ISO/TC 20/SC 14 - Space systems and operations

This document provides terms and definitions for design, tests, reliability analysis and quality control of liquid rocket engines. The terms can be used in all types of documentation and subject-matter literature, related to standardization or use of the results of field-specific works.

This document establishes procedures for the analysis of failures that occur during the acceptance testing or operation of launch pad and integration site facilities, systems and equipment. The procedures define the processes for investigating, analysing and identifying the probable causes of failures, and for developing corrective actions to preclude future failures. This document provides: — rules for investigating, analysing and identifying the causes of failures; — sufficient information so that corrective action can be implemented to prevent failure recurrence; — a uniform method for maintaining records of the findings of all failure causes so as to provide information for other failure investigations. This document applies to launch pad and integration sites used for the launch of launch vehicle with spacecraft for public and commercial purposes.

This document describes minimum requirements for small spacecraft. This document covers 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 can be applied by small spacecraft developers, as well as dispenser providers and launch operators.

This document 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. This document applies to all structural items, including fracture-critical hardware used in space systems during all phases of the mission, with the following exceptions: adaptive structures, propulsion systems, nuclear systems, and thermal protection systems.

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

This document establishes general requirements for the application of fracture control technology to fracture-critical items (FCIs) fabricated from metallic, non-metallic or composite materials. It also establishes mechanical damage control requirements for mechanical-damage-critical items (MDCIs) fabricated from composite materials. These requirements, when implemented on a particular space system, can assure a high level of confidence in achieving safe operation and mission success. This document provides the minimum fracture control and mechanical damage control requirements for FCIs and MDCIs in general space systems, including launch vehicles, spacecraft and ground support equipment. With modifications, these requirements can also be applicable to reusable launch vehicles (RLVs). This document is not applicable to projects which already have a set of specific fracture and damage control requirements suitable for their special applications. This document is not applicable to processing detected defects.

This document provides general requirements of manufacturing readiness review (MRR) for deliverable space products, including initiation process of MRR, implementation process of MRR and activities after MRR. This document is applicable to the MRR of deliverable space products.

This document provides the criteria for stable on-orbit operation of the spacecraft's AOCS. It addresses the factors affecting the spacecraft's on-orbit stability by specifying principles and requirements for establishing the spacecraft AOCS's capability for stable on-orbit operation, which include: — principles for judging data validity and the requisite procedures for handling such data; — anomaly detection; — management of software and hardware failures; — safety boundary checks; — activation protocols for emergency survival modes. This document also establishes the functional interface between on-orbit autonomy and ground-based maintenance operations, ensuring that the spacecraft maintains its intended attitude and orbit. This document is applicable to the attitude and orbit control systems of various types of spacecraft.

This document establishes the general safety launch collision avoidance (safety LCOLA) requirements for the avoidance of collision between the collection of newly launched objects resulting from a space launch [including launch vehicle stage(s) and payloads or released objects] and human-inhabited or human-habitable space stations and space vehicles. The document specifies the requirements for the analysis of launch times and procedures for identifying safe launch opportunities. It also describes the assessment and constraints for collision avoidance risk evaluation metrics (launch collision probability and standoff distance).

This document specifies procedures in the preparation and carrying out of the modernization process of launch complexes and their components. These procedures are devised in case there is a need to make changes in existing configuration of launch complexes. This document establishes the following: a) modernization stages; b) modernization performance requirements; c) functions of the main participants of the modernization process and their interactions. This document is applicable to organizations involved in the modernization of the launch complexes.

This document provides criteria for planning or rating a failure reporting, analysis and corrective action (FRACA) process, with regard to its capability to collect, process, assess, and eliminate or control failures, in a cost-effective manner that is commensurate with the product safety or mission severity category and life cycle systems engineering product-critical characteristics data. This document is applicable for managing failures that occur to space, launch and ground control systems and equipment after qualification. The requirements in this document apply to all stakeholders that contribute to the design, analysis, test, production and operation of space systems, as required in ISO 14300-2.

This document provides information on how electrical designers determine the allowable limit of electric wire in space condition. This document provides the basis of the allowable wire current and its derated value in published technical standards. This document also provides the results of comparing the derated wire current values depending on the number of bundled wires, wire type and temperature environments, which can help the system designer to handle the difference when determining the limit of wire ampacity.

This document defines, extending the requirements of ISO 14300-1, the principles and requirements for integrated risk management on a space project. It explains what is needed to implement a project-integrated risk management policy by any project actor, at any level (i.e. customer, first-level supplier or lower-level suppliers). This document contains a summary of the general risk management process, which is subdivided into four basic steps and nine tasks. This document is applicable to all the space project phases, as defined in ISO 14300-1.

This document defines the principles used to determine loads and the induced environment during the service life of a space system and its components, taking account of the notions of probability, combined loads, corresponding safety factors and life cycle.

This document provides product assurance requirements and recommendations for commercial satellites throughout all phases. This document is applicable to the prime contractor, subcontractors and suppliers.

This document provides requirements for the safety management and operation of assembly, integration and test (AIT) activities related to spacecraft projects and applications including the responsibilities of the organization involved in the AIT operations for spacecraft products. This document provides a method to identify hazards, control and reduce safety risk to acceptable levels in the activities of spacecraft assembly, integration, testing, hoisting, logistics and handling. This document is applicable to space test centres and entities providing operating infrastructure and facilities for spacecraft AIT. It can serve as a reference for the AIT of the spacecraft system, its subsystems and equipment.

This document establishes requirements and guidance for the ground-based environmental testing of thermal control materials (TCMs) applied on spacecraft surface. This document describes the test methods for the following environmental conditions: charged particle radiation(s), solar ultraviolet (UV) radiation, atomic oxygen (AO) and thermal cycling. This document does not cover other environmental effects such as contamination effect of the Xenon ion engines plume (so called artificial effect) or the effects of neutron (see detailed information in Annex B). This document is applicable to typical TCM(s), including but not limited to, paint, silicate, film, anodic oxide, and glass (optical solar reflector, OSR). This document can be referenced for other materials, to which similar requirements apply. This document is devoted to material estimation or evaluation tests and can be tailored according to specific applications.

This document defines requirements and procedures for analysing the risk that an unmanned spacecraft fails as a result of a space debris or meteoroid impact.

This document describes internal and external interfaces of CubeSat. The internal interface includes the interface between components and the interface between a CubeSat platform and a mission payload. The external interface is limited to the umbilical connectors, i.e. access port. The document also describes the items to be included in the datasheet of the CubeSat components and platforms. The datasheet requirements apply to catalogued commercial products ready for sale. This document does not cover the interface between CubeSat and its deployer, i.e. POD. This document is applicable to CubeSats of all sizes.

This document specifies requirements for the list of parameters, measured during firing bench and flight tests. The requirements of the document apply to all the types of expendable liquid rocket engines supplied to the user: a) operating on all types of propellant (including cryogenic); b) with afterburning (with gradual burning) and without afterburning (without gradual burning); c) low-thrust engines: one component (monopropellant) and two-component (bipropellant); d) with a single firing or multiple firings. The document doesn’t specify firing bench test preparation and testing procedure, methods of test results processing and analysis, or requirements to measurement accuracy. The document specifies mandatory and optional parameters.

This document presents the requirements and recommendations for the management of systems engineering for space systems. This document addresses the systems engineering activities and provides guidelines for interfacing with specific major management subjects (e.g. configuration management, data management, interface management, risk management, requirements management, and integrated logistics support). This document establishes a common reference for all customers and suppliers in the space sector to work with management of systems engineering for all space products and projects. This document does not describe in detail the standard systems engineering process or project management process for all types of space systems.

This document defines requirements and recommendations to be used for the management of cybersecurity in space systems. Space systems include manned and unmanned spacecraft, launcher, payload, experiment, ground equipment and any other space facilities. This document describes the processes, techniques, and responsibilities for managing the cybersecurity, ways to prevent and mitigate accidents and incidents. This document addresses systems engineering activities and provides requirements and recommendations for security engineering. This document establishes a common reference for the space sector to work to manage the systems engineering issues related to cybersecurity for all space products, services and projects. This document doesn't describe in detail the systems engineering processes or related project management processes, or detailed requirements or processes for cybersecurity.

This document contains internationally accepted descriptions of the main phenomena of space weather, including its sources and effects upon space systems. This document is applicable for a variety of engineering and scientific domains. It is applicable to space system operations include ground-based, on-orbit, and deep space automated satellite operations. It can be applied by developers of software systems for space systems, designers of space systems, and launchers of space systems.

This document provides technical methods to calculate the precipitation efficiency and liability of a flight model by measuring the screening effectiveness of thermal cycles. This document is applicable to the recurring production unit and other hardware assembly levels, as either an option to reduce or a method to tailor the baseline number of cycles for thermal vacuum and thermal cycle acceptance tests.

This document 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 document describes the effective vertical cut-off rigidities of charged particles for near-Earth space and establishes principal requirements for their calculation based on different models of Earth’s geomagnetic field.[1] The techniques are useful for determination of penetrating into the Earth's magnetosphere by charged particle fluxes, as well as for test and estimations of the impact on spacecrafts and other equipment in the near-Earth space.

This document 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. This document does not cover critical-conditions-induced fatigue, creep and crack growths. Notwithstanding these limitations in scope, the results of stress calculations based on the requirements of this document are applicable to other critical condition analysis. This document is applicable to the determination of the stress/strain distribution and margins of safety in launch vehicles and spacecraft load-bearing elements 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 this document. In accordance with the requirements of this document, the models, methods and procedures for stress calculation can also be applicable to the displacements and deformation calculation, as well as the calculation of loads, applied to substructures and structural elements under consideration. When this document is applied, it is assumed that temperature distribution has been determined and is used as input data.

This document describes a process for the long-duration orbit lifetime prediction of orbit lifetime for spacecraft, launch vehicles, upper stages and associated debris in LEO-crossing orbits after mission phase (including any mission lifetime extensions). The document also clarifies: a) modelling approaches and resources for solar and geomagnetic activity modelling; b) resources for atmosphere model selection; c) approaches for spacecraft ballistic coefficient estimation.

This document specifies design and minimum verification requirements for lithium-ion batteries from the perspectives of performance, safety and logistics. This document is applicable to battery assemblies for space vehicles and component cells of batteries, which are critical devices to be harmonized with standards and regulations for other industries. In addition, this document is applicable to component cells which are not designed for space vehicles but can be used in space.

This document specifies four standard message formats for use in transferring spacecraft orbit information between space agencies and commercial or governmental spacecraft operators: The Orbit Parameter Message (OPM), the Orbit Mean-Elements Message (OMM), the Orbit Ephemeris Message (OEM), and the Orbit Comprehensive Message (OCM). Such exchanges are used for: a) pre-flight planning for tracking or navigation support; b) scheduling tracking support; c) carrying out tracking operations (sometimes called metric predicts); d) performing orbit comparisons; e) carrying out navigation operations such as orbit propagation and orbit reconstruction; f) assessing mutual physical and electromagnetic interference among satellites orbiting the same celestial body (primarily Earth, Moon, and Mars at present); g) performing orbit conjunction (collision avoidance) studies; and h) developing and executing collaborative maneuvers to mitigate interference or enhance mutual operations. This document includes sets of requirements and criteria that the message formats have been designed to meet. For exchanges in which these requirements do not capture the needs of the participating agencies and satellite operators, another mechanism may be selected. This document is an international standard published under the auspices of CCSDS and International Standards Organization (ISO) Technical Committee 20, Subcommittee 13, developed jointly and in concert with the ISO TC20/SC14. As such, this CCSDS standard is also properly labeled as ISO 26900. The recommended Orbit Data Message format is ASCII (reference REF R_ISO_IEC_8859_1_1998 \h [4] 08D0C9EA79F9BACE118C8200AA004BA90B02000000080000001600000052005F00490053004F005F004900450043005F0038003800350039005F0031005F0031003900390038000000 ). This document describes both ‘Keyword = Value Notation’ (KVN) as well as Extensible Markup Language (XML) (reference REF R_505x0b3XMLSpecificationforNavigationDa \h[5] 08D0C9EA79F9BACE118C8200AA004BA90B02000000080000002800000052005F00350030003500780030006200330058004D004C00530070006500630069006600690063006100740069006F006E0066006F0072004E0061007600690067006100740069006F006E0044000000 ) formatted messages. Selection of KVN or XML format should be mutually agreed between message exchange partners. NOTE – As currently specified, an OPM, OMM, or OEM file is to represent orbit data for a single spacecraft, and the OCM is to represent orbit data for either a single spacecraft or single parent spacecraft of a parent/child spacecraft deployment scenario. It is possible that the architecture may support multiple spacecraft per file; this could be considered in the future.

This document provides requirements that are either unique or particularly relevant to large constellations of spacecraft operating in the LEO protected region throughout their life cycle, including planning, designing, testing, operating and disposal activities. The requirements in this document are applicable to large constellation owners. While some are directly applicable to the constellation owners, others are allocated to the manufactures or operators under the responsibility of the constellation owners.

This document specifies lessons learned principles and guidelines that are applicable in all space project activities (management, technical, quality, cost and schedule). The application of this document is intended to be included in the supplier quality management system, but can be tailored in individual contracts as agreed by the customer and supplier, depending on: — the content of each project (size, technological level and novelty, particular organization, participants, etc.); — the interest and usefulness of the related information. The lessons learned information can result from any situation which can be encountered in similar contexts for future projects, i.e.: — undesirable experiences to be avoided; — strategies, rules, principles of design, validation, tests and operations proved to be successful or necessary. This document neither endorses nor recommends the transmission of company proprietary information to external entities as part of a lessons learned process. Implementing a formal lessons learned process as outlined in this document makes it possible to capture and benefit from this information. The lessons learned activity is an important contribution to the processing of the preventive and corrective actions specified in ISO 9001, ISO 17666, ISO 14620-1 and ISO 23460. This document also provides lessons learned processes and suggested lessons learned forms.

This document specifies the space programme/project management requirements, applicable through a top-down approach in a contractual relationship between customers and suppliers.

This document defines the product assurance (PA) policy, objectives, principles, and requirements for the establishment and implementation of PA programmes for space programmes covering mission definition, design, development, production and operations of space products, including disposal. The PA discipline covers: PA management, quality assurance, safety assurance, dependability (reliability, availability and maintainability), assurance of software and hardware products, as well as parts (including electrical, electromechanical and electronic components, and mechanical parts), materials and processes assurance. This document defines their respective objectives, policies, and principles to achieve the stated overall PA objectives throughout the complete life cycle of the products. This document applies to space products.

This document defines the quality assurance (QA) requirements for the establishment and implementation of product QA programmes for projects covering mission definition, design, development, production and operations of space systems, including disposal. It is applicable to the customer-supplier relationship for space products to the extent agreed by both parties.

This document specifies a method for determining the identity and quantity of volatile off-gassed compounds from materials and assembled articles utilized in manned, pressurized spacecraft.

This document specifies a method for the determination of the flammability of aerospace materials by upward flame propagation. This test determines if a material, when exposed to a standard ignition source, will self-extinguish and not transfer burning debris which can ignite adjacent materials.

This document 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). These tests determine if a wire insulation material, when exposed to a standard ignition source, will self-extinguish and not transfer burning debris which can ignite adjacent materials.

This document describes the technology for simulating space environments such as vacuum, cold black, and heat flux, as well as the compositions and functions of a thermal vacuum chamber (TVC). This kind of facility defined in this document is suitable for thermal vacuum tests (TVT) and thermal balance tests (TBT) on spacecraft-system level as well as on large-spacecraft-component level.

This document defines the general criteria for the development of flight-to-ground umbilical systems used by a space system. These criteria apply to the service arms or equivalent mechanisms, umbilical carriers and plates, couplings, connectors, withdrawal and retract devices, handling mechanisms and control systems for mechanisms, as well as the prevention of accidental cross-connection.

This document establishes basic requirements for interface control documents (ICD) writing and interface control procedures for the following items included in the launch system: payload, launch vehicle, ground support equipment (according to ISO 14625) and launch site (buildings with utility systems), specifically: a) ICD between the ground support equipment and the payload; b) ICD between the ground support equipment and the launch vehicle; c) ICD between items of the ground support equipment; d) ICD between the ground support equipment and the launch site. This document is applicable to organizations developing ground support equipment and to operators performing space activity.

This document provides the test requirements of three typical separation test methods, which are the combined separation test, the horizontal separation test, the individual falling separation test, for the separation between the launch vehicle (LV) and the spacecraft (or between stages of a prototype LV model). It also provides the requirements for the separation test unit, test data, test timing and sequence, pre-test simulation, test environment, exception handling, test results assessment, test documentation, test facilities, test installation, preliminary adjustment of the test setup, measurement and data acquisition. This document is applicable to test providers and interested parties to implement the separation test between the launch vehicle and the spacecraft.

This document specifies processes, requirements and recommendations for the breakdown of project management structures, collectively called project breakdown structures, in terms of the various specification (i.e. requirements), functional, product, work, cost, business and organizational breakdown structures that are established and implemented to contribute to the success of a space programme, which is often composed of one or more projects. It specifies the various types of project breakdown structures and gives processes, requirements and guidance concerning the composition of these breakdown structures. This document is applicable to project breakdown structures for a project, including at the top level of a programme, i.e. level 0, as indicated in ISO 14300-1. It is intended to be used either by an independent developer as a partial basis for programme processes or as a basis for an agreement between a supplier and a customer. This document also provides descriptions of the kinds of project breakdown structures that are commonly useful in contributing to the success of a space project. Other project breakdown structures not described in this document also often contribute to the success of a space project.

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 the requirements for a dependability (reliability, availability and maintainability) assurance programme for space projects. It defines the dependability requirements for space products as well as for system functions implemented in software, and the interaction between hardware and software. This document is applicable to all programme phases.

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 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 defines the primary space debris mitigation requirements applicable to all elements of unmanned systems launched into, or passing through, near-Earth space, including launch vehicle orbital stages, operating spacecraft and any objects released as part of normal operations.

This document specifies process requirements for project reviews as a set of required functions. It establishes requirements and recommendations on the function inputs, outputs, mechanisms and controlling conditions. This document specifies the responsibilities of a review board and gives guidance concerning review board composition. This document also provides descriptions of the kinds of reviews that are commonly useful in assuring the success of a space project. This document is applicable to status reviews for a project at any level within a larger project, as well as for major milestone reviews at the top level of a major project. It is intended to be used either by an independent developer as a basis for enterprise processes, or as a basis for an agreement between a supplier and a customer. It is intended for use in implementing the review requirements of ISO 14300-1, and ISO 14300-2, ISO 15865 and such other space systems and operations standards that require formal reviews.

This document contains requirements and guidelines for the utilization of off-the-shelf (OTS) items, their selection, acquisition, integration, qualification and implementation related to a space product or system. This document doesn't cover piece parts and materials, such as electrical, electronic and electromechanical (EEE) parts, thermocouples, rivets, fasteners, connectors, fittings, adhesives, insulation, wiring and plumbing.