49.140 - Space systems and operations
ICS 49.140 Details
Space systems and operations
Raumfahrtsysteme. Raumfahrtoperationen
Systemes spatiaux, développement et mise en oeuvre
Vesoljski sistemi in operacije
General Information
Frequently Asked Questions
ICS 49.140 is a classification code in the International Classification for Standards (ICS) system. It covers "Space systems and operations". The ICS is a hierarchical classification system used to organize international, regional, and national standards, facilitating the search and identification of standards across different fields.
There are 1112 standards classified under ICS 49.140 (Space systems and operations). These standards are published by international and regional standardization bodies including ISO, IEC, CEN, CENELEC, and ETSI.
The International Classification for Standards (ICS) is a hierarchical classification system maintained by ISO to organize standards and related documents. It uses a three-level structure with field (2 digits), group (3 digits), and sub-group (2 digits) codes. The ICS helps users find standards by subject area and enables statistical analysis of standards development activities.
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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.
- Standard28 pagesEnglish languagesale 15% off
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.
- Standard35 pagesEnglish languagesale 15% off
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.
- Standard52 pagesEnglish languagesale 15% off
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.
- Standard38 pagesEnglish languagesale 15% off
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.
- Standard43 pagesEnglish languagesale 15% off
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].
- Standard92 pagesEnglish languagesale 15% off
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.
- Standard102 pagesEnglish languagesale 15% off
The scope of the present document is to provide the elements needed for elaborating the programme execution logic and drafting the execution plan for the realization of a product.
NOTE 1 In this document, the term “logic” alone is sometimes used for “execution logic”.
NOTE 2 In this document, the term “product” is used to designate the object of the program concerned, and the term “system” is used to designate the product for anything related to system engineering.
NOTE 3 The product is also considered a “system-of-interest” and its enabling systems are also taken into account.
The execution logic and plan enable customers/suppliers to reach an agreement on how their respective processes and activities can be organized.
The aim is to enable each actor in the programme to manage their activities with sufficient visibility of the sequencing of the other stakeholdersʼ activities.
This document belongs to the documents supporting EN 9200 relating to the programme management specification.
The present document describes the principles of programme execution logic and defines the corresponding management requirements. This description is supplemented:
— on the one hand, in terms of execution logic principles, by:
— the challenges of a basic logic common to all actors (synchronization);
— the applicable criteria to set up this basic logic;
— the translation of this logic into the programme processes;
— on the other hand, in terms of implementing the execution logic, by:
— the procedures for practical implementation of the management requirements defined in EN 9200;
— adaptations of the logic according to the various constraints and specificities of the programme, and justification of these adaptations;
— the consistency between the basic logic at system level and the logics at subsystem and constituent levels.
The breakdown of clauses as used in this document gives a gradual understanding of the approach to be adopted to construct an execution logic. For instance:
— Clause 5 presents the end-purpose of a programme execution logic as well as the associated basic concepts and the constituents of this logic;
— Clause 6 describes and characterizes the process for building the logic;
— Clause 7 concerns change control to the execution logic;
— Clause 8 concentrates on the importance of capitalization and lessons learned.
This document applies to aeronautical, space and defence programmes. The principles can be extended to other areas of activity.
It applies to realization of a single product, of several samples or of a series. It applies to any customer/supplier level, while ensuring consistency between successive levels.
The principles described concern all programme actors, from initial expression of need through to closure of the programme.
- Standard47 pagesEnglish languagee-Library read for1 day
The scope of the present document is to provide the elements needed for elaborating the programme execution logic and drafting the execution plan for the realization of a product.
NOTE 1 In this document, the term “logic” alone is sometimes used for “execution logic”.
NOTE 2 In this document, the term “product” is used to designate the object of the program concerned, and the term “system” is used to designate the product for anything related to system engineering.
NOTE 3 The product is also considered a “system-of-interest” and its enabling systems are also taken into account.
The execution logic and plan enable customers/suppliers to reach an agreement on how their respective processes and activities can be organized.
The aim is to enable each actor in the programme to manage their activities with sufficient visibility of the sequencing of the other stakeholdersʼ activities.
This document belongs to the documents supporting EN 9200 relating to the programme management specification.
The present document describes the principles of programme execution logic and defines the corresponding management requirements. This description is supplemented:
— on the one hand, in terms of execution logic principles, by:
— the challenges of a basic logic common to all actors (synchronization);
— the applicable criteria to set up this basic logic;
— the translation of this logic into the programme processes;
— on the other hand, in terms of implementing the execution logic, by:
— the procedures for practical implementation of the management requirements defined in EN 9200;
— adaptations of the logic according to the various constraints and specificities of the programme, and justification of these adaptations;
— the consistency between the basic logic at system level and the logics at subsystem and constituent levels.
The breakdown of clauses as used in this document gives a gradual understanding of the approach to be adopted to construct an execution logic. For instance:
— Clause 5 presents the end-purpose of a programme execution logic as well as the associated basic concepts and the constituents of this logic;
— Clause 6 describes and characterizes the process for building the logic;
— Clause 7 concerns change control to the execution logic;
— Clause 8 concentrates on the importance of capitalization and lessons learned.
This document applies to aeronautical, space and defence programmes. The principles can be extended to other areas of activity.
It applies to realization of a single product, of several samples or of a series. It applies to any customer/supplier level, while ensuring consistency between successive levels.
The principles described concern all programme actors, from initial expression of need through to closure of the programme.
- Standard47 pagesEnglish languagee-Library read for1 day
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.
- Standard151 pagesEnglish languagee-Library read for1 day
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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.
- Standard30 pagesEnglish languagesale 15% off
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.
- Standard9 pagesEnglish languagesale 15% off
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.
- Standard69 pagesEnglish languagesale 15% off
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.
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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.
- Standard29 pagesEnglish languagesale 15% off
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.
- Standard9 pagesEnglish languagesale 15% off
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.
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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).
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The purpose of this document is to provide customers and their suppliers with a document specifying the notions of “construction” and “management” of product dependability and safety (RAMS).
It offers programme directors and project managers information likely to help them:
— determine the tasks to be performed and the application procedures, according to the specific nature of the programme and its goals;
— define and implement the provisions necessary for performing these tasks;
— within programme execution, situate the various tasks involved in constructing and managing the RAMS of a product.
This document applies to all programmes that involve customer/supplier relation.
RAMS management concerns not only all the products covered by these programmes, but also the components of these products and the production and support resources and processes to be implemented.
The provisions of this document can be negotiated at all levels between the parties directly concerned by a given programme. This implies, on the part of the ordering parties, that each lower level is provided with the information needed to perform the tasks and meet the specified targets. This also implies, on the part of suppliers, an escalation of information pertaining to the RAMS results of the products for which they are responsible.
This document is mainly concerned with the technical aspects, aspects of a legislative (in particular safety at work and regulatory conformity) and confidential nature are not dealt with in this document.
- Standard44 pagesEnglish languagee-Library read for1 day
The purpose of this document is to provide customers and their suppliers with a document specifying the notions of product reliability "construction" and "management".
It offers programme directors and project managers information likely to help them:
- determine the tasks to be performed and the application procedures, according to the specific nature of the programme and its goals;
- define and implement the provisions necessary for performing these tasks;
- within programme execution, situate the various tasks involved in constructing and managing the reliability of a product.
This document applies to all programmes (in particular aeronautical, space and armament programmes).
These reliability construction procedures concern not only all the products and its constituents covered by these programmes, but also the means and manufacturing processes to be implemented for their realization.
The provisions of this document can be negotiated at all levels between the parties directly concerned by a given programme. This implies, on the part of the customer, that each lower level is provided with the information necessary to perform tasks and meet the specified targets.
- Standard30 pagesEnglish languagee-Library read for1 day
The purpose of this document is to provide customers and their suppliers with a document specifying the notions of product reliability "construction" and "management".
It offers programme directors and project managers information likely to help them:
- determine the tasks to be performed and the application procedures, according to the specific nature of the programme and its goals;
- define and implement the provisions necessary for performing these tasks;
- within programme execution, situate the various tasks involved in constructing and managing the reliability of a product.
This document applies to all programmes (in particular aeronautical, space and armament programmes).
These reliability construction procedures concern not only all the products and its constituents covered by these programmes, but also the means and manufacturing processes to be implemented for their realization.
The provisions of this document can be negotiated at all levels between the parties directly concerned by a given programme. This implies, on the part of the customer, that each lower level is provided with the information necessary to perform tasks and meet the specified targets.
- Standard30 pagesEnglish languagee-Library read for1 day
The purpose of this document is to provide customers and their suppliers with a document specifying the notions of “construction” and “management” of product dependability and safety (RAMS).
It offers programme directors and project managers information likely to help them:
— determine the tasks to be performed and the application procedures, according to the specific nature of the programme and its goals;
— define and implement the provisions necessary for performing these tasks;
— within programme execution, situate the various tasks involved in constructing and managing the RAMS of a product.
This document applies to all programmes that involve customer/supplier relation.
RAMS management concerns not only all the products covered by these programmes, but also the components of these products and the production and support resources and processes to be implemented.
The provisions of this document can be negotiated at all levels between the parties directly concerned by a given programme. This implies, on the part of the ordering parties, that each lower level is provided with the information needed to perform the tasks and meet the specified targets. This also implies, on the part of suppliers, an escalation of information pertaining to the RAMS results of the products for which they are responsible.
This document is mainly concerned with the technical aspects, aspects of a legislative (in particular safety at work and regulatory conformity) and confidential nature are not dealt with in this document.
- Standard44 pagesEnglish languagee-Library read for1 day
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.
- Standard8 pagesEnglish languagesale 15% off
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.
- Standard22 pagesEnglish languagesale 15% off
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.
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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.
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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.
- Standard26 pagesEnglish languagesale 15% off
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.
- Standard151 pagesEnglish languagee-Library read for1 day
- Standard139 pagesEnglish languagesale 15% off
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.
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This document defines a CCSDS Recommended Practice on which to base an audit and certification process for assessing the trustworthiness of digital repositories. The scope of application of this document is the entire range of digital repositories.
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This document deals with the aspects of a project, in particular the terminology used. Many of these terms are already used with various definitions within the target communities for this practice, for example, space, science, life sciences, libraries, records management, and archival communities. It is expected that other communities can easily map this terminology to the terminology used within those communities. The Reference Model for an Open Archival Information System (OAIS) provided a starting point and inputs from a variety of other sources were used to arrive at the terms used within this standard. This document accomplishes the following: – identifies the Additional Information to be collected or improved at various points; – forms a basis for the specification of Data Management Plans (DMPs); – forms a basis for the identification and/or development of additional standards and implementation guides, including those that address particular concerns in more detail.
- Standard59 pagesEnglish languagesale 15% off
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.
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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.
- Standard23 pagesEnglish languagesale 15% off
This document is intended to stablish and define functional and performance requirements and associated tests for Galileo Timing Receivers. This document covers the following topics related to Galileo Timing Receivers:
- GNSS constellations and frequencies processed: Galileo plus additionally GPS, with nominal mode being dual-frequency processing,
- Time scales processed, including at least Galileo System Time and Universal Time Coordinate,
- User dynamics, with two operation modes: static users with well-known and static antenna position and dynamics users with moving antenna,
- Holdover devices,
- Nominal and back-up modes, including single-frequency modes, single-constellation modes and holdover mode.
- Processing of timing integrity information disseminated by the Galileo System,
- Time Receiver Autonomous Integrity Monitoring processing,
- Anti-jamming and anti-spoofing capabilities, including Automatic Gain Control monitoring and Galileo Open Service Navigation Message Authentication processing,
- Robustness to multipath.
In addition, this document gives guidelines for the installation and maintenance of the receiver, including antenna, cabling and receiver installation, initial and periodic receiver calibration, and periodic maintenance.
On top of the functional requirements, performance requirements this document defines in terms of different key performance indicators such as:
- Accuracy, availability, continuity and integrity requirements,
- T-RAIM performances, including time to alert,
- Holdover performances including maximum degradation of the timing solution with time and maximum holdover time,
This document also gives a simple test suite to verify the most fundamental requirements of the Galileo Timing Receivers.
- Standard112 pagesEnglish languagee-Library read for1 day
This document is intended to stablish and define functional and performance requirements and associated tests for Galileo Timing Receivers. This document covers the following topics related to Galileo Timing Receivers:
- GNSS constellations and frequencies processed: Galileo plus additionally GPS, with nominal mode being dual-frequency processing,
- Time scales processed, including at least Galileo System Time and Universal Time Coordinate,
- User dynamics, with two operation modes: static users with well-known and static antenna position and dynamics users with moving antenna,
- Holdover devices,
- Nominal and back-up modes, including single-frequency modes, single-constellation modes and holdover mode.
- Processing of timing integrity information disseminated by the Galileo System,
- Time Receiver Autonomous Integrity Monitoring processing,
- Anti-jamming and anti-spoofing capabilities, including Automatic Gain Control monitoring and Galileo Open Service Navigation Message Authentication processing,
- Robustness to multipath.
In addition, this document gives guidelines for the installation and maintenance of the receiver, including antenna, cabling and receiver installation, initial and periodic receiver calibration, and periodic maintenance.
On top of the functional requirements, performance requirements this document defines in terms of different key performance indicators such as:
- Accuracy, availability, continuity and integrity requirements,
- T-RAIM performances, including time to alert,
- Holdover performances including maximum degradation of the timing solution with time and maximum holdover time,
This document also gives a simple test suite to verify the most fundamental requirements of the Galileo Timing Receivers.
- Standard112 pagesEnglish languagee-Library read for1 day
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.
- Standard59 pagesEnglish languagesale 15% off
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.
- Standard34 pagesEnglish languagesale 15% off
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.
- Standard19 pagesEnglish languagesale 15% off
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.
- Technical specification8 pagesEnglish languagesale 15% off
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.
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This document 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 document, 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.
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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.
- Technical report29 pagesEnglish languagesale 15% off
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.
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ABSTRACT
This specification establishes the requirements for parts intended for aerospace use and machined from polychlorotrifluoroethylene (PCTFE) homopolymers. This specification, however, does not cover parts machined from PCTFE copolymer, PCTFE film or tape, or modified PCTFE. Material covered by this specification is on four types, differentiated based on intended uses and exposures: Types I (high service pressure) and II (low service pressure) for use in air and oxygen media, Type II for use in inert and reactive media, and Type IV for use in other media. The parts shall be manufactured from virgin, unplasticized, pure PCTFE homopolymer, and the use of recycled polymer or regrind shall be prohibited. The base material shall be free of defects and contaminants. The finished parts shall be white or gray in color with a natural translucent appearance, and shall be free of voids, scratches, fissures, inclusions, or entrapped air bubbles. Tests for specific gravity, melting point, tensile strength and elongation, deformation under load, zero strength time, mechanical impact (in ambient liquid oxygen and pressurized liquid and gaseous oxygen environments), and dimensional stability shall be performed and shall conform to the requirements specified.
SCOPE
1.1 This specification is intended to be a means of calling out finished machined parts ready for aerospace use. Such parts may also find use in selected commercial applications where there are clear benefits derived from the use of parts with high molecular weight, good molecular weight retention during processing, dimensional stability, controlled crystallinity, and tightly controlled engineering tolerances.
1.2 This specification establishes requirements for parts machined from virgin, unplasticized, 100 % polychlorotrifluoroethylene (PCTFE) homopolymers.
1.3 This specification does not cover parts machined from PCTFE copolymers, PCTFE film or tape less than 0.25-mm (0.010-in.) thick, or modified PCTFE (containing pigments or plasticizers).
1.4 This specification does not allow parts containing recycled material.
1.5 The specification does not cover PCTFE parts intended for general use applications, in which control of dimensional stability, molecular weight, and crystallinity are not as important. For machined PCTFE parts intended for general use, use Specification D7211.
1.6 This specification classifies parts into three classes based upon intended uses and exposures: oxygen-containing media, reactive media, and inert media.
1.7 Application—PCTFE components covered by this specification are virgin, 100 % PCTFE resin, free of plasticizers and other additives. The components are combustion resistant in oxygen, dimensionally stable, and meet other specific physical characteristics appropriate for their end use. They are used in valves, regulators, and other devices in oxygen, air, helium, nitrogen, hydrogen, ammonia, and other aerospace media systems. The components typically are used as valve seats, o-rings, seals, and gaskets. They are removed and replaced during normal maintenance procedures. The components provide reliable sealing surfaces resulting in proper closure of valves and related devices and no leakage from the system into the environment. They will experience static mechanical loading, cyclic mechanical loading, temperatures ranging from cryogenic to 71°C (160°F), and pressures up to 68.9 MPa (10,000, psig) for oxygen and air media, and 103.4 MPa (15,000 psig) for inert media.
1.8 The values stated in SI units are to be regarded as standard. The values in parentheses are for information only.
1.9 The following precautionary caveat pertains only to the test methods portion, Section 13, of this specification: This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental pra...
- Technical specification7 pagesEnglish language
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.
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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.
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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.
- Standard14 pagesEnglish languagesale 15% off
ABSTRACT
This specification provides minimum requirements for the control, indication, and operational characteristics of propulsion systems. It was developed based on propulsion system installed on aeroplanes, but may be applicable to other applications. The applicant for a design approval must seek the individual guidance to their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
SCOPE
1.1 This specification covers minimum requirements for the control, indication, and operational characteristics of propulsion systems. It was developed based on propulsion system installed on aeroplanes, but may be applicable to other applications as well.
1.2 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their Aeroplane Airworthiness regulations (Hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links. Annex A1 maps the Means of Compliance described in this specification to EASA CS-23, amendment 5, or later, and FAA 14 CFR Part 23, amendment 64, or later.
1.3 Units—The values stated are SI units followed by imperial units in brackets. The values stated in each system are not necessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be used independently of the other, and values from the two systems shall not be combined.
1.4 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.
1.5 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
- Technical specification12 pagesEnglish language
- Technical specification12 pagesEnglish language
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.
- Standard48 pagesEnglish languagesale 15% off
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.
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