ISO/TC 20/SC 14/WG 1 - Design engineering and production

This document specifies class codes to classify global navigation satellite system (GNSS) receivers. The class codes represent how signals transmitted from radionavigation satellites are processed. This document applies to all types of GNSS receiver devices. The class codes in this document are not applicable to the following items: — condition of radionavigation satellites; — radio propagation environment including multipath, masking and obstacle; — additional antenna of a receiver device; — additional application software in a receiver device.

This document specifies test equipment and techniques used to identify interactions resulting from exposure of a material to an aerospace fluid. It is applicable for determining interactive reactions between propellants and materials used in the design, construction, and operation of propellant storage, transfer, and flight systems.

This document describes a process for managing, controlling and monitoring the mass properties of space systems. The relationship between this management plan and the performance parameters for mass properties to be met throughout the mission is described. Ground handling, dynamics analysis and test set-ups that rely on accurate mass properties inputs are identified. This document covers all programme phases from pre-proposal through to end of life.

This document specifies requirements for GNSS positioning augmentation centres that distribute correction data to provide higher accuracy and integrity information for positioning users in the civil and commercial market. The GNSS positioning augmentation centres cover the following types of positioning: a) real-time sub-meter to decimetre-level positioning; b) real-time centimetre-level positioning; c) post-processed geodetic positioning. This document also specifies roles of the following stakeholders and functions of the software present at GNSS positioning augmentation centres: — role of planner; — role of designer; — role of administrator; — function of software.

This document contains a process to establish performance requirements for the purpose of ensuring space systems electromagnetic compatibility (EMC). The engineering issues to be addressed in order to achieve system-level EMC are identified herein, with guidance and rationale towards achieving specification conformance. The method for the derivation of typical equipment-level requirements from a space-system-level requirement is illustrated. This document also aids in the selection of tailored requirements for a specific mission (see Annex A).

This document deals with control systems developed as part of a space project. It is applicable to all the elements of a space control system, including the space segment, the ground segment and the launch service segment. This document establishes general principles for all technical activities of space control engineering, including control engineering management, requirements definition, analysis, design, production, verification and validation, operation, maintenance, and disposal. It also provides requirements to progressively refine and manage control system realizations in space systems including multiple control systems. The requirements of this document can be tailored for each specific space program application.

This document establishes requirements for the design, material selection and characterization, fabrication, testing and inspection of all space mechanisms on spacecraft and payloads to meet the mission performance requirements. This document does not cover the requirements for mechanisms on expendable and reusable launch vehicles. Applicability of the requirements contained in this document to launch vehicle mechanisms is a decision left to the individual launch vehicle project. This document applies specifically to all moving mechanisms used in spacecraft during all phases of the mission, with the exception of engines and thermal protection systems.

This document provides requirements and recommendation for space-based systems that, using satellite radionavigation services, provide high accuracy positioning of rovers. It is particularly intended for rovers whose operation requires meeting specific safety requirements, including in situations of low visibility. This document also provides methods to verify the system requirements, as well as complementary information on particular applications (Annex A), mobile mapping systems (Annex B) and augmented positioning (Annexes C and D).

This document establishes the requirements for simulation of the space control system, including the objective, architecture and procedure, etc. This document is applicable to four phases of control system development, including conceptual design, detailed design, prototype and integrated system. The control system referred to in this document is the flight control system for guidance, navigation and control (GNC) of space systems which include launch vehicle, satellite and spaceship, etc. This document establishes a minimum set of requirements for simulation of the flight control system, and provides guidance to engineers on what to simulate in each phase of control system development. The requirements are generic in nature because of their broad applicability to all types of simulations. Implementation details of the requirements are addressed in project-specific standards, requirements, and handbooks, etc.

This document provides detailed information on the various methods of assessing the health status of lithium-ion space batteries in flight and makes recommendations to battery suppliers, spacecraft manufacturers and operators to ease this assessment.

This document defines the requirements and verification methods from design to on-orbit operation for Satellite Based Passive Microwave Sensors. This document covers the requirements for, design, analysis, manufacturing, ground tests and on-orbit self-sensor calibration and validation. In addition, this document includes the conditions considered for on-orbit inter-comparison among sensors as preparation for cross-calibration. This document includes some examples on how to apply the development of passive microwave sensors as shown in Annex A through D.

This document describes minimum requirements for small spacecraft. Small spacecraft may employ untraditional spacecraft development and management philosophy. These spacecraft projects are usually budget-limited or mass-limited, which makes a single (exclusive) launch unaffordable. 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. Regardless of the development philosophy, there are minimum requirements every spacecraft complies with. This document explicitly states those requirements and also refers to existing applicable standards. In that sense, this document serves as the top document to cover the minimum requirements for various stages of small spacecraft system life-cycle — with emphasis on design, launch, deployment, operation, and disposal phases. In this way, (1) safety, (2) harmlessness to co-passengers and launcher, and (3) debris mitigation, are all assured. This document is addressed to small spacecraft developers, as well as dispenser providers and/or the launch operators.

ISO 19683:2017 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. ISO 19683:2017 places emphasis on achieving reliability against infant mortality after satellite launch to orbit while maintaining low cost and fast delivery. ISO 19683:2017 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 Figure 1. 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. ISO 19683:2017 includes CubeSat, as long as it is developed with the untraditional processes.

ISO 17770:2017 addresses CubeSats, CubeSat Deployer and related verification of assurance/quality terms and metrics. ISO 17770:2017 defines a unique class of picosatellite, the CubeSat. CubeSats are ideal as space development projects for universities around the world. In addition to their significant role in educating space scientists and engineers, CubeSats provide a low-cost platform for testing and space qualification of the next generation of small payloads in space. A key component of the project is the development of a standard CubeSat Deployer. This Deployer is capable of releasing a number of CubeSats as secondary payloads on a wide range of launchers. The standard Deployer requires all CubeSats to conform to common physical requirements, and share a standard Deployer interface. CubeSat development time and cost can be significantly reduced by the development of standards that are shared by a large number of spacecraft. Normative control of the CubeSat design, qualification and acceptance testing is generally applied from other small satellite specific standards with the exception of CubeSat/Deployer launch environment test.

ISO 10785:2011 specifies general and detailed requirements for bellows used in space systems. It establishes requirements with regard to material, design, analysis, fabrication, material, testing, inspection and operation for space use. ISO 10785:2011 is applicable to metallic bellows which are used as pressure bearing components and are integrated into a pressure system. ISO 10785:2011 is not applicable to engine bellows or valve bellows.

ISO 10786:2011 establishes requirements for the design; material selection and characterization; fabrication; testing and inspection of all structural items in space systems, including expendable and reusable launch vehicles, satellites and their payloads. When implemented for a particular space system, it will assure high confidence in achieving safe and reliable operation in all phases of its planned mission. ISO 10786:2011 applies specifically to all structural items, including fracture-critical hardware used in space systems during all phases of the mission, with the following exceptions: adaptive structures, engines and thermal protection systems.

ISO 21648:2008 establishes the design, analysis, material selection and characterization, fabrication, test and inspection of the flywheel module (FM) in a flywheel used for energy storage in space systems. These requirements, when implemented on a flywheel module, will ensure a high level of confidence in achieving safe operation and mission success. With appropriate modifications, ISO 21648:2008 can also be applied to similar devices, such as momentum and reaction wheels and control-moment gyroscopes. The requirements set forth in ISO 21648:2008 are the minimum requirements for flywheel modules in flywheels used in space flight applications. They are specifically applicable to the parts in the flywheel rotor assembly (FRA), including rim, hub and/or shaft and other associated rotating parts, such as the bearings and the motor generator rotor. The requirements are also relevant to the non-rotating parts, such as module housing, main suspension assembly (magnetic or rolling element bearings, superconductor bearings, etc.), motor stator, caging mechanism and sensors within the module housing, and backup bearings, if applicable. However, control and interface electronics are not covered in ISO 21648:2008.

ISO 16454:2007 is intended to be used for the determination of the stress/strain distribution and margins of safety in launch vehicles and spacecraft primary structure design. Liquid propellant engine structures, solid propellant engine nozzles and the solid propellant itself are not covered, but liquid propellant tanks, pressure vessels and solid propellant cases are within the scope of ISO 16454:2007. ISO 16454:2007 provides requirements for the determination of maximum stress and corresponding margin of safety under loading, and defines criteria for static strength failure modes, such as rupture, collapse and detrimental yielding. Critical conditions associated with fatigue, creep and crack growths are not covered. Notwithstanding these limitations in scope, the results of stress calculations based on the requirements of ISO 16454:2007 are applicable to other critical condition analyses. In accordance with the requirements of ISO 16454:2007, models, methods and procedures for stress determination can also be applied to the displacements and deformation calculations, as well as to the loads definition, applied to substructures and structural members of structures under consideration. When ISO 16454:2007 is applied, it is assumed that temperature distribution has been determined and is used as input data.

ISO 14624-7:2006 specifies test equipment and techniques used to identify interactions resulting from exposure of a material to an aerospace fluid. ISO 14624-7:2006 can be used to determine the reactivity of materials with aerospace fluids. It provides a means to determine the effects of minor amounts of aerospace fluids, such as in a splash or spill, on materials used in ground support processing operations, and in the selection of personal safety equipment.

ISO 14624-6:2006 specifies test equipment and techniques used to identify interactions resulting from exposure of a material to an aerospace fluid. ISO 14624-6:2006 can be used to determine the reactivity of processing materials with aerospace fluids either through intent or casual exposure. It provides a means to determine the effects of minor amounts of fluids, such as a splash or spill, on materials used in ground support processing operations.

ISO 21347:2005 establishes general requirements for the application of fracture control technology to fracture critical items (FCIs) fabricated by metallic, non-metallic or composite materials. It also establishes mechanical damage control requirements for mechanical damage critical items (MDCIs) fabricated by composite materials. These requirements, when implemented on a particular space system, may assure a high level of confidence in achieving safe operation and mission success. The requirements set forth in ISO 21347:2005 are the minimum fracture control and mechanical damage control requirements for FCIs and MDCIs in general space systems, including launch vehicles and spacecraft. With necessary modifications, these requirements may also be applicable to reusable launch vehicles (RLVs). ISO 21347:2005 is not applicable to the NASA Space Shuttle and its payloads or the International Space Station and its equipment since they already have a set of specific requirements suitable for their special applications. ISO 21347:2005 is not applicable in processing detected defects.

ISO 15387:2005 specifies the requirements for measurement and calibration procedures of single-junction space solar cells only. The main body of ISO 15387:2004 specifies the requirements for Air Mass Zero (AM0) standard calibration. The relative measurement procedures are provided as annexes.

ISO 14954:2005 normalizes the exchange of mathematical models between spacecraft contractors (SCC) and launch service providers (LSP). It identifies standard methods for modelling the dynamic behaviour of both launch vehicles (LV) and spacecraft (SC) particularly when they are coupled prior to launch and during the early moments of the launch phase. In standard mode, the delivered models represent dynamic and static behaviour at the launcher interface. The requirements provided in ISO 14954:2005 are the minimum necessary for dynamic coupled analysis. They may be not sufficient for stress analysis. ISO 14954:2005 does not include the validation of spacecraft models.

ISO 14623:2003, based on general space experience and practice, specifies general and detailed requirements for metallic pressure vessels, composite overwrapped pressure vessels with metallic liners and metallic pressurized structures used in space systems. It is not applicable to pressure components (lines, fittings, valves, hoses, etc.) or to special pressurized hardware (batteries, heat pipes, cryostats and sealed containers).

ISO 14624-4:2003 specifies a test method for determining the flammability of aerospace materials in pressurized gaseous oxygen (GOX) and oxygen-enriched environments, at ambient temperature. This method may also be used to provide supplementary information by testing at pressures other than the intended use pressure. The standard pressure range for this test method is from ambient to 69 000 kPa.

This International Standard specifies a procedure for determining the loading level of a qualification test of a launch vehicle structure and takes into account all the minimum allowable strength characteristics necessary for these structures. This International Standard establishes the required resistance necessary for all mass-produced items to comply with product assurance criteria.

This International Standard establishes general requirements for contamination and cleanliness control that are applicable, at all tiers of supply, to the development of space systems, including ground processing facilities, ground support equipment, launch vehicles, spacecraft, payloads, and ground processing and on-orbit operations. It also provides guidelines for the establishment of a contamination and cleanliness control programme.

ISO 14624-5:2006 specifies test equipment and techniques used to identify interactions resulting from exposure of a material to an aerospace fluid. ISO 14624-5:2006 may be used to determine the reactivity of system and component materials with aerospace fluids. It is applicable for determining interactive reactions between propellants and materials used in the design, construction, and operation of propellant storage, transfer, and flight systems. While this procedure is an excellent quick screen test for long-term propellant compatibility, it is semi-qualitative, and (if exposures exceed twelve months) long-term tests need to be used to quantify degradation as a function of time under use conditions.

ISO 14624-3:2005 specifies a method for determining the identity and quantity of volatile offgassed products from materials and assembled articles utilized in manned, pressurized spacecraft. This test method is not intended to model or simulate spacecraft atmospheres.

ISO 15388:2004 establishes general requirements for contamination and cleanliness control to be applied, at all tiers of supply, to the development of space systems including ground processing facilities, ground support equipment, launch vehicles, spacecraft, payloads, and ground processing and on-orbit operations. It also provides guidelines for the establishment of a contamination and cleanliness control programme.

ISO 14624-1:2003 specifies a method for the determination of the flammability of aerospace materials by upward flame propagation. Specifically, this test determines if a material, when exposed to a standard ignition source, will self-extinguish and not transfer burning debris to adjacent materials which can be ignited by such debris.

ISO 14624-2:2003 specifies two test methods for determining the flammability of electrical-wire insulation and accessory materials by exposure to an external ignition source in a static environment (Test A) and in a gas-flow environment (Test B).

ISO 14302:2002 establishes performance requirements for the purpose of ensuring space systems electromagnetic compatibility (EMC). The engineering issues to be addressed in order to achieve system-level EMC are identified herein, with guidance and rationale towards achieving specification conformance. The method for the derivation of typical equipment-level requirements from a space-system-level requirement is illustrated.