| Name |
Description |
Abstract |
Status |
Publication date |
Edition |
Number of pages |
Technical committee |
ICS |
| ISO 15390:2004 |
Space environment (natural and artificial) — Galactic cosmic ray model |
ISO 15390:2004 specifies a model for estimating the radiation impact of galactic cosmic rays (GCR) on hardware and on biological and other objects when in space. ISO 15390:2004 can also be used in scientific research to generalize the available experimental evidence for GCR fluxes. ISO 15390:2004 establishes the model parameters and characteristics of variations in the 101 MeV to 105 MeV GCR particles (electrons, protons, and Z = 2 to 92 nuclei in the near-Earth space beyond the Earth's magnetosphere).
|
Published |
2004-06 |
Edition : 1 |
Number of pages : 6 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15395:1998 |
Space data and information transfer systems — Standard formatted data units — Control authority data structures |
|
Published |
1998-05 |
Edition : 1 |
Number of pages : 19 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15396:1998 |
Space data and information transfer systems — Cross support reference model — Space link extension services |
|
Withdrawn |
1998-04 |
Edition : 1 |
Number of pages : 93 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15396:2007 |
Space data and information transfer systems — Cross support reference model — Space link extension services |
ISO 15396:2007 defines a cross-support reference model which provides a common basis for coordinating the development of CCSDS Recommended Standards for space link extension (SLE) service specifications and serves as a reference to maintain the consistency of these Recommended Standards.
|
Published |
2007-04 |
Edition : 2 |
Number of pages : 102 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15856:2010 |
Space systems — Space environment — Simulation guidelines for radiation exposure of non-metallic materials |
ISO 15856:2009 is the first part of a series on space environment simulation for on-ground tests of materials used in space. This International Standard covers the testing of non-metallic materials exposed to simulated space radiation. Non-metallic materials include glasses, ceramics and polymer-metal composite materials such as metal matrix composites and laminated materials. ISO 15856:2009 does not cover semiconductor materials used for electronic components. The types of simulated radiation include charged particles (electrons and protons), solar ultraviolet radiation and soft X-radiation of solar flares. Synergistic interactions of the radiation environment are covered only for these natural, and some induced, environmental effects.
ISO 15856:2009 outlines the recommended methodology and practices for the simulation of space radiation effects on materials. Simulation methods are used to reproduce the effects of the space radiation environment on materials that are located on surfaces of space vehicles and behind shielding.
|
Published |
2010-08 |
Edition : 1 |
Number of pages : 24 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15859-1:2004 |
Space systems — Fluid characteristics, sampling and test methods — Part 1: Oxygen |
ISO 15859-1:2004 specifies the limit values for the composition of oxygen and establishes the sampling and test requirements applicable for the verification of the oxygen composition.
ISO 15859-1:2004 is applicable to oxygen used in both flight hardware and ground facilities, systems and equipment, of the following types and grades: Type I, gaseous (Grade A: standard, purging/pressurization, Grade CB: crew breathing, Grade F: fuel-cell) and Type II, liquid (Grade A: oxidize, Grade B: oxidizer, Grade F: fuel-cell).
ISO 15859-1:2004 is applicable to influents only to the extent specified herein.
ISO 15859-1:2004 is applicable to any sampling operation required to ensure that, when the fluid enters the launch vehicle or spacecraft, the fluid composition complies with the limits provided hereafter or with any technical specification agreed for a particular use.
|
Published |
2004-06 |
Edition : 1 |
Number of pages : 9 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15859-2:2004 |
Space systems — Fluid characteristics, sampling and test methods — Part 2: Hydrogen |
ISO 15859-2:2004 specifies limits for the composition of hydrogen and establishes the sampling and test requirements applicable for the verification of the hydrogen composition.
ISO 15859-2:2004 is applicable to hydrogen used in both flight hardware and ground facilities, systems and equipment, of the following types and grades: Type I, gaseous (Grade A: fuel, Grade F: fuel) and Type II, liquid (Grade A: fuel, Grade F: fuel).
ISO 15859-2:2004 is applicable to influents only to the extent specified.
ISO 15859-2:2004 is applicable to any sampling operation required to ensure that, when the fluid enters the launch vehicle or spacecraft, the fluid composition complies with the limits provided hereafter or with any technical specification agreed to for a particular use.
|
Published |
2004-06 |
Edition : 1 |
Number of pages : 8 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 22538-3:2007 |
Space systems — Oxygen safety — Part 3: Selection of non-metallic materials for oxygen systems and components |
ISO 22538-3:2007 describes a process for the selection of non-metallic materials for oxygen systems and their components. ISO 22538-3:2007 applies equally to ground support equipment, launch vehicles and spacecraft.
|
Published |
2007-09 |
Edition : 1 |
Number of pages : 11 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15859-3:2004 |
Space systems — Fluid characteristics, sampling and test methods — Part 3: Nitrogen |
ISO 15859-3:2004 specifies limits for the composition of nitrogen and establishes the sampling and test requirements applicable for the verification of nitrogen composition.
ISO 15859-3:2004 is applicable to nitrogen, used in both flight hardware and ground facilities, systems and equipment, of the following types and grades of nitrogen: Type I, gaseous (Grade A: purging/pressurizing, Grade B: crew breathing, Grade C, Grade F, Grade J) and Type II, liquid (Grade A: purging/pressurizing, Grade B: crew breathing, Grade C, Grade F).
ISO 15859-3:2004 is applicable to influents only within the specified limits.
ISO 15859-3:2004 is applicable to any sampling operation required to ensure that, when the fluid enters the launch vehicle or spacecraft, the fluid composition complies with the limits provided hereafter or with any technical specification agreed to for a particular use.
|
Published |
2004-06 |
Edition : 1 |
Number of pages : 10 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15859-4:2004 |
Space systems — Fluid characteristics, sampling and test methods — Part 4: Helium |
ISO 15859-4:2004 specifies limits for the composition of helium and establishes the sampling and test requirements applicable for the verification of the helium composition.
ISO 15859-4:2004 is applicable to helium, used in both flight hardware and ground facilities, systems and equipment, of the following types and grades:Type I, gaseous (Grade A: purging and pressurizing helium, Grade F: purging and pressurizing helium, Grade J: purging and pressurizing helium) and Type II, liquid (Grade A: purging and pressurizing helium, Grade F: purging and pressurizing helium).
ISO 15859-4:2004 is applicable to influents only within the specified limits.
ISO 15859-4:2004 is applicable to any sampling operation required to ensure that, when the fluid enters the launch vehicle or spacecraft, the fluid composition complies with the limits provided hereafter or with any technical specification agreed to for a particular use.
|
Published |
2004-06 |
Edition : 1 |
Number of pages : 8 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15859-5:2004 |
Space systems — Fluid characteristics, sampling and test methods — Part 5: Nitrogen tetroxide propellants |
ISO 15859-5:2004 specifies limits for the chemical composition and physical properties of nitrogen tetroxide (N2O4)-based propellants and establishes the sampling and test requirements applicable for the verification of the nitrogen tetroxide composition.
ISO 15859-5:2004 is applicable to N2O4-based propellants, used as oxidizers in propellant systems of space systems as well as in both flight hardware and ground facilities, systems, and equipment, of types NTO (N2O4 with red-brown colour), MON-1 (N2O4 and NO with green colour), MON-3 (N2O4 and NO with green colour), MON-10 (N2O4 and NO with green colour) and MON-25 (N2O4 and NO with green colour) as well as grades standard (no iron requirement) and low-iron (0,5 microgram per gram or 1,0 microgram per gram iron maximum).
ISO 15859-5:2004 is applicable to influents only within the specified limits herein.
ISO 15859-5:2004 is applicable to any sampling operation required to ensure that, when the fluid enters the launch vehicle or spacecraft, the fluid composition complies with the limits provided hereafter or with any technical specification agreed to for a particular use.
|
Published |
2004-06 |
Edition : 1 |
Number of pages : 6 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15859-6:2004 |
Space systems — Fluid characteristics, sampling and test methods — Part 6: Monomethylhydrazine propellant |
ISO 15859-6:2004 specifies limits for the composition of monomethylhydrazine and establishes the sampling and test requirements applicable for the verification of the monomethylhydrazine (MMH) composition.
ISO 15859-6:2004 is applicable to monomethylhydrazine propellant, used as a fuel in propellant systems of space systems as well as in both flight hardware and ground facilities, systems, and equipment, of Grade A (98,0 % pure) and Grade F (98,5 % pure).
ISO 15859-6:2004 is applicable to influents only within the specified limits herein.
ISO 15859-6:2004 is applicable to any sampling operation required to ensure that, when the fluid enters the launch vehicle or spacecraft, the fluid composition complies with the limits provided hereafter or with any technical specification agreed to for a particular use.
|
Published |
2004-06 |
Edition : 1 |
Number of pages : 6 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15859-7:2004 |
Space systems — Fluid characteristics, sampling and test methods — Part 7: Hydrazine propellant |
ISO 15859-7:2004 specifies limits for the composition and physical properties of anhydrous hydrazine (N2H4) and establishes the sampling and test requirements applicable for the verification of the anhydrous hydrazine composition.
ISO 15859-7:2004 is applicable to anhydrous hydrazine propellant, intended for use as fuel in propellant systems of space systems as well as in both flight hardware and ground facilities, systems, and equipment, of grades: standard [normal production and quality control (suitable for most uses)], monopropellant [normal product with strict control of specified impurities (to be specified only for monopropellant catalytic engines where extended life of the catalyst is desired)] and high purity (special production with strict control of specified impurities).
ISO 15859-7:2004 is applicable to influents only within the specified limits herein. Hydrazine may be of the liquid type.
ISO 15859-7:2004 is applicable to any sampling operation required to ensure that, when the fluid enters the launch vehicle or spacecraft, the fluid composition complies with the limits provided hereafter or with any technical specification agreed to for a particular use.
|
Published |
2004-06 |
Edition : 1 |
Number of pages : 7 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 17433:2003 |
Space data and information transfer systems — Packet telemetry services |
ISO 17433:2003 specifies the requirements for packet telemetry services in space data and information transfer systems. The purpose of this document is to establish common requirements for the services provided between protocol layers of the space to ground link. It does not define the extension of these services across distributed components of the spacecraft or ground data systems.
|
Withdrawn |
2003-02 |
Edition : 2 |
Number of pages : 83 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15859-8:2004 |
Space systems — Fluid characteristics, sampling and test methods — Part 8: Kerosine propellant |
ISO 15859-8:2004 specifies limits for the composition of kerosine and establishes the sampling and test requirements applicable for the verification of the kerosine composition.
ISO 15859-8:2004 is applicable to kerosine propellants sampling and test methods for used in both flight hardware and ground support facilities, systems, and equipment.
ISO 15859-8:2004 may be applied to influent or effluent kerosine.
ISO 15859-8:2004 is applicable to any sampling operation required to ensure that, when the fluid enters the launch vehicle or spacecraft, the fluid composition complies with the limits provided hereafter or with any technical specification agreed to for a particular use.
|
Published |
2004-06 |
Edition : 1 |
Number of pages : 8 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15859-9:2004 |
Space systems — Fluid characteristics, sampling and test methods — Part 9: Argon |
ISO 15859-9:2004 specifies limits for the composition of argon (Ar) and establishes the sampling and test requirements applicable for the verification of the argon (Ar) composition.
ISO 15859-9:2004 is applicable to argon, used for purging and pressurization of space systems as well as in both flight hardware and ground facilities, systems, and equipment, of Type I (gaseous) and Type II (liquid)
ISO 15859-9:2004 is applicable to influents only within the specified limits herein.
ISO 15859-9:2004 is applicable to any sampling operation required to ensure that, when the fluid enters the launch vehicle or spacecraft, the fluid composition complies with the limits provided hereafter or with any technical specification agreed to for a particular use.
|
Published |
2004-06 |
Edition : 1 |
Number of pages : 7 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15859-10:2004 |
Space systems — Fluid characteristics, sampling and test methods — Part 10: Water |
ISO 15859-10:2004 specifies limits for the composition of water and establishes the sampling and test requirements applicable for the verification of the water composition.
ISO 15859-10:2004 is applicable to only potable water and high-purity demineralized or deionized water, used for cooling and servicing of space systems as well as both flight hardware and ground servicing, system, and equipment, of Type HP (high purity) and Type P [potable (drinking)].
It is not applicable to other types of water that may be provided to a space system. ISO 15859-10:2004 is applicable to influents only within the specified limits herein.
ISO 15859-10:2004 is applicable to any sampling operation required to ensure that, when the fluid enters the launch vehicle or spacecraft, the fluid composition complies with the limits provided hereafter or with any technical specification agreed to for a particular use.
|
Published |
2004-06 |
Edition : 1 |
Number of pages : 9 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15859-11:2004 |
Space systems — Fluid characteristics, sampling and test methods — Part 11: Ammonia |
ISO 15859-11:2004 specifies limits for the composition of ammonia (NH3) and establishes the sampling and test requirements applicable for the verification of the ammonia composition.
ISO 15859-11:2004 is applicable to sampling and test methods for ammonia used in both flight hardware and ground support facilities, systems, and equipment. ISO 15859-11:2004 is applicable to ammonia influents only within the specified limits herein.
ISO 15859-11:2004 is applicable to any sampling operation required to ensure that, when the fluid enters the launch vehicle or spacecraft, the fluid composition complies with the limits provided hereafter or with any technical specification agreed to for a particular use.
|
Published |
2004-06 |
Edition : 1 |
Number of pages : 5 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15859-12:2004 |
Space systems — Fluid characteristics, sampling and test methods — Part 12: Carbon dioxide |
ISO 15859-12:2004 specifies limits for the composition of carbon dioxide (CO2) and establishes the sampling and test requirements applicable for the verification of the carbon dioxide composition.
ISO 15859-12:2004 is applicable to composition, sampling, and test methods for carbon dioxide intended for purging and pressurization in both space systems flight hardware and ground support facilities, systems, and equipment. ISO 15859-12:2004 may be applied to carbon dioxide influents. Carbon dioxide may be of the gaseous or liquid type.
ISO 15859-12:2004 is applicable to any sampling operation required to ensure that, when the fluid enters the launch vehicle or spacecraft, the fluid composition complies with the limits provided hereafter or with any technical specification agreed to for a particular use.
|
Published |
2004-06 |
Edition : 1 |
Number of pages : 4 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15859-13:2004 |
Space systems — Fluid characteristics, sampling and test methods — Part 13: Breathing air |
ISO 15859-13:2004 specifies limits for the composition of breathing air and establishes the sampling and test requirements applicable for the verification of the breathing air composition.
ISO 15859-13:2004 is applicable to sampling and test methods for breathing air intended for purging and pressurization of space systems as well as flight hardware and ground support facilities, systems, and equipment. ISO 15859-13:2004 may be applied to influent breathing air.
ISO 15859-13:2004 is applicable to any sampling operation required to ensure that, when the fluid enters the launch vehicle or spacecraft, the fluid composition complies with the limits provided hereafter or with any technical specification agreed to for a particular use.
|
Published |
2004-06 |
Edition : 1 |
Number of pages : 7 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 22538-4:2007 |
Space systems — Oxygen safety — Part 4: Hazards analyses for oxygen systems and components |
ISO 22538-4:2007 provides a process for conducting hazards analyses on parts, components and systems in oxygen and oxygen-enriched environments. ISO 22538-4:2007 identifies processes that may be used on ground support equipment, launch vehicles and spacecraft.
|
Published |
2007-09 |
Edition : 1 |
Number of pages : 9 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15860:2006 |
Space systems — Gas contamination — Measurement methods for field tests |
ISO 15860:2006 covers gases (air, nitrogen, helium, and argon) compressed up to 40 MPa used in systems and units of space vehicle launch and technical complexes.
ISO 15860:2006 determines compressed gas impurities (mechanical impurities, water vapour, oil, and foreign gases) content measurement methods. It can be used by countries and firms participating in the development, redesign, modernization, and maintenance of space vehicle launch sites and technical complexes.
|
Published |
2006-08 |
Edition : 1 |
Number of pages : 14 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15862:2009 |
Space systems — Launch-vehicle-to-spacecraft flight environments telemetry data processing |
ISO 15862:2009 provides basic requirements for the measurement of the spacecraft flight environments generated by the launch vehicle, telemetry data processing and formats of analysis reports.
ISO 15862:2009 defines the field and number of measurement parameters, the principles of data processing, the format of delivered data and the content and the form of the flight environment analysis report.
Flight telemetry data are used to verify if flight environment conditions exceed pre-flight analyses and environmental test results. In the event of a launch failure, adequate flight environment data can assist in investigating and analysing failure causes.
ISO 15862:2009 is applicable to commercial launch vehicles and related ground processing, no matter which launch vehicle agencies are selected.
|
Published |
2009-02 |
Edition : 1 |
Number of pages : 9 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15863:2003 |
Space systems — Spacecraft-to-launch-vehicle interface control document |
The purpose of ISO 15863:2003 is to provide spacecraft (SC) and launch vehicle (LV) organizations with the general format for presenting the interface control document (ICD) that verifies and controls the compatibility between SC and LV for a dedicated mission. ISO 15863:2003 addresses the definition of the mission, the compatibility of the SC with the LV environment, including all mechanical, electrical, radio frequency, and electromagnetic aspects related to SC to LV and SC to launch range interfaces, verification analyses and tests for the induced environment, and the necessary facilities and support for launch range operations.
|
Published |
2003-11 |
Edition : 1 |
Number of pages : 28 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15864:2004 |
Space systems — General test methods for space craft, subsystems and units |
ISO 15864:2004 provides the baseline standard on the subject of testing at the system, subsystem, and unit level for applicable unmanned spacecraft programs. It also provides the requirements for documentation associated with testing activities.
The acceptance criteria, specifications or procedures, and other detail test requirements applicable to a particular program are defined in the applicable technical specifications and statement of work. When requirements have to be verified by measuring product performance and function under various simulated environments, the method is referred to as "Test." The requirements of ISO 15864:2004 may be tailored for each specific space program application.
|
Withdrawn |
2004-08 |
Edition : 1 |
Number of pages : 30 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15864:2021 |
Space systems — General test methods for spacecraft, subsystems and units |
This document provides the baseline standard on the subject of testing at the system, subsystem and unit levels for applicable unmanned spacecraft programmes. It also provides the requirements for documentation associated with testing activities.
This document contains provisions for qualification and acceptance testing, or proto-flight testing (PFT). It assumes that hardware development is complete.
|
Published |
2021-07 |
Edition : 2 |
Number of pages : 34 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15865:2005 |
Space systems — Qualification assessment |
ISO 15865:2005 establishes common rules for assessing the qualification of space systems and products used in space systems against their functional and technical specifications. It establishes a basis for determining system or product readiness for any stage of the life cycle. This includes, for example, readiness for development, manufacture, test, operation, modification, or disposal.
ISO 15865:2005 is applicable to systems and products used in flight or ground support and to products at all levels in a product tree. It applies to systems and products consisting of hardware, software, facilities, materials, methods, processes, procedures or any combination of these.
It establishes common rules for assessment of item readiness and approaches to qualification.
ISO 15865:2005 is intended for use as the basis for a design justification plan. It is intended to be used either in establishing an agreement for such a plan between a customer and a supplier or as the basis for a supplier's internal qualification practices.
|
Withdrawn |
2005-03 |
Edition : 1 |
Number of pages : 21 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15865:2022 |
Space systems — Qualification assessment |
This document establishes general rules for qualification assessment of space systems and products used in space systems against their functional and technical specifications. It establishes general requirements for determining system or product readiness for any stage of the life cycle. This includes, for example, readiness for development, manufacture, test, operation, modification, or disposal.
This document is applicable to systems and products used in flight or ground support and to products at all levels in a product tree. It applies to systems and products consisting of hardware, software, facilities, materials, methods, processes, procedures or any combination of these.
It establishes common:
a) general requirements for qualification assessment of item readiness;
b) approaches to qualification.
This document is intended for use as the basis for a design justification plan. It is intended to be used either in establishing an agreement for such a plan between a customer and a supplier or as the basis for a supplier’s internal qualification practices.
|
Published |
2022-10 |
Edition : 2 |
Number of pages : 21 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15887:2013 |
Space data and information transfer systems — Lossless data compression |
ISO 15887:2013 establishes a source-coding data-compression algorithm applied to digital data and specifies how these compressed data shall be inserted into source packets for retrieval and decoding.
Source coding for data compression is a method utilized in data systems to reduce the volume of digital data to achieve benefits in areas including, but not limited to:
reduction of transmission channel bandwidth;
reduction of the buffering and storage requirement;
reduction of data-transmission time at a given rate.
The characteristics of source codes are specified only to the extent necessary to ensure multi-mission support capabilities. ISO 15887:2013 does not attempt to quantify the relative bandwidth reduction, the merits of each approach discussed, or the design requirements for coders and associated decoders. Some performance information is included in CCSDS 120.0-G-2.
ISO 15887:2013 addresses only Lossless source coding, which is applicable to a wide range of digital data, both imaging and non-imaging, where the requirement is for a moderate data-rate reduction constrained to allow no distortion to be added in the data compression/decompression process. The decompression process is not addressed.
|
Published |
2013-06 |
Edition : 2 |
Number of pages : 41 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15888:2000 |
Space data and information transfer systems — Standard formatted data units — Referencing environment |
This International Standard specifies the requirements for referencing environments for standard formatted data
units for space data and information transfer systems.
|
Published |
2000-10 |
Edition : 1 |
Number of pages : 47 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15889:2000 |
Space data and information transfer systems — Data description language — EAST specification |
|
Withdrawn |
2000-10 |
Edition : 1 |
Number of pages : 105 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15889:2003 |
Space data and information transfer systems — Data description language — EAST specification |
ISO 15889:2003 specifies the requirements for the Enhanced Ada SubseT (EAST) language (CCSDS 0010) used to create descriptions of data, called data description records (DDRs). The use of this language ensures complete and exact understanding of space data as well as its automated transfer and interpretation on any host machine having the appropriate software tools.
|
Withdrawn |
2003-02 |
Edition : 2 |
Number of pages : 115 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15889:2011 |
Space data and information transfer systems — The data description language EAST specification |
ISO 15889:2011 defines the Enhanced Ada SubseT (EAST) language used to create descriptions of data called Data Description Records (DDRs). Such DDRs ensure a complete and exact understanding of the data and allow it to be interpreted in an automated fashion. This means that a software tool is able to analyse a DDR and interpret the format of the associated data. This allows the software to extract values from the data on any host machine (i.e. on a different machine from the one that produced the data).
|
Published |
2011-10 |
Edition : 3 |
Number of pages : 123 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15891:2000 |
Space data and information transfer systems — Protocol specification for space communications — Network protocol |
|
Withdrawn |
2000-09 |
Edition : 1 |
Number of pages : 116 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15892:2000 |
Space data and information transfer systems — Protocol specification for space communications — Security protocol |
|
Withdrawn |
2000-09 |
Edition : 1 |
Number of pages : 59 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15893:2000 |
Space data and information transfer systems — Protocol specification for space communications — Transport protocol |
|
Withdrawn |
2000-09 |
Edition : 1 |
Number of pages : 121 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15893:2010 |
Space data and information transfer systems — Space communications protocol specification (SCPS) — Transport protocol (SCPS-TP) |
ISO 15893:2010 specifies the requirements for the services and protocols of the space communications protocol specification (SCPS) transport service. These requirements are meant to allow independent implementations of this protocol in space and ground segments of the SCPS network to interoperate.
ISO 15893:2010 is applicable to any kind of space mission or infrastructure, regardless of complexity.
|
Published |
2010-09 |
Edition : 2 |
Number of pages : 109 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 15894:2000 |
Space data and information transfer systems — Protocol specification for space communications — File protocol |
|
Withdrawn |
2000-09 |
Edition : 1 |
Number of pages : 92 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18439:2013 |
Space data and information transfer systems — Space Communication Cross Support — Service Management — Service Specification |
ISO 18439:2013 defines a set of Space Communication Cross Support Service Management (SCCS-SM) services by which space link service providers and space missions exchange information needed to arrange spacecraft contact periods and establish the operating parameters of the space link services and cross support transfer services during those contact periods.
|
Withdrawn |
2013-06 |
Edition : 1 |
Number of pages : 498 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 16091:2002 |
Space systems — Integrated logistic support |
ISO 16091:2002 describes the set of management requirements needed to identify and provide logistic support, so the customer can operate and maintain a product in its operational environment for the expected lifetime.
These requirements also aim, throughout the product life cycle, at implementing everything pertinent to the control of the risks considered as critical regarding the operational objectives.
The management requirements are applicable to those activities necessary to design, develop, deliver, deploy and manage an organized and structured set of materials and software, services, processes and information dedicated to support the system throughout its life cycle.
ISO 16091:2002 specifies management, studies, production activities, information management processes and tasks to meet the customer's need for logistic support.
When viewed from the perspective of a specific programme or project context, the requirements defined in ISO 16091:2002 should be tailored to match the genuine requirements of a particular profile and circumstances of a programme or project.
|
Withdrawn |
2002-12 |
Edition : 1 |
Number of pages : 22 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 16091:2018 |
Space systems — Integrated logistic support |
This document describes the set of management requirements needed to identify and provide logistic support, so the customer can operate and maintain a product in its operational environment for the expected lifetime.
These requirements also aim, throughout the product life cycle, at implementing everything pertinent to the control of risks considered as critical for operational objectives.
The management requirements are applicable to those activities necessary to design, develop, deliver, deploy and manage an organized and structured set of materials and software, services, processes and information dedicated to support the system throughout its life cycle.
This document specifies management, studies, production activities, information management processes and tasks to meet the customer's need for logistic support.
When viewed from the perspective of a specific project context, the requirements defined in this document are tailored to match the genuine requirements of a particular profile and circumstances of a project.
NOTE Tailoring is the process by which individual requirements of specifications, standards and related documents are evaluated, and made applicable to a specific project by selection, and in some exceptional cases, modification of existing or addition of new requirements.
|
Published |
2018-09 |
Edition : 2 |
Number of pages : 23 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 16126:2014 |
Space systems — Assessment of survivability of unmanned spacecraft against space debris and meteoroid impacts to ensure successful post-mission disposal |
ISO 16126:2014 defines requirements and a procedure for assessing the survivability of an unmanned spacecraft against space debris and meteoroid impacts to ensure the survival of critical components required to perform post-mission disposal. ISO 16126:2014 also describes two impact risk analysis procedures that can be used to satisfy the requirements.
ISO 16126:2014 is part of a set of International Standards that collectively aim to reduce the growth of space debris by ensuring that spacecraft are designed, operated, and disposed of in a manner that prevents them from generating debris throughout their orbital lifetime.
|
Published |
2014-04 |
Edition : 1 |
Number of pages : 19 |
Technical Committee |
49.140
Space systems and operations
|
| ISO/DIS 16126 |
Space systems — Survivability of unmanned spacecraft against space debris and meteoroid impacts for the purpose of space debris mitigation |
|
Under development |
|
Edition : 2 |
Number of pages : 61 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 16127:2014 |
Space systems — Prevention of break-up of unmanned spacecraft |
ISO 16127:2014 defines the requirements to reduce the risk of in-orbit break-up of unmanned spacecraft, both during and after their operational lives. The aim would be met by reducing the possibility of a break-up caused by an unplanned internally caused event and by depleting to a safe level all the sources of stored energy at the end of a spacecraft's life. ISO 16127:2014 is designed for use in planning, verifying and implementing the prevention of break-up of a spacecraft.
ISO 16127:2014 applies only to unmanned spacecraft operating in Earth orbit.
|
Withdrawn |
2014-02 |
Edition : 1 |
Number of pages : 9 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 16157:2018 |
Space systems — Human-life activity support systems and equipment integration in space flight — Techno-medical requirements for space vehicle human habitation environments |
This document is a second level standard is one of the several others regarding human-life activity support systems and equipment integration in space flight.
This document, along with first and third level standards, form a complex three-level international standard entitled "Space systems — Human-life activity support systems and equipment integration in space flight".
It is applicable to human space flight programs in all manned space objects, including spacecraft, space stations, lunar and planetary bases, as well as extravehicular activity. It covers all phases for developing a manned space object, such as design, production, tests, operation, and maintenance.
|
Published |
2018-06 |
Edition : 1 |
Number of pages : 7 |
Technical Committee |
49.140
Space systems and operations
|
| ISO/TR 16158:2013 |
Space systems — Avoiding collisions with orbiting objects |
ISO/TR 16158:2013 is a guide for establishing essential collaborative enterprises to sustain the space environment and employ it effectively. This requires diligent collaboration among all who operate satellites.
ISO/TR 16158:2013 describes some widely used techniques for perceiving close approaches, estimating collision probability, estimating the cumulative probability of survival, and manoeuvring to avoid collisions.
|
Withdrawn |
2013-12 |
Edition : 1 |
Number of pages : 17 |
Technical Committee |
49.140
Space systems and operations
|
| ISO/TR 16158:2021 |
Space systems — Avoiding collisions among orbiting objects |
This document is a guide for establishing essential collaborative enterprises to sustain the space environment and employ it effectively.
This document describes some widely used techniques for perceiving close approaches, estimating collision probability, estimating the cumulative probability of survival, and manoeuvring to avoid collisions.
NOTE Satellite operators accept that all conjunction and collision assessment techniques are statistical. All suffer false positives and/or missed detections. The degree of uncertainty in the estimated outcomes is not uniform across all satellite orbits or all assessment intervals. No comparison within a feasible number of test cases can reveal the set of techniques that is uniformly most appropriate for all.
|
Published |
2021-10 |
Edition : 2 |
Number of pages : 31 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 16159:2012 |
Space systems — Launch pad and integration site — Facility, system and equipment failure analysis |
ISO 16159:2012 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.
The purpose of ISO 16159:2012 is to provide
rules for investigating, analysing and identifying the causes of failures,
sufficient information so that corrective action may be implemented to prevent failure recurrence, and
a uniform method for maintaining records of the findings of all failure causes so as to provide information for other failure investigations.
|
Published |
2012-08 |
Edition : 1 |
Number of pages : 8 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 16164:2015 |
Space systems — Disposal of satellites operating in or crossing Low Earth Orbit |
ISO 16164:2015 focuses on the post-mission disposal of spacecraft operating in, or crossing, Low Earth Orbit (LEO). The disposal of orbital launch stages operating in, or crossing, LEO is not dealt with in this International Standard.
Post-mission disposal of an Earth-orbiting spacecraft broadly means removing the spacecraft from its operational orbit after the end of mission, manoeuvring it to a region of space where it is less likely to interfere or collide with other operational spacecraft or with orbital debris and passivating.
For a spacecraft operating in, or crossing LEO, there are six disposal options that might be used to ensure its compliance with orbital debris mitigation requirements (as stated in ISO 24113). In order of preference, these are the following:
a) retrieving it and performing a controlled re-entry to recover it safely on the Earth;
b) manoeuvring it in a controlled manner into a targeted re-entry with a well-defined impact footprint on the surface of the Earth to limit the possibility of human casualty;
c) manoeuvring it in a controlled manner to an orbit that has a decay lifetime short enough to meet all orbital debris mitigation requirements;
d) augmenting its orbital decay by deploying a device so that the remaining orbital lifetime is short enough to meet all orbital debris mitigation requirements;
e) allowing its orbit to decay naturally, given that all orbital debris mitigation requirements will be met without the need for a disposal manoeuvre or other action;
f) manoeuvring it in a controlled manner to an orbit with a perigee altitude sufficiently above the LEO protected region (i.e. a graveyard orbit) that long-term perturbation forces do not cause it to re-enter the LEO protected region within 100 years.
ISO 16164:2015 specifies requirements for the following:
a) planning for disposal and passivation of spacecraft operating in LEO to ensure that final disposal is sufficiently characterized and that adequate propellant will be reserved for any propulsive manoeuvre required,
b) selecting a disposal orbit where the spacecraft will re-enter the Earth's atmosphere within the next 25-years, or where the spacecraft will not re-enter the protected region within the next 100-years, and
c) estimating, prior to launch, a 90 % or better probability of successfully executing the disposal manoeuvre.
Techniques for planning and executing space hardware disposal are provided that reflect current internationally accepted guidelines and consider current operational procedures and best practices.
|
Withdrawn |
2015-07 |
Edition : 1 |
Number of pages : 11 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 16192:2010 |
Space systems — Experience gained in space projects (Lessons learned) — Principles and guidelines |
ISO 16192:2010 outlines lessons learned principles and guidelines that are applicable in all space project activities (management, technical, quality, cost and schedule).
The application of ISO 16192:2010 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.), and
the interest and usefulness of the related information.
The lessons learned information can result from any situations which might be encountered in similar contexts for future projects, i.e.
undesirable experiences that need to be avoided;
strategies, rules, principles of design, validation, tests and operations that proved to be successful or necessary.
ISO 16192:2010 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 ISO 16192:2010 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 and ISO 17666.
ISO 16192:2010 also provides lessons learned processes and suggested lessons learned forms.
|
Withdrawn |
2010-06 |
Edition : 1 |
Number of pages : 12 |
Technical Committee |
49.020
Aircraft and space vehicles in general
;
49.140
Space systems and operations
|
| ISO 16378:2022 |
Space systems — Measurements of thermo-optical properties of thermal control materials |
This document specifies the multiple measurement methods, instruments, equipment, and samples used to calculate the thermo-optical properties of thermal control materials. This document compares their features, indicates their limitations and biases, and guides the applications. This document also defines requirements for calibration and reference materials to ensure data quality.
This document specifies the following test methods, including the configuration of samples and calculations.
a) Solar absorptance using a spectrophotometer (αs) — Annex A.
b) Solar absorptance using the comparative test method (αp) — Annex B.
c) Hemispherical infrared emittance using the thermal test method (εh-t) — Annex C.
d) Normal infrared emittance using an IR spectrometer (εn-s) — Annex D.
e) Normal infrared emittance using ellipsoid collector optics (εn-e) — Annex E.
f) Normal infrared emittance using two rotating cavities (εn-c) — Annex F.
|
Published |
2022-09 |
Edition : 2 |
Number of pages : 37 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 16192:2017 |
Space systems — Experience gained in space projects (lessons learned) — Principles and guidelines |
ISO 16192:2017 outlines 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 might be encountered in similar contexts for future projects, i.e.:
- undesirable experiences that need to be avoided;
- strategies, rules, principles of design, validation, tests and operations that proved to be successful or necessary.
ISO 16192:2017 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 and ISO 17666.
ISO 16192:2017 also provides lessons learned processes and suggested lessons learned forms.
|
Published |
2017-04 |
Edition : 2 |
Number of pages : 13 |
Technical Committee |
49.020
Aircraft and space vehicles in general
;
49.140
Space systems and operations
|
| ISO/DIS 16192 |
Space systems — Experience gained in space projects (lessons learned) — Principles and guidelines |
ISO 16192:2017 outlines 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 might be encountered in similar contexts for future projects, i.e.:
- undesirable experiences that need to be avoided;
- strategies, rules, principles of design, validation, tests and operations that proved to be successful or necessary.
ISO 16192:2017 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 and ISO 17666.
ISO 16192:2017 also provides lessons learned processes and suggested lessons learned forms.
|
Under development |
|
Edition : 3 |
Number of pages : 13 |
Technical Committee |
49.020
Aircraft and space vehicles in general
;
49.140
Space systems and operations
|
| ISO/CD 16215-1 |
Space systems — Space-based positioning, navigation and timing (PNT) services — Part 1: Architectural basis |
This document specifies architectural basis of space-based positioning, navigation and timing (PNT) services for civil land, maritime and aerial applications using a global navigation satellite system (GNSS).
|
Under development |
|
Edition : 1 |
|
Technical Committee |
49.140
Space systems and operations
|
| ISO 16290:2013 |
Space systems — Definition of the Technology Readiness Levels (TRLs) and their criteria of assessment |
ISO 16290:2013 defines Technology Readiness Levels (TRLs). It is applicable primarily to space system hardware, although the definitions could be used in a wider domain in many cases.
The definition of the TRLs provides the conditions to be met at each level, enabling accurate TRL assessment.
|
Published |
2013-11 |
Edition : 1 |
Number of pages : 12 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 16363:2012 |
Space data and information transfer systems — Audit and certification of trustworthy digital repositories |
ISO 16363:2012 defines a recommended practice for assessing the trustworthiness of digital repositories. It is applicable to the entire range of digital repositories. ISO 16363:2012 can be used as a basis for certification.
|
Published |
2012-02 |
Edition : 1 |
Number of pages : 70 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 16378:2013 |
Space systems — Measurements of thermo-optical properties of thermal control materials |
ISO 16378:2013 specifies the multiple measurement methods, instruments, equipment, and samples used to calculate the thermo-optical properties of thermal control materials. It compares their features, indicates their limitations and biases, and guides the applications. These measurements will be performed at ground test facilities with the purpose of obtaining material properties. The measured properties will be used for material selection, thermal design of spacecraft, process control, quality control, etc. Also, on-orbit temperature data in the beginning of life can be assessed using the data obtained by ground measurement. Requirements for calibration and reference materials to ensure data quality are also defined.
The following test methods are detailed in the annexes of ISO 16378:2013 including the configuration of samples and calculations:
Solar absorptance using a spectrophotometer: (αs);
Solar absorptance using the comparative test method: (αp);
Hemispherical infrared emittance using the thermal test method: (εh-t);
Normal infrared emittance using an IR spectrometer: (εn-s);
Normal infrared emittance using ellipsoid collector optics (εn-e);
Normal infrared emittance using two rotating cavities: (εn-c).
|
Withdrawn |
2013-12 |
Edition : 1 |
Number of pages : 36 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 16404:2013 |
Space systems — Programme management — Requirements management |
ISO 16404:2013 presents the requirements for Requirements Management (RM) for space projects.
ISO 16404:2013 addresses the space programme/project management requirements, applicable through a top-down approach in a contractual relationship between customers and suppliers.
The objective of ISO 16404:2013 is to state and establish a common reference framework for all the customers and suppliers in the space sector to deploy Requirements Management for all space products and projects.
ISO 16404:2013 on Requirements Management includes
? a definition of the Requirements Management scope for the space sector,
? the standard processes for Requirements Management within the product lifecycle management, and
? a set of rules for Requirements Management activities to be implemented by the actors (customers and suppliers), including rules derived from best practices.
|
Withdrawn |
2013-11 |
Edition : 1 |
Number of pages : 16 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 16404:2020 |
Space systems — Programme management — Requirements management |
This document presents the requirements for requirements management (RM) for space projects.
This document addresses the space programme/project management requirements, applicable through a top-down approach in a contractual relationship between customers and suppliers.
The objective of this document is to state and establish a common reference framework for all the customers and suppliers in the space sector to deploy requirements management for all space products and projects.
This document on requirements management includes
— a definition of the requirements management scope for the space sector,
— the standard processes for requirements management within the product lifecycle management, and
— a set of rules for requirements management activities to be implemented by the actors (customers and suppliers), including rules derived from best practices.
The primary target audience for this document includes
— the requirements management/systems engineering process owners of the customers and suppliers,
— the programme/project managers managing the space programmes, and
— the chief engineers and the quality managers.
The term "programme" is understood as a group of several projects. Both "programme" and "project" can be used in the same context throughout this document.
In addition, this document allows customer/supplier flexibility in its implementation and tailoring.
|
Published |
2020-05 |
Edition : 2 |
Number of pages : 15 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 16454:2007 |
Space systems — Structural design — Stress analysis requirements |
ISO 16454:2007 is intended to be used for the determination of the stress/strain distribution and margins of safety in launch vehicles and spacecraft primary structure design. Liquid propellant engine structures, solid propellant engine nozzles and the solid propellant itself are not covered, but liquid propellant tanks, pressure vessels and solid propellant cases are within the scope of ISO 16454:2007.
ISO 16454:2007 provides requirements for the determination of maximum stress and corresponding margin of safety under loading, and defines criteria for static strength failure modes, such as rupture, collapse and detrimental yielding. Critical conditions associated with fatigue, creep and crack growths are not covered. Notwithstanding these limitations in scope, the results of stress calculations based on the requirements of ISO 16454:2007 are applicable to other critical condition analyses.
In accordance with the requirements of ISO 16454:2007, models, methods and procedures for stress determination can also be applied to the displacements and deformation calculations, as well as to the loads definition, applied to substructures and structural members of structures under consideration. When ISO 16454:2007 is applied, it is assumed that temperature distribution has been determined and is used as input data.
|
Published |
2007-11 |
Edition : 1 |
Number of pages : 13 |
Technical Committee |
49.140
Space systems and operations
|
| ISO/DIS 16454 |
Space systems — Structural design — Stress analysis requirements |
ISO 16454:2007 is intended to be used for the determination of the stress/strain distribution and margins of safety in launch vehicles and spacecraft primary structure design. Liquid propellant engine structures, solid propellant engine nozzles and the solid propellant itself are not covered, but liquid propellant tanks, pressure vessels and solid propellant cases are within the scope of ISO 16454:2007.
ISO 16454:2007 provides requirements for the determination of maximum stress and corresponding margin of safety under loading, and defines criteria for static strength failure modes, such as rupture, collapse and detrimental yielding. Critical conditions associated with fatigue, creep and crack growths are not covered. Notwithstanding these limitations in scope, the results of stress calculations based on the requirements of ISO 16454:2007 are applicable to other critical condition analyses.
In accordance with the requirements of ISO 16454:2007, models, methods and procedures for stress determination can also be applied to the displacements and deformation calculations, as well as to the loads definition, applied to substructures and structural members of structures under consideration. When ISO 16454:2007 is applied, it is assumed that temperature distribution has been determined and is used as input data.
|
Under development |
|
Edition : 2 |
Number of pages : 13 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 16457:2014 |
Space systems — Space environment (natural and artificial) — The Earth's ionosphere model: international reference ionosphere (IRI) model and extensions to the plasmasphere |
ISO 16457:2014 provides guidance to potential users for the specification of the global distribution of ionosphere densities and temperatures, as well as the total content of electrons in the height interval from 50 km to 1 500 km. It includes and explains several options for a plasmaspheric extension of the model, embracing the geographical area between latitudes of 80°S and 80°N and longitudes of 0°E to 360°E, for any time of day, any day of year, and various solar and magnetic activity conditions.
|
Withdrawn |
2014-04 |
Edition : 1 |
Number of pages : 15 |
Technical Committee |
07.060
Geology. Meteorology. Hydrology
;
49.140
Space systems and operations
|
| ISO/TS 16457:2009 |
Space systems — Space environment (natural and artificial) — The Earth's ionosphere model: international reference ionosphere (IRI) model and extensions to the plasmasphere |
ISO/TS 16457:2009 provides guidance to potential users for the specification of the global distribution of ionosphere densities and temperatures, as well as the total content of electrons in the height interval from 50 km to 1 500 km. It includes and explains several options for a plasmaspheric extension of the model, embracing the geographical area between latitudes of 80°S and 80°N and longitudes of 0°E to 360°E, for any time of day, any day of year, and various solar and magnetic activity conditions.
|
Withdrawn |
2009-02 |
Edition : 1 |
Number of pages : 7 |
Technical Committee |
07.060
Geology. Meteorology. Hydrology
;
49.140
Space systems and operations
|
| ISO 16457:2022 |
Space environment (natural and artificial) — The Earth's ionosphere model — International reference ionosphere (IRI) model and extensions to the plasmasphere |
This document provides guidance to potential users for the specification of the global distribution of ionosphere densities and temperatures, as well as the total content of electrons in the height interval from 50 km to 1 500 km. It includes and explains several options for a plasmaspheric extension of the model, embracing the geographical area between latitudes of 80°S and 80°N and longitudes of 0°E to 360°E, for any time of day, any day of year, and various solar and magnetic activity conditions.
A brief introduction to ionospheric and plasmaspheric physics is given in Annex A. Annex B provides an overview over physical models, because they are important for understanding and modelling the physical processes that produce the ionospheric plasma.
|
Published |
2022-02 |
Edition : 2 |
Number of pages : 19 |
Technical Committee |
07.060
Geology. Meteorology. Hydrology
;
49.140
Space systems and operations
|
| ISO 16458:2004 |
Space systems — Unmanned spacecraft transportation — General requirements |
ISO 16458:2004 is applicable to unmanned spacecraft and their supporting hardware including science instrument and payloads. It establishes the requirements for transportation by rail, road, air, and water and as a part of a launch vehicle and establishes the requirements for special containers and loading/unloading operations meant to safeguard unmanned spacecraft and their supporting hardware during transportation.
ISO 16458:2004 is intended to be applied in international transportation. It may also be used in national transportation.
|
Published |
2004-01 |
Edition : 1 |
Number of pages : 8 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 16679:2015 |
Space systems — Relative motion analysis elements after LV/SC separation |
ISO 16679:2015 provides relative motion analysis elements after LV/SC separation, including analysis input, analysis principle, analysis method and analysis output. It is applicable to the mission design and verification for the prediction of relative motion after LV/SC separation.
This International Standard focuses on the relative motion between the objects involved in one launch mission. It does not cover the issues about the collision avoidance between newly launched objects and on-orbit ones.
|
Published |
2015-09 |
Edition : 1 |
Number of pages : 10 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 16691:2014 |
Space systems — Thermal control coatings for spacecraft — General requirements |
ISO 16691:2014 defines general requirements for thermal control coatings (TCC) that are applied on metallic and/or non-metallic surfaces of spacecraft and payloads in order to provide the following thermo-optical properties: αs: solar absorptance; ε: emittance.
The function of TCC is to reduce external heat absorption and/or to regulate radiant heat exchange between on-board equipment on spacecraft.
|
Published |
2014-02 |
Edition : 1 |
Number of pages : 17 |
Technical Committee |
49.140
Space systems and operations
;
49.025.01
Materials for aerospace construction in general
|
| ISO 16694:2015 |
Space systems — The measured parameters at firing bench and flight tests of liquid rocket engines |
ISO 16694:2015 applies to all types of liquid rocket engines for expendable launch systems and satellites:
a) Combustible fuel (including cryogenic);
b) Large-thrust, multiple component engines, with and without afterburning;
c) Low-thrust engines, one component (mono-propellant) and two-component (bi-propellant).
This International Standard establishes a list of parameters to be measured and registered with the firing stand and flight tests of serial LRE.
The order of preparation and carrying out of stand and flight tests, methods of processing, and analysis of tests results of liquid rocket engines, also measurement accuracy requirements are not regulated by this International Standard. Measurement accuracy requirements are established by engine designer.
Parameters listed in this International Standard characterize performance attributes of liquid rocket engines and are used for evaluating of technical state of engines (operative, inoperative), if they correspond to the requirements specified and possibilities of putting them into operation.
There are parameters specified in this International Standard, obligatory for registration and optional ones.
The manufacturer of liquid rocket engines can determine additional list of parameters for specific items taking into account their design and diagrammatical features.
The meaning "optional parameter" denotes (in cases when a proper unit or a component can be the part of an engine) that according to the manufacturer's decision, measurements are allowed not to be made.
Measurement of parameters at firing stand and flight tests of liquid rocket engines is be made by means of the same sensors if possible.
|
Published |
2015-03 |
Edition : 1 |
Number of pages : 13 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 16726:2018 |
Space systems — Human-life activity support systems and equipment integration in space flight — Techno-medical requirements for space vehicle human habitation environments — Requirements for the air quality affected by harmful chemical contaminants |
ISO 16726:2018 is a 3rd level standard with respect to ISO 17763 and is a 2nd level standard with respect to ISO 16157.
ISO 16726:2018 establishes environmental conditions for spacecraft air quality, including harmful chemical contaminants and requirements for harmful air contaminants' removal systems.
NOTE These systems support stated environmental conditions.
|
Published |
2018-05 |
Edition : 1 |
Number of pages : 10 |
Technical Committee |
49.140
Space systems and operations
|
| ISO/CD 16694 |
Space systems — Measured parameters at firing bench and flight tests of liquid rocket engines |
ISO 16694:2015 applies to all types of liquid rocket engines for expendable launch systems and satellites:
a) Combustible fuel (including cryogenic);
b) Large-thrust, multiple component engines, with and without afterburning;
c) Low-thrust engines, one component (mono-propellant) and two-component (bi-propellant).
This International Standard establishes a list of parameters to be measured and registered with the firing stand and flight tests of serial LRE.
The order of preparation and carrying out of stand and flight tests, methods of processing, and analysis of tests results of liquid rocket engines, also measurement accuracy requirements are not regulated by this International Standard. Measurement accuracy requirements are established by engine designer.
Parameters listed in this International Standard characterize performance attributes of liquid rocket engines and are used for evaluating of technical state of engines (operative, inoperative), if they correspond to the requirements specified and possibilities of putting them into operation.
There are parameters specified in this International Standard, obligatory for registration and optional ones.
The manufacturer of liquid rocket engines can determine additional list of parameters for specific items taking into account their design and diagrammatical features.
The meaning "optional parameter" denotes (in cases when a proper unit or a component can be the part of an engine) that according to the manufacturer's decision, measurements are allowed not to be made.
Measurement of parameters at firing stand and flight tests of liquid rocket engines is be made by means of the same sensors if possible.
|
Under development |
|
Edition : 2 |
|
Technical Committee |
49.140
Space systems and operations
|
| ISO 16695:2014 |
Space environment (natural and artificial) — Geomagnetic reference models |
ISO 16695:2014 defines reference models representing the geomagnetic field. It closely mirrors and clarifies specifications which have been in use for many decades.
The approach is to represent the corresponding scalar magnetic potential by a spherical harmonic expansion having specified numerical coefficients, called Gauss coefficients. ISO 16695:2014 covers models in which, at any one time, changes of the magnetic field are modelled by a linear time-dependence of each Gauss coefficient. A model might consist of a succession of sub-models, in each of which the coefficients change linearly with time. For such a step-wise linear model, the coefficients are continuous in time. ISO 16695:2014 provides the formulae and a step-by-step computational procedure to evaluate a geomagnetic reference model for any desired location and date.
ISO 16695:2014 does not specify the interpretation of the geophysical content of a geomagnetic reference model. It is left to the producer of a model to specify which internal and external magnetic sources are included in (or excluded from) their model.
|
Published |
2014-02 |
Edition : 1 |
Number of pages : 18 |
Technical Committee |
49.140
Space systems and operations
|
| ISO/TS 16697:2012 |
Space systems — Safety and compatibility of materials - Method to determine the flammability thresholds of materials |
ISO/TS 16697:2012 provides a method to determine the oxygen concentration threshold when a material exposed to a standard ignition source self-extinguishes at a given constant total pressure, temperature, convective flow, and gravity-level conditions. The method can also be used to determine other flammability limits, such as the total pressure or forced convective velocity thresholds, while maintaining other test conditions constant.
|
Published |
2012-08 |
Edition : 1 |
Number of pages : 8 |
Technical Committee |
49.140
Space systems and operations
;
13.220.40
Ignitability and burning behaviour of materials and products
;
49.025.01
Materials for aerospace construction in general
|
| ISO 16698:2013 |
Space environment (natural and artificial) — Methods for estimation of future geomagnetic activity |
ISO 16698:2013 specifies the methods used for estimating geomagnetic indices for time intervals ranging from short-term (hours to a few months) to the long-term (months to years).
Geomagnetic indices are used to describe the activity levels of the disturbance of the geomagnetic field. These indices can be used to estimate upper atmospheric and plasmaspheric densities and many other space environment models. They are also used as the input parameters for orbital lifetime prediction and worst-case environment analysis of electrostatic charging.
ISO 16698:2013 is useful for users who want to predict future geomagnetic indices and space environment.
|
Withdrawn |
2013-05 |
Edition : 1 |
Number of pages : 21 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 16698:2019 |
Space environment (natural and artificial) — Methods for estimation of future geomagnetic activity |
This document specifies the methods used for estimating geomagnetic indices for time intervals ranging from short-term (hours to a few months) to long-term (months to years). This document is intended for use to predict future geomagnetic indices and space environment.
|
Published |
2019-12 |
Edition : 2 |
Number of pages : 25 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 16699:2015 |
Space systems — Disposal of orbital launch stages |
ISO 16699:2015 focuses on disposal of launch vehicle stages used during launch of spacecraft to be operated in space where the orbital launch stages are left in orbit after the spacecraft are released.
End-of-mission disposal of launch vehicle orbital stages broadly means removing the stages from the protected regions of space (see ISO 24113) so as not to collide or otherwise interfere with the other users of those protected regions in the future. ISO 24113 also requires that "During the disposal phase, a spacecraft or launch vehicle orbital stage shall permanently deplete or make safe all remaining on-board sources of stored energy in a controlled sequence." These "passivation" actions are typically either accomplished in the course of disposal, or immediately follow the disposal operations. In this document, the term "disposal actions" refers to both disposal manoeuvres and to passivation actions (note: passivation actions are not required after the final manoeuvre leading to a controlled re-entry).
ISO 24113 provides six options for spacecraft or orbital launch stage disposal. This International Standard specifies techniques for planning and executing disposal of orbital launch stages that are consistent with ISO 24113 requirements, reflect current internationally accepted guidelines, and consider current operational procedures and best practices.
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Withdrawn |
2015-11 |
Edition : 1 |
Number of pages : 6 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 16781:2013 |
Space systems — Simulation requirements for control system |
ISO 16781:2013 provides guidance to control system engineers on what to simulate and how to use simulation to support their system engineering tasks. ISO 16781:2013 provides simulation requirements of control system for different phases in the process of designing a control system. Control system engineers can carry out various types of simulation experiments during various phases, according to ISO 16781:2013. ISO 16781:2013 establishes a minimum set of requirements for simulation of control system. The requirements are generic in nature because of their broad applicability to all types of simulations.
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Withdrawn |
2013-11 |
Edition : 1 |
Number of pages : 24 |
Technical Committee |
49.140
Space systems and operations
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| ISO 16781:2021 |
Space systems — Simulation requirements for control system |
This document establishes the requirements for simulation of the space control system, including the objective, architecture and procedure, etc. This document is applicable to four phases of control system development, including conceptual design, detailed design, prototype and integrated system.
The control system referred to in this document is the flight control system for guidance, navigation and control (GNC) of space systems which include launch vehicle, satellite and spaceship, etc. This document establishes a minimum set of requirements for simulation of the flight control system, and provides guidance to engineers on what to simulate in each phase of control system development. The requirements are generic in nature because of their broad applicability to all types of simulations. Implementation details of the requirements are addressed in project-specific standards, requirements, and handbooks, etc.
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Published |
2021-03 |
Edition : 2 |
Number of pages : 22 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 16919:2014 |
Space data and information transfer systems — Requirements for bodies providing audit and certification of candidate trustworthy digital repositories |
ISO 16919:2014 is meant primarily for those setting up and managing the organization performing the auditing and certification of digital repositories.
It should also be of use to those who work in or are responsible for digital repositories seeking objective measurement of the trustworthiness of their repository and wishing to understand the processes involved.
The main purpose is to define a CCSDS Recommended Practice (and ISO International Standard) on which to base the operations of the organization(s) which assess the trustworthiness of digital repositories using ISO 16363 and provide the appropriate certification. ISO 16919:2014 specifies requirements for bodies providing audit and certification of digital repositories, based on the metrics contained within ISO/IEC 17021 and CCSDS 652.0-M-1/ISO 16363. It is primarily intended to support the accreditation of bodies providing such certification.
ISO/IEC 17021 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.
ISO 16919:2014 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 clause numbers are kept consistent with those of ISO/IEC 17021. Some subclauses are applicable as they stand, and these are simply enumerated; otherwise additions to subclauses are explicitly given. In the former case, the clauses may consist of just a few sentences. As a result, this document must be read in conjunction with ISO/IEC 17021.
The requirements contained in this document need to be demonstrated in terms of competence and reliability by any organization or body providing certification of digital repositories.
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Published |
2014-11 |
Edition : 1 |
Number of pages : 22 |
Technical Committee |
49.140
Space systems and operations
;
03.120.20
Product and company certification. Conformity assessment
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| ISO 17107:2011 |
Space data and information transfer systems — XML specification for navigation data messages |
ISO 17107:2011 specifies a format for use in exchanging spacecraft navigation data. Such exchanges are used for distributing attitude, orbit, and tracking data between space agencies. ISO 17107:2011 specifies an integrated Extensible Markup Language (XML) schema set that applies to Navigation Data Messages (NDMs) defined in the CCSDS Recommended Standards for Attitude Data Messages (ADM), Orbit Data Messages (ODM), and Tracking Data Message (TDM).
This XML schema set is suited to inter-agency exchanges of any number of NDMs (ADM, ODM, and/or TDM).
ISO 17107:2011 is applicable only to the schema content and layout, and to instantiations of the schema, but not to the transmission of any instantiation of the schema. The potential for compression/decompression of the message is an aspect of the transmission that is not part of this specification. The means of transmission of an XML-formatted NDM between agencies is beyond the scope of ISO 17107:2011; such arrangements require specification via other means, for example, in an Interface Control Document (ICD).
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Published |
2011-11 |
Edition : 1 |
Number of pages : 85 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 17214:2011 |
Space data and information transfer systems — Spacecraft onboard interface services — Time access service |
ISO 17214:2011 defines services and service interfaces provided by the Spacecraft Onboard Interface Services (SOIS) time access service. It specifies only the service and not the methods of providing the service, although use of the SOIS subnetwork services is assumed.
ISO 17214:2011 conforms to the principles set out in the SOIS Green Book (CCSDS 850.0-G-1) and it is intended to be applied together with it.
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Withdrawn |
2011-12 |
Edition : 1 |
Number of pages : 35 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 17255:2014 |
Space systems — Programme management — Statement of work |
ISO 17255:2014 provides an overview of the purpose and descriptions of statement of work (SOW), its required contents, and process for developing the document.
ISO 17255:2014 is applicable to all types of space systems, product elements, and projects.
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Published |
2014-06 |
Edition : 1 |
Number of pages : 18 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 17401 |
Space systems — Spacecraft interface requirements document for launch vehicle services |
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Under development |
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Edition : 2 |
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Technical Committee |
49.140
Space systems and operations
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| ISO 17433:2001 |
Space data and information transfer systems — Packet telemetry services |
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Withdrawn |
2001-04 |
Edition : 1 |
Number of pages : 87 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 17355:2003 |
Space data and information transfer systems — CCSDS file delivery protocol |
ISO 17355:2002 specifies the requirements for a file delivery protocol and associated service for application in the space environment. It is intended for use over the current and envisaged packet delivery services used in the space environment.
ISO 17355:2002 specifies a protocol and associated services that are applicable to space missions with continuous duplex contact, intermittent duplex contact, asymmetrical time-disjunct contact, and simplex contact and operates in the space-to-ground, ground-to-space, and space-to-space directions of transfer. It may be initiated by the file sending or receiving entity.
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Withdrawn |
2003-02 |
Edition : 1 |
Number of pages : 152 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 17355:2004 |
Space data and information transfer systems — CCSDS file delivery protocol |
ISO 17355:2004 specifies the requirements for a file delivery protocol and associated service for application in the space environment. It is intended for use over the current and envisaged packet delivery services used in the space environment.
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Withdrawn |
2004-05 |
Edition : 2 |
Number of pages : 153 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 17355:2007 |
Space data and information transfer systems — CCSDS file delivery protocol |
ISO 17355:2007 defines a CCSDS file delivery protocol (CFDP) and associated service for application in the space environment. It is intended for use over the current and envisaged packet delivery services used in the space environment, including
CCSDS conventional packet telecommand;
CCSDS conventional packet telemetry;
CCSDS advanced orbiting systems (AOS) path service.
It may also operate over a wide variety of ground network services, including those specified by the CCSDS for cross-support purposes. The protocol operates in the space-to-ground, ground-to-space, and space-to-space directions of transfer. It may be initiated by the file sending or receiving entity. In the interests of interoperability, protocol elements are included for generalized forms of standard file manipulation operations based on assumptions of a common model for a ‘filestore', or medium used to store files. It is recognized, however, that the precise nature and capabilities of filestore management systems are operating-system dependent and, for that reason, the protocol assumes a virtual filestore and associated services that an implementation must map to the capabilities of the actual filestore used.
The scope and field of application are furthermore detailed in subclauses 1.2 and 1.3 of the enclosed CCSDS publication.
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Published |
2007-05 |
Edition : 3 |
Number of pages : 153 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 17399:2003 |
Space systems — Man-systems integration |
ISO 17399:2003 defines all generic requirements for manned space flight vehicle/habitat structures and flight crew training or simulation facilities and the related equipment that directly interfaces with manned space system flight crew members. ISO 17399:2003 covers the field of human factors as they relate to the space environment and space habitats. These man-systems integration requirements apply to space system launch, re-entry, on-orbit and extraterrestrial environments.
The requirements specified in ISO 17399:2003 are applicable to any manned space flight programme.
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Withdrawn |
2003-10 |
Edition : 1 |
Number of pages : 1 |
Technical Committee |
49.140
Space systems and operations
|
| ISO/TR 17400:2003 |
Space systems — Space launch complexes, integration sites and other facilities — General testing guidelines |
ISO/TR 17400:2003 is applicable to new projects and programs and to redesigned and upgraded launch pad and integration sites. ISO/TR 17400:2003 establishes the testing phases, goals, and general aspects for launch space complexes and complexes for assembly and tests of a vehicle and spacecraft and the associated equipment that, after successful testing, will be ready for launch vehicle processing and launch. ISO/TR 17400:2003 may be applicable to the creation of international launch pad and integration sites. At creation of new launching space complexes and complexes for assembly and tests of a vehicle and spacecraft (or at their modernization) within the framework of one country, the rules established by that country may be applied.
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Withdrawn |
2003-02 |
Edition : 1 |
Number of pages : 23 |
Technical Committee |
49.140
Space systems and operations
|
| ISO/TR 17400:2021 |
Space systems — Space launch complexes, integration sites and other facilities — General testing guidelines |
This document is applicable to new projects and programs and to redesigned and upgraded launch pad and integration sites. This document describes the testing phases, goals, and general aspects for launch space complexes and complexes for assembly and tests of a vehicle and spacecraft and the associated equipment that, after successful testing, will be ready for launch vehicle processing and launch. This document can be applied to the creation of international launch pad and integration sites. At creation of new launching space complexes and complexes for assembly and tests of a vehicle and spacecraft (or at their modernization) within the framework of one country, the rules established by that country can be applied.
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Published |
2021-08 |
Edition : 2 |
Number of pages : 23 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 17401:2004 |
Space systems — Spacecraft interface requirements document for launch vehicle services |
ISO 17401:2004 provides spacecraft (SC) organizations with the general format for presenting the interface requirement document (IRD) for launch vehicle services. The IRD provides a list of the major technical requirements spacecraft agencies provide to launch vehicle (LV) agencies when submitting an application for launch services.
ISO 17401:2004 is applicable to all existing commercial LV and related launch facilities so as to permit SC contractors to prepare a single interface requirement document for a given SC mission, independently of the LV contractor to be selected.
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Published |
2004-06 |
Edition : 1 |
Number of pages : 21 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 17520:2016 |
Space environment (natural and artificial) — Cosmic ray and solar energetic particle penetration inward the magnetosphere — Method of determination of the effective vertical cut-off rigidity |
ISO 17520:2016 describes the effective vertical cut-off rigidities of charged particles for near-Earth space and establishes principal requirements for their calculation. In Annex A, the calculation technique is verified using a typical example. This International Standard can be used to develop calculation techniques 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 spacecraft and other equipment in the near-Earth space.
This International Standard is valid for calculating the particle penetration by any of the component of interplanetary charged particles (Galactic, Solar, and Anomalous) with rigidities above 0,2 GV. The main goals of the present standardization for the determination of the effective vertical geomagnetic cut-off rigidities are as follows:
- provide an unambiguous procedure for calculation of the cut-off rigidities inside of the Earth's magnetosphere reflecting dependences on geomagnetic disturbances and local time;
- provide means of estimation of the impact of charged particle fluxes in interpretation and analysis of space experiments;
- provide efficient calculations of the transmission functions of low-altitude orbits of spacecraft and manned space-station;
- determine impact of solar energetic particle flux on spacecraft instrumentation and astronauts using results of independent online measurement of interplanetary particle fluxes.
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Published |
2016-04 |
Edition : 1 |
Number of pages : 11 |
Technical Committee |
49.140
Space systems and operations
|
| ISO/DIS 17520 |
Space environment (natural and artificial) — Cosmic ray and solar energetic particle penetration inward the magnetosphere — Method of determination of the effective vertical cut-off rigidity |
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Under development |
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Edition : 2 |
Number of pages : 15 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 17540:2016 |
Space systems — Liquid rocket engines and test stands — Terms and definitions |
ISO 17540:2016 provides terms and definitions in scope of design, testing, reliability analysis and quality control of liquid rocket engines. The terms are required for use in all types of documentation and literature including in the scope of standardization or using the results of this activity.
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Published |
2016-12 |
Edition : 1 |
Number of pages : 32 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 17546:2016 |
Space systems — Lithium ion battery for space vehicles — Design and verification requirements |
ISO 17546:2016 specifies design and minimum verification requirements for lithium ion rechargeable (including lithium ion polymer) batteries for space vehicles.
Lithium ion secondary electrochemical systems use intercalation compounds (intercalated lithium exists in an ionic or quasi-atomic form within the lattice of the electrode material) in the positive and in the negative electrodes.
The focus of this International Standard is on "battery assembly" and cell is described as "component cells" to be harmonized with other industrial standards and regulations.
"Performance"," safety", and "logistics" are the main points of view to specify.
ISO 17546:2016 does not address "disposal" or "recycle"; however, some recommendations regarding disposal are suggested.
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Published |
2016-03 |
Edition : 1 |
Number of pages : 52 |
Technical Committee |
49.140
Space systems and operations
|
| ISO/DIS 17546 |
Space systems — Lithium ion battery for space vehicles — Design and verification requirements |
ISO 17546:2016 specifies design and minimum verification requirements for lithium ion rechargeable (including lithium ion polymer) batteries for space vehicles.
Lithium ion secondary electrochemical systems use intercalation compounds (intercalated lithium exists in an ionic or quasi-atomic form within the lattice of the electrode material) in the positive and in the negative electrodes.
The focus of this International Standard is on "battery assembly" and cell is described as "component cells" to be harmonized with other industrial standards and regulations.
"Performance"," safety", and "logistics" are the main points of view to specify.
ISO 17546:2016 does not address "disposal" or "recycle"; however, some recommendations regarding disposal are suggested.
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Under development |
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Edition : 2 |
Number of pages : 58 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 17566:2011 |
Space systems — General test documentation |
ISO 17566:2011 provides a specific format for the development of test documentation for an individual test of a spacecraft, subsystem or unit. It is focused on the definition of the format for test plans, test specifications, test procedures and test reports.
The scope of ISO 17566:2011 does not include overall programme test planning. A specific test plan can also be part of the overall spacecraft project test plan.
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Published |
2011-07 |
Edition : 1 |
Number of pages : 26 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 17666:2003 |
Space systems — Risk management |
ISO 17666:2003 extends 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).
ISO 17666:2003 contains a summary of the general risk management process, which is subdivided into four (4) basic steps and nine (9) tasks. The implementation can be tailored to project-specific conditions.
The risk management process requires information exchange among all project domains and provides visibility over risks, with a ranking according to their criticality for the project. These risks are monitored and controlled according to the rules defined for the domains to which they belong.
ISO 17666:2003 is applicable to all space project phases, as defined in ISO 14300-1.
When viewed from the perspective of a specific programme or project context, the requirements defined in ISO 17666:2003 should be tailored to match the genuine requirements of a particular profile and circumstances of a programme or project.
|
Withdrawn |
2003-04 |
Edition : 1 |
Number of pages : 19 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 1756:1975 |
Industrial trucks — Dimensions of stillages — Connection gauge |
Specifies the dimensions of the stillages in direct contact with the hand-operated elevating trucks: free height, minimum free width.
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Published |
1975-06 |
Edition : 1 |
Number of pages : 1 |
Technical Committee |
53.060
Industrial trucks
|
| ISO 17666:2016 |
Space systems — Risk management |
ISO 17666:2016 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).
It contains a summary of the general risk management process, which is subdivided into four (4) basic steps and nine (9) tasks. The implementation can be tailored to project-specific conditions.
The risk management process requires information exchange among all project domains and provides visibility over risks, with a ranking according to their criticality for the project; these risks are monitored and controlled according to the rules defined for the domains to which they belong.
The fields of application of ISO 17666:2016 are all the space project phases. A definition of project phasing is given in ISO 14300‑1.
When viewed from the perspective of a specific programme or project context, the requirements defined in ISO 17666:2016 are tailored to match the genuine requirements of a particular profile and circumstances of a programme or project.
|
Published |
2016-11 |
Edition : 2 |
Number of pages : 20 |
Technical Committee |
49.140
Space systems and operations
|
| ISO/DIS 17666 |
Space systems — Risk management |
ISO 17666:2016 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).
It contains a summary of the general risk management process, which is subdivided into four (4) basic steps and nine (9) tasks. The implementation can be tailored to project-specific conditions.
The risk management process requires information exchange among all project domains and provides visibility over risks, with a ranking according to their criticality for the project; these risks are monitored and controlled according to the rules defined for the domains to which they belong.
The fields of application of ISO 17666:2016 are all the space project phases. A definition of project phasing is given in ISO 14300‑1.
When viewed from the perspective of a specific programme or project context, the requirements defined in ISO 17666:2016 are tailored to match the genuine requirements of a particular profile and circumstances of a programme or project.
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Under development |
|
Edition : 3 |
Number of pages : 22 |
Technical Committee |
49.140
Space systems and operations
|