ISO/TC 20 - Aircraft and space vehicles

This document specifies requirements for the classification and grading of civil uncrewed aircraft systems (UAS). This document applies to heavier-than-air aircraft as well as aerostats of any possible architecture. This document applies to the industrial conception, development, design, production and delivery of civil UAS. It also applies to operations, modification, repair and maintenance of civil UAS. NOTE The characteristics in this document can be used individually or in combination, to meet specific needs of the classification and grading of civil UAS. This document does not apply to taxonomies of: automation levels; vertiports; UTM services.

This document defines the contents, methods and requirements of configuration management for space projects, and the responsibilities and authorities of related parties. It is intended to be used in conjunction with ISO 14300-1:2023, Clause 10. This document is applicable to the configuration management of space projects from the mission analysis phase to the disposal phase.

This document specifies the safety programme and the technical safety requirements that are implemented in order to conform to the safety policy defined in ISO 14300-2. It is intended to protect flight and ground personnel, the launch vehicle, associated payloads, ground support equipment, the general public, public and private property, and the environment from hazards associated with space systems. This document is applicable to all space projects where during any project phase there exists the potential for hazards to personnel or the general public, space flight systems, ground support equipment, facilities, public or private property, or the environment.

This document specifies the procedures for training personnel who will be involved in the operation of uncrewed aircraft systems (UAS). This document defines: knowledge, skill, attitude and qualification criteria required for UAS remote pilots (RP), remote pilot in command (rPIC) and UAS training organizations (UTO) that provide training to UAS remote pilots and other personnel involved in UAS operations; training curriculum and contents for specific learning courses; qualification and criteria for verification of achieved competence by the training organizations; general procedures for providing training of UAS personnel. NOTE 1 An UTO can include additional topics or learning objectives, such as when required by legally binding rules in the applicable jurisdiction. NOTE 2 A UAS operator can also act as the UTO, providing that possible conflict of interest between training and operations is properly managed.

This document specifies the interfaces between a launch vehicle (LV) and the spacecraft (SC) being launched, to provide LV and SC organizations with the necessary format for presenting the required technical data on existing and future interfaces. Its intended purpose is to minimize costs and reduce the risks from errors resulting from miscommunication. It does not limit the ability of LV or SC organizations to specify unique requirements.

This document specifies the requirements for safe commercial operations of uncrewed aircraft system (UAS), including the external safety-critical service providing command and control (C2) Link. This document applies to all commercial UAS regardless of size, application or location and represents the international best practice for the safe commercial operation of any UAS.

This document defines terms used in the field of pilot training with the use of technical equipment, called flight simulators, enhancing safety by allowing pilots to practice various scenarios in a controlled environments, without the need of an actual aircraft. This document establishes the terms and definitions of the basic concepts applied in science, engineering and manufacturing in the field of flight simulation training devices (airplane and helicopter).

This document provides a framework to assess, reduce and control the potential risks that spacecraft and launch vehicle orbital stages (referred to hereinafter as “space vehicles”) pose to people and the environment when those space vehicles re-enter the Earth's atmosphere and impact the Earth’s surface. It applies to the planning, design and review of space vehicle missions for which controlled or uncontrolled re-entry is inevitable. This document applies to the following objects when assessing their risk to the ground: objects re-entering from orbit; launch vehicles (including payloads, other objects separated during the ascent phase, etc.) that are mentioned in flight safety activities under ISO 14620-2:2019[1], 6.2; interplanetary spacecraft returning to Earth. This document does not apply to systems with wings and control functions intended for targeted landing. This document assumes that the main specifications and operational procedures for ensuring safety on the ground against the re-entry of spacecraft containing radioactive material have already been determined in the mission requirements definition stage, system definition stage, operational concept definition stage, etc. Therefore, apart from matters related to re-entry safety, the main parts of the mission design and operational concept of spacecraft containing radioactive material are outside the scope of this standard.

This document specifies the design requirements (and tests) for the crimping of insulated and non-insulated joints to general purpose electrical cables for aircraft, with conductors of copper, copper alloy, aluminium or aluminium alloy, in locations in which the stabilized conductor temperature does not exceed the values specified for the relevant type of cable, i.e. 105 °C, 190 °C or 260 °C. This document specifies the type of cable to use for the joints (see 4.1). The document also contains recommendations relating to the inspection of such connections and the tools used to perform the crimping operation. Because satisfactory crimping is dependent upon the maintenance and setting of tools, it also contains recommendations for tests to confirm their serviceability. NOTE Testing of crimped joints to assess their suitability for aircraft shows that certain environmental conditions, for example vibration, have no significant effect on the performance of the joints. Therefore, such tests are not provided in this document.

This document is applicable to whole body vibration as a significant hazard. It also specifies the methods for determining the vibration emission transmitted to the whole body of drivers standing or seated on freely moveable ground support equipment (GSE) when driving, for purposes of type evaluation and declaration. This document also specifies methods for verifying vibration emission. This document is applicable to self-powered GSE only. The test results do not apply to the determination of whole body vibration exposure of persons. This document is intended to be used in conjunction with the different parts of the EN 1915 series and the EN 12312 series. This document does not apply to GSE manufactured before the date of its publication.

This document provides the workflow and technical requirements for perceiving, evaluating and avoiding collisions among orbiting objects, data requirements for these tasks, identifies techniques that can be used to estimate either the probability or the consequence of collisions, or both, and provides requirements and guidance for executing collision avoidance manoeuvres.

This document specifies the required characteristics for metric plain or slotted (castellated) nuts, with MJ threads according to ISO 5855-2, for use in aerospace construction. It is applicable to nuts as defined above, provided that reference is made to this document in the relevant definition document.

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].

This document specifies test methods for fitting assemblies used in aircraft fluid systems in the pressure and temperature ranges covered by pressure from classes B, to K, and temperature types I, II and III of ISO 6771. This document applies each time that it is referred to in a procurement specification or other definition document which contains the pass and fail criteria for these tests.

This document specifies the required characteristics for metric self-locking nuts, with MJ threads, for use in aerospace construction at a maximum temperature less than or equal to 425 °C. It is applicable to nuts as defined above, provided that reference is made to this document in the relevant definition document.

This document specifies the requirements and procedures for the calibration of primary and secondary reference solar cells under the air mass zero (AM0) spectrum. It is applicable to both single-junction and multi-junction solar cells.

This document comprehensively examines information grounded in International Standards applicable to uncrewed aircraft system (UAS) traffic management (UTM) systems and the operational frameworks for UTM systems across various countries. It systematically catalogues the current entities involved in UTM systems, including the actors, services, functions and data. Additionally, it delineates the safety, security and quality specifications for these services, focusing on data management and referring, where appropriate, to standards developed by other standard development organizations (SDOs).

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 the minimum requirements for airworthiness approval of air cargo pallets, nets and containers, generally designated as air cargo unit load devices (ULD). This document is intended to provide a uniform technical reference for air cargo unit load devices approval. As a prerequisite, it is presupposed that the applicable general civil aviation requirements and the aircraft manufacturer’s approved Weight and Balance Manual are followed. This document defines the minimum performance requirements and test parameters for air cargo unit load devices requiring approval of airworthiness for installation in an approved aircraft cargo compartment and restraint system that complies with the cargo restraint and occupant protection requirements of CCAR 25, EASA CS-25 or 14 CFR Part 25, except for the 9,0 g forward ultimate inertia force of § 25.561 (b) (3) (ii). This document applies to airworthiness approved air cargo unit load devices intended for carriage on board civil transport category airplanes type certificated under CCAR 25, EASA CS-25 or 14 CFR Part 25, or equivalent. This document exclusively applies to unit load devices airworthiness approval and testing parameters. It does not apply to aircraft design or aircraft operating requirements, which are provided by the approved Weight and Balance Manual for each aircraft type. Other aspects that do not directly pertain to air cargo unit load devices airworthiness approval and testing are not covered by this document, e.g.: — ULD design specifications; — ULD in service damage limits; — ULD restraint malfunction limitations; — ULD test methods; — ULD load distribution models; — ULD maximum allowable contours; — ULD CG (centre for gravity) location control means; — ULD pressure equalization methods; — ULD utilization guidelines. NOTE The requirements for cargo covers are not defined in this document, except insofar as net restraint is incorporated therein.

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 specifies the characteristics and quality assurance requirements for MJ thread bolts made of heat and corrosion resisting steel, of strength class 1 100 MPa, for aerospace construction. It is applicable whenever it is referenced in a definition document.

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 defines terms relating to uncrewed aircraft systems that are widely used in science and technology.

This document specifies test methods for metric self-locking nuts with MJ threads intended for use in aerospace applications at maximum operating temperature greater than 425 °C. It describes the test device and the method for each test. It applies to self-locking nuts as defined above, provided that the relevant documents (dimensional standard, product standard, drawing, procurement specification, etc.) refer to this document.

This document is applicable to seamless tubing of circular cross-section made from titanium alloy and intended for use primarily in systems with system operating pressure of 35 MPa (5 080 psi) (Pressure Class J), but usage is not limited to such applications.

This document defines the terms related to air cargo and aircraft ground equipment. The terms and definitions of this document are primarily intended to provide uniform understanding. It is intended that they be used in any other documents, manuals and standards in the areas of air cargo and airport ground equipment.

This document specifies a planar flexure test procedure for reconnectable and permanent hydraulic tube joints and fittings. This procedure is intended for conducting flexure tests on fittings with high-strength hydraulic tubes made of corrosion-resisting steel, titanium and aluminium for use on commercial and military aircraft.

This document specifies the characteristics and quality assurance requirements for MJ thread bolts made of alloy steel, of strength class 1 100 MPa, for aerospace construction. It is applicable whenever it is referenced in a definition document.

This document specifies requirements for producing and testing a dyed sulfuric acid anodic coating on aluminium alloys. The anodizing process is applied in the manufacture of aerospace products to improve paint adhesion and resistance to corrosion and can colour the part in accordance with the drawing requirements.

This document specifies the requirements for technical procedures, quality inspection, etc. for the surface treatment of austenitic stainless steel parts (e.g. 300 series, AISI 651, A286 or equivalent). This document applies to the removal of organic and inorganic contaminants, surface cleaning, surface finishing and surface passivation before the non-destructive test of austenitic stainless steel parts.

This document specifies the requirements for technical procedures, quality inspection, etc. for the surface treatment of martensitic, precipitation hardening and maraging stainless steel parts (e.g.400 series, 17-7PH, 17-4PH, 15-5PH, AM350, AM355, PH15-7Mo, PH13-8Mo, Custom 450 and 455 or equivalent). It provides practical methods for removing contaminants and for obtaining suitable corrosion resistance for aerospace applications. This document applies to the removal of organic and inorganic contaminants, surface cleaning, surface finishing and surface passivation before non-destructive inspection of martensitic, precipitation hardening and maraging stainless steel parts.

This document specifies requirements for producing and testing an undyed sulfuric acid anodic coating on aluminium alloys. The anodizing process is applied in the manufacture of aerospace products to improve paint adhesion and resistance to corrosion.

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 specifies the minimum design and performance criteria and testing methods of passive fire-resistant containers (FRCs) used in cargo compartments of civil transport aircraft to improve fire protection. This document does not cover requirements for fire detection or suppression devices. The specified fire-resistant containers (FRCs) are passive devices capable of containing a fire for a specific duration.

This document specifies safety and quality requirements for detection and avoidance (DAA) systems used between uncrewed aircraft systems (UAS) and other objects including aircraft. This document includes the requirements for radars and optical sensors used for DAA and is derived to meet the requirements for UAS operations involving DAA set out in ISO 21384-3.

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 specifies the outside diameters and thicknesses of tubes, for all metallic materials, to be selected for all uses in aircraft structural and system design.

This document defines the CCSDS and International Organization for Standardization (ISO) Reference Model for an Open Archival Information System (OAIS). An OAIS is an Archive system consisting of hardware, software, information, and policy-based processes and procedures put in place and operated by an organization and its staff. The organization has accepted the responsibility to preserve information and make it available for a Designated Community. The organization may be part of a larger organization. The system meets a set of mandatory responsibilities that allow an OAIS Archive to be distinguished from other uses of the term ‘archive’. The set of mandatory responsibilities an OAIS Archive must perform are defined in REF _Ref511638039 \r \h 3.2 08D0C9EA79F9BACE118C8200AA004BA90B02000000080000000E0000005F005200650066003500310031003600330038003000330039000000 . The term ‘Open’ in OAIS is used to imply that this Recommended Practice, as well as future related Recommended Practices and standards, are developed in open forums, and it does not imply that access to the Archive is unrestricted. The information being maintained has been deemed to need Long Term Preservation, even if the OAIS itself is not permanent. Long Term is long enough to be concerned with the impacts of changing technologies, as well as support for new media and data formats, or with a changing Knowledge Base of the Designated Community or changes within the Designated Community or its definition. Long Term may extend indefinitely. In this Reference Model there is a particular focus on digital information, both as the primary forms of information held and as supporting information for both digitally and physically preserved materials. Therefore, the model accommodates information that is inherently non-digital (e.g., a physical sample), but the modelling and preservation of such information is not addressed in detail. This Reference Model: – provides a framework for the understanding and increased awareness of archival concepts needed for Long Term digital information preservation and access; – provides the concepts needed by non-archival organizations to be effective participants in the preservation process; – provides a framework, including terminology and concepts, for describing and comparing architectures and operations of existing and future Archives; – provides a framework for describing and comparing different Long Term Preservation strategies and techniques; – provides a basis for comparing the data models of digital information preserved by Archives and for discussing how the data models and the underlying information may change over time; – provides a framework that may be expanded by other efforts to cover Long Term Preservation of information that is NOT in digital form (e.g., physical media and physical samples); – expands consensus on the elements and processes for Long Term digital information preservation and access, and promotes a larger market which vendors can support; – guides the identification and production of OAIS-related standards. The reference model addresses a full range of archival information preservation functions including ingest, archival storage, data management, access, and dissemination. It also addresses the migration of digital information to new media and forms, the information models used to represent the information, the role of software in information preservation, and the exchange of digital information among Archives. It identifies both internal and external interfaces to the Archive functions, and it identifies a number of high-level services at these interfaces. It provides various illustrative examples and some ‘best practice’ recommendations. It defines a minimal set of responsibilities for an Archive to be called an OAIS, and it also defines a maximal Archive to provide a broad set of useful terms and concepts.

This document specifies minimum requirements for dimensions and unobstructed space around main deck passenger doors on the outer skin of civil transport aircraft, applicable when these doors are designed to accept the connection of existing passenger boarding bridges or transfer vehicles. This document is not applicable to existing models of civil transport aircraft, or derivative models with entry into service up to the year 2000 with the same fuselage, for which the aircraft-mating section of passenger boarding bridges or passenger transfer vehicles is expected to be compatible with ISO 16004.

This document defines a CCSDS Recommended Practice (and ISO standard) on which to base the operations of the organization(s) which assess the trustworthiness of digital repositories using the latest version of CCSDS 652.0/ISO 16363 (reference REF R_652x0m2AuditandCertificationofTrustwor \h[1] 08D0C9EA79F9BACE118C8200AA004BA90B02000000080000002900000052005F00360035003200780030006D0032004100750064006900740061006E006400430065007200740069006600690063006100740069006F006E006F0066005400720075007300740077006F0072000000 ) and provide the appropriate certification. This document specifies requirements for bodies providing audit and certification of digital repositories, based on the metrics contained within ISO/IEC 17021-1 (reference REF R_ISOIEC170212011ConformityAssessmentReq \h \* MERGEFORMAT [4] 08D0C9EA79F9BACE118C8200AA004BA90B02000000080000002900000052005F00490053004F0049004500430031003700300032003100320030003100310043006F006E0066006F0072006D006900740079004100730073006500730073006D0065006E0074005200650071000000 ) and reference REF R_652x0m2AuditandCertificationofTrustwor \h[1] 08D0C9EA79F9BACE118C8200AA004BA90B02000000080000002900000052005F00360035003200780030006D0032004100750064006900740061006E006400430065007200740069006600690063006100740069006F006E006F0066005400720075007300740077006F0072000000 . It is primarily intended to support the accreditation of bodies providing such certification. ISO/IEC 17021-1 provides the bulk of the requirements on bodies offering audit and certification for general types of management systems. However, for each specific type of system, specific additional requirements will be needed, for example, to specify the standard against which the audit is to be made and the qualifications which auditors require. This document provides the (small number of) specific additions required for bodies providing audit and certification of candidate trustworthy digital repositories. Trustworthy here means that they can be trusted to maintain, over the long-term, the understandability and usability of digitally encoded information placed into their safekeeping. In order improve readability the section numbers are kept consistent with those of ISO/IEC 17021-1. Some subsections are applicable as they stand, and these are simply enumerated; otherwise additions to subsections are explicitly given. In the former case the sections may consist of just a few sentences. As a result this document must be read in conjunction with ISO/IEC 17021-1. The requirements contained in this CCSDS Recommended Practice need to be demonstrated in terms of competence and reliability by any organization or body providing certification of digital repositories.