requirements can be used as a reference for subsystem-level and unit-level test article.

This document specifies requirements for the implementation of spacecraft level micro-vibration tests on space systems to be considered by test providers, including test designers and test engineers. It also gives guidance for spacecraft designers and interested parties. The spacecraft level micro-vibration test is applicable to space systems which contain payload equipment sensitive to the micro-vibration environment which only induced by the internal disturbance sources on-orbit, e.g. for the purpose of earth observation, space telescopes, optical experiments, telecommunication.

This document establishes a set of requirements for planning and executing verification programmes for commercial/non-commercial manned and unmanned space systems. This document defines a distributed verification programme for each contractor that engages in the development of any element of a space system, starting from the lowest level (i.e. unit/piece part level) and the earliest phase (i.e. requirement phase) to the acceptance and the delivery review of a system’s development as well as the launch site activities. This document primarily addresses verification associated with space, launch, and ground segment acquisitions. Space support segments including range safety, ground support equipment, and launch operation facilities, which are not otherwise addressed in this document, can also benefit from the described verification programme and management processes.

This document specifies the verification test activities for assessing the RF performance of integrated spacecraft, including test items, test requirements, and typical test procedures, test facility and chamber environment, with respect to the testing using compact range. This document is applicable to the RF performance test for spacecraft at system level using compact range.

This document provides guidance and requirements for test providers and interested parties to implement vibration testing. This document specifies methods, including the force limiting approach, to mitigate unnecessary over-testing of spacecraft, subsystems and units for space application. The technical requirements in this document can be tailored to meet the actual test objectives.

This document provides the baseline standard on the subject of testing at the system, subsystem and unit levels for applicable unmanned spacecraft programmes. It also provides the requirements for documentation associated with testing activities. This document contains provisions for qualification and acceptance testing, or proto-flight testing (PFT). It assumes that hardware development is complete.

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.

This document provides requirements for launch system designers or interface designers regarding interfaces between LV and EGSE, which is used to support on-line processing. It defines electrical interface types, design requirements, environment requirements, verification methods (analyses and tests), and interface check operation requirements. This document is intended to minimize design costs and reduce risks from errors resulting from miscommunication. It does not limit LV or EGSE organizational requirements to specify a unique interface.

ISO 21494:2019 specifies magnetic test methods including magnetic field test methods, magnetic moment test methods, magnetization and demagnetization test methods and magnetic compensation test methods. This document is applicable to magnetic tests on several levels: spacecraft-level, subsystem-level and unit-level. ISO 21494:2019 gives guidelines for conducting magnetic tests both in zero-magnetic field environment provided by magnetic test facilities and in the presence of the geomagnetic field environment.

ISO 17540:2016 provides terms and definitions in scope of design, testing, reliability analysis and quality control of liquid rocket engines. The terms are required for use in all types of documentation and literature including in the scope of standardization or using the results of this activity.

This International Standard provides space system manufacturing organizations with the minimum interface related items and generic format for creating the interface control document (ICD) which subsystems or units suppliers prepare for spacecraft systems (SC) integrators. In this International Standard, ICD is not defined to contain descriptions regarding various properties of subsystems or units or tasks to be done by suppliers, i.e. performance, functions, endurance to launch mechanical environment, or quality assurance provisions. Such descriptions are presumed to be defined in other contractual documents such as technical specifications.

A general definition of initialization is that it begins at separation of the spacecraft (SC) from the launcher. In some cases, a more exact definition will be that initialization begins in flight, upon planned change in mode or state of the SC from the launch configuration. Commissioning is completed when the SC, including its payload, is certified for initial mission operations. Prior to certification for mission operations, the SC is described as a test article in the three parts of ISO 10784. ISO 10784 does not include a requirement for contingency plans, but does include a statement of the need for contingency planning. ISO 10784-1:2011 outlines general descriptive information for SC initialization and commissioning as might be appropriate for programme management, project engineering or programme test documentation. Since the SC is considered a test article at this phase of its operational life, ISO 17566 is used as a normative reference in constructing the initialization plan and the commissioning report. It provides SC manufacturers, SC operators and other stakeholders with a common language and form to verify and document spacecraft initialization and commissioning prior to normal SC mission operations.

A general definition of initialization is that it begins at separation of the spacecraft (SC) from the launcher. In some cases, a more exact definition will be that initialization begins in flight, upon planned change in mode or state of the SC from the launch configuration. Commissioning is completed when the SC, including its payload, is certified for initial mission operations. Prior to certification for mission operations, the SC is described as a test article in the three parts of ISO 10784. ISO 10784 does not include a requirement for contingency plans, but does include a statement of the need for contingency planning. ISO 10784-2:2011 provides SC manufacturers and operators with a specific form and format to write spacecraft initialization plans required to configure and verify the SC to perform normal mission operations. Since the SC is considered a test article at this phase of its operational life, ISO 17566 is used as a normative reference in constructing the initialization plan. It provides SC manufacturers, operators and other stakeholders with a common language and form to verify and document spacecraft initialization prior to normal SC mission operations.

A general definition of initialization is that it begins at separation of the spacecraft (SC) from the launcher. In some cases, a more exact definition will be that initialization begins in flight, upon planned change in mode or state of the SC from the launch configuration. Commissioning is completed when the SC, including its payload, is certified for initial mission operations. Prior to certification for mission operations, the SC is described as a test article in the three parts of ISO 10784. ISO 10784 does not include a requirement for contingency plans, but does include a statement of the need for contingency planning. ISO 10784-3:2011 outlines general descriptive information for SC initialization and commissioning as might be appropriate for programme management, project engineering or programme test documentation. Since the SC is considered a test article at this phase of its operational life, ISO 17566 is used as a normative reference in constructing the commissioning report. It provides SC manufacturers, SC operators and other stakeholders with a common language and form to verify and document spacecraft initialization and commissioning prior to normal SC mission operations.

ISO 17566:2011 provides a specific format for the development of test documentation for an individual test of a spacecraft, subsystem or unit. It is focused on the definition of the format for test plans, test specifications, test procedures and test reports. The scope of ISO 17566:2011 does not include overall programme test planning. A specific test plan can also be part of the overall spacecraft project test plan.

ISO 15862:2009 provides basic requirements for the measurement of the spacecraft flight environments generated by the launch vehicle, telemetry data processing and formats of analysis reports. ISO 15862:2009 defines the field and number of measurement parameters, the principles of data processing, the format of delivered data and the content and the form of the flight environment analysis report. Flight telemetry data are used to verify if flight environment conditions exceed pre-flight analyses and environmental test results. In the event of a launch failure, adequate flight environment data can assist in investigating and analysing failure causes. ISO 15862:2009 is applicable to commercial launch vehicles and related ground processing, no matter which launch vehicle agencies are selected.

ISO 19933:2007 provides a specific format to report the test process and results of spacecraft (SC) qualification to the launch environment. The following types of tests are considered: static load; modal survey; sine vibration; acoustic noise; random vibration; shock; and electromagnetic compatibility (EMC). The definition of test specifications and test requirements are derived from launch vehicle (LV) user's manuals as defined in ISO 14303. Only those tests that are intended to demonstrate the compliance of a given SC design with its LV environment are taken into consideration.

The purpose of ISO 15863:2003 is to provide spacecraft (SC) and launch vehicle (LV) organizations with the general format for presenting the interface control document (ICD) that verifies and controls the compatibility between SC and LV for a dedicated mission. ISO 15863:2003 addresses the definition of the mission, the compatibility of the SC with the LV environment, including all mechanical, electrical, radio frequency, and electromagnetic aspects related to SC to LV and SC to launch range interfaces, verification analyses and tests for the induced environment, and the necessary facilities and support for launch range operations.

This International Standard defines the principles used to determine loads and the induced environment during the service life of a space flight vehicle and its components, taking account of the notions of probability, combined loads, corresponding safety factors and lifecycle.

ISO 24917:2010 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.

ISO 15864:2004 provides the baseline standard on the subject of testing at the system, subsystem, and unit level for applicable unmanned spacecraft programs. It also provides the requirements for documentation associated with testing activities. The acceptance criteria, specifications or procedures, and other detail test requirements applicable to a particular program are defined in the applicable technical specifications and statement of work. When requirements have to be verified by measuring product performance and function under various simulated environments, the method is referred to as "Test." The requirements of ISO 15864:2004 may be tailored for each specific space program application.

ISO 17401:2004 provides spacecraft (SC) organizations with the general format for presenting the interface requirement document (IRD) for launch vehicle services. The IRD provides a list of the major technical requirements spacecraft agencies provide to launch vehicle (LV) agencies when submitting an application for launch services. ISO 17401:2004 is applicable to all existing commercial LV and related launch facilities so as to permit SC contractors to prepare a single interface requirement document for a given SC mission, independently of the LV contractor to be selected.