| Name |
Description |
Abstract |
Status |
Publication date |
Edition |
Number of pages |
Technical committee |
ICS |
| ISO 17689:2015 |
Space systems — Interface control documents between ground systems, ground support equipment and launch vehicle with payload |
ISO 17689:2015 is applied for organizations developing ground support equipment and also for operators performing space activity.
Interface control documents format defined here does not contain the descriptions regarding various properties of ground support equipment (i.e. performance, functions or endurance to launch mechanical environment or quality assurance provisions) which are defined in technical specifications.
Control of interfaces, independently of its frequency or depth, cannot replace stages of parameters definition of high-quality production and development of technical requirements of project, design and development. Interfaces control is used as a control process that can provide necessary verification of successful finishing of design at a stated in contract period.
This International Standard establishes basic requirements for interface control documents (ICD) writing and interface control procedures for the following items included in launch system: payload, launch vehicle, ground support equipment (according to ISO 14625:2007) and launch site (buildings with technical systems). Notably
a) ICD between payload and launch vehicle (according to ISO 15863:2003),
b) ICD between ground support equipment and payload (this International Standard),
c) ICD between ground support equipment and launch vehicle (this International Standard),
d) ICD between items of ground support equipment (this International Standard), and
e) ICD between ground support equipment and launch site (this International Standard).
|
Published |
2015-10 |
Edition : 1 |
Number of pages : 17 |
Technical Committee |
49.140
Space systems and operations
|
| ISO/FDIS 17689 |
Space systems — Interface control documents between ground systems, ground support equipment and launch vehicle with payload |
ISO 17689:2015 is applied for organizations developing ground support equipment and also for operators performing space activity.
Interface control documents format defined here does not contain the descriptions regarding various properties of ground support equipment (i.e. performance, functions or endurance to launch mechanical environment or quality assurance provisions) which are defined in technical specifications.
Control of interfaces, independently of its frequency or depth, cannot replace stages of parameters definition of high-quality production and development of technical requirements of project, design and development. Interfaces control is used as a control process that can provide necessary verification of successful finishing of design at a stated in contract period.
This International Standard establishes basic requirements for interface control documents (ICD) writing and interface control procedures for the following items included in launch system: payload, launch vehicle, ground support equipment (according to ISO 14625:2007) and launch site (buildings with technical systems). Notably
a) ICD between payload and launch vehicle (according to ISO 15863:2003),
b) ICD between ground support equipment and payload (this International Standard),
c) ICD between ground support equipment and launch vehicle (this International Standard),
d) ICD between items of ground support equipment (this International Standard), and
e) ICD between ground support equipment and launch site (this International Standard).
|
Under development |
|
Edition : 2 |
|
Technical Committee |
49.140
Space systems and operations
|
| ISO 17761:2015 |
Space environment (natural and artificial) — Model of high energy radiation at low altitudes (300 km to 600 km) |
ISO 17761:2015 describes the fluxes of charged particles for near-Earth space on base of the PAMELA experiment data. This International Standard can be used to calculate fluxes of protons with energy more than 100 MeV up to geomagnetic cut-off rigidity at low altitudes (300 km to 600 km). The main goal of this International Standard is determining the impact of energetic charged particle flux upon spacecraft instrumentation and astronauts.
|
Published |
2015-11 |
Edition : 1 |
Number of pages : 6 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 17763:2018 |
Space systems — Human-life activity support systems and equipment integration in space flight |
This document (first level standard) is the main document among the others regarding human-life activity support systems and equipment integration in space flight.
This document, along with second and third level standards, forms a complex three-level international standard entitled: Space systems — Human-life activity support systems and equipment integration in space flight.
It is applicable to all human space flight programmes in all manned space objects, including space systems, space stations, lunar and planetary bases, as well as extravehicular activity. It covers all phases of development of a manned space object, such as design, production, tests, operation, and maintenance.
|
Published |
2018-09 |
Edition : 1 |
Number of pages : 7 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 17770:2017 |
Space systems — Cube satellites (CubeSats) |
ISO 17770:2017 addresses CubeSats, CubeSat Deployer and related verification of assurance/quality terms and metrics.
ISO 17770:2017 defines a unique class of picosatellite, the CubeSat. CubeSats are ideal as space development projects for universities around the world. In addition to their significant role in educating space scientists and engineers, CubeSats provide a low-cost platform for testing and space qualification of the next generation of small payloads in space. A key component of the project is the development of a standard CubeSat Deployer.
This Deployer is capable of releasing a number of CubeSats as secondary payloads on a wide range of launchers. The standard Deployer requires all CubeSats to conform to common physical requirements, and share a standard Deployer interface. CubeSat development time and cost can be significantly reduced by the development of standards that are shared by a large number of spacecraft.
Normative control of the CubeSat design, qualification and acceptance testing is generally applied from other small satellite specific standards with the exception of CubeSat/Deployer launch environment test.
|
Published |
2017-06 |
Edition : 1 |
Number of pages : 9 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 17807:2013 |
Space data and information transfer systems - Asynchronous message service |
ISO 17807:2013 defines a CCSDS Asynchronous Message Service (AMS) for mission data system communications. The service and its protocols implement an architectural concept under which the modules of mission systems, distinct sequential flows of application control logic, whether called processes, tasks, or threads, may be designed as if they were to operate in isolation, each one producing and consuming mission information without explicit awareness of which other modules are currently operating. Communication relationships among such modules are self-configuring; this tends to minimize complexity in the development and operations of modular data systems.
A system built on this model is a society of generally autonomous interoperating modules that may fluctuate freely over time in response to changing mission objectives, module functional upgrades, and recovery from individual module failure. The purpose of AMS, then, is to reduce mission cost and risk by providing standard, reusable infrastructure for the exchange of information among data system modules in a manner that is simple to use, highly automated, flexible, robust, scalable, and efficient.
ISO 17807:2013 specifies the protocol procedures and data units that accomplish automatic configuration of AMS communication relationships, dynamic reconfiguration of those relationships during operations, and the use of those relationships to accomplish the exchange of mission information among data system modules.
|
Published |
2013-06 |
Edition : 1 |
Number of pages : 147 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 17808:2014 |
Space data and information transfer systems — Telemetry (TM) channel coding profiles |
ISO 17808:2014 presents recommendations regarding the usage of coding schemes described in references [1]-[2] in the various mission profiles that are encountered in space research, space operations, and Earth exploration.
Within this document, it is assumed that at the sending end the Synchronization and Channel Coding sublayer
accepts at a constant rate transfer frames of fixed length from the Data Link protocol sublayer;
performs the encoding and synchronization functions selected for the mission; and
delivers a continuous and contiguous stream of channel symbols to the Physical layer.
At the receiving end, the Synchronization and Channel Coding sublayer:
accepts a continuous and contiguous stream of channel symbols from the Physical layer;
performs the synchronization and decoding functions selected for the mission;
delivers transfer frames to the Data Link protocol sublayer.
Profiles for Earth-to-space and Proximity links are out of scope and are not addressed in this document. Communication profiles for space-to-Earth links that are currently not supported by CCSDS, e.g. via data relay satellites, are not addressed in this document.
|
Published |
2014-07 |
Edition : 1 |
Number of pages : 12 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 17809:2014 |
Space data and information transfer systems - Delta-differential one-way ranging (Delta-DOR) operations |
Delta Differential One-Way Ranging (Delta-DOR) operations are applicable to space agencies that operate deep space missions that require accurate determination of the spacecraft position in the plane of the sky. For operations where these requirements do not capture the needs of the participating agencies, Delta-DOR operations may not be appropriate.
ISO 17809:2014 addresses rationale, requirements and criteria that Delta-DOR operations processes should be designed to meet.
|
Published |
2014-07 |
Edition : 1 |
Number of pages : 45 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 21494:2019 |
Space systems — Magnetic testing |
ISO 21494:2019 specifies magnetic test methods including magnetic field test methods, magnetic moment test methods, magnetization and demagnetization test methods and magnetic compensation test methods. This document is applicable to magnetic tests on several levels: spacecraft-level, subsystem-level and unit-level.
ISO 21494:2019 gives guidelines for conducting magnetic tests both in zero-magnetic field environment provided by magnetic test facilities and in the presence of the geomagnetic field environment.
|
Published |
2019-02 |
Edition : 1 |
Number of pages : 27 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 17810:2014 |
Space data and information transfer systems — Data transmission and pseudo-random noise (PN) ranging for 2 GHz code division multiple access (CDMA) link via data relay satellite |
ISO 17810:2014 defines CDMA spread spectrum modulation schemes in terms of:
a) the services provided to the users of this specification;
b) spreading code formats; and
c) the procedures performed to generate and process the code formats.
It does not specify:
a) individual implementations or products;
b) the methods or technologies required to perform the procedures; or
c) the management activities required to configure and control the system.
ISO 17810:2014 provides only those parameter requirements relating to signal compatibility with the existing SNIP PN spread modulation systems (see C.1). There are many other types of requirements, not specifically related to PN spread modulation signal formats, which must be met to ensure system compatibility with existing SNIP hardware. Examples would include forward error correction coding format, data signal formats, etc.
ISO 17810:2014 applies to the creation of agency standards and to the future data communications over space links between CCSDS agencies in cross-support situations. ISO 17810:2014 includes comprehensive specification of the data formats and procedures for inter-agency cross support. It is neither a specification of, nor a design for, real systems that may be implemented for existing or future missions.
ISO 17810:2014 is to be invoked through the normal standards programs of each CCSDS agency, and is applicable to those missions for which cross support based on capabilities described in ISO 17810:2014 is anticipated. Where mandatory capabilities are clearly indicated in sections of ISO 17810:2014, they must be implemented when this document is used as a basis for cross support. Where options are allowed or implied, implementation of these options is subject to specific bilateral cross-support agreements between the agencies involved.
|
Published |
2014-07 |
Edition : 1 |
Number of pages : 41 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 17851:2016 |
Space systems — Space environment simulation for material tests — General principles and criteria |
ISO 17851:2016 provides a general description of the whole set of space environment components which affect spacecrafts in various outer space regions, and the physical and chemical processes causing material degradation in a space environment, including synergistic effects. This International Standard defines the most important general principles and criteria of space environment simulation during material tests, and formulates the general requirements to laboratory test facilities and to physical and mathematical models that are applied to the research of the space environment impact on materials. The basic purpose of this International Standard is to
- provide a general description of the methodology in selecting a set of space environment components and their characteristics during spacecraft material tests, and
- determine general principles and criteria for the tests.
Additionally, such methodology will help in the understanding of the degree of coverage of space materials tests with existing International Standards on the specific test types, and help define the actual directions in developing new International Standards.
ISO 17851:2016 can be applied as a reference document in designing spacecrafts, forecasting spacecraft lifetime, conducting ground-based tests, and analyzing changes in material properties during operation.
|
Published |
2016-09 |
Edition : 1 |
Number of pages : 24 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 17854:2013 |
Space data and information transfer systems — Flexible advanced coding and modulation scheme for high rate telemetry applications |
ISO 17854:2013 defines an efficient and comprehensive coding and modulation solution able to support a wide range of spectral efficiency values and data rates. The main target is given by high data rate telemetry applications, i.e. Earth Exploration Satellite Service (EESS) telemetry payload, where the increase of the system throughput by means of advanced adaptive techniques is deemed essential in order to fulfil the requirements imposed by future missions.
ISO 17854:2013 presents a turbo-like coding/modulation scheme based on one possible realization of a Serial Concatenated Convolutional Code (SCCC). This scheme makes use of a set of a large variety of modulation techniques (including QPSK, 8PSK, 16APSK, 32APSK, and 64APSK) and a wide range of coding rates. The number of different modulation schemes available, combined with a properly selected coding rate, allows the overall system to make efficient use of the available bandwidth, adapting itself to the variable conditions of the link. The proposed scheme can implement Variable Coding and Modulation (VCM) mode, which varies the transmission scheme to the channel conditions following a predetermined schedule (for example, as a function of the elevation angle). When a channel is available to provide feedback (e.g. via Telecommand), the transmission scheme can be dynamically adjusted using the Adaptive Coding and Modulation (ACM) mode. The proposed coding scheme is easily adapted to any of the available modulation formats thanks to the pragmatic approach adopted: the outputs of the binary encoders are mapped to the considered modulation scheme, after being interleaved. In other words, a bit-interleaved coded modulation scheme is proposed.
The use of SCCC is intended mainly for high data rate applications. The Forward Error Correction (FEC) scheme is based on the concatenation of two simple four-state encoder structures. The SCCC scheme implies a Physical Layer frame of constant length, with pilots inserted in fixed positions. This architecture simplifies the synchronization procedure, thus further allowing fast and efficient acquisition at very high rates for the receiver.
ISO 17854:2013 describes a technique incorporating multiple modulation formats paired with a flexible coding and synchronization method in a tightly integrated fashion. In particular, ISO 17854:2013 provides a series of recommended formats where each format pairs a modulation technique with a tailored implementation of the coding and synchronization method. However, where these modulations and/or codes are recommended in other CCSDS documents, ISO 17854:2013 does not limit the choice of modulations and/or codes consistent with those recommendations.
|
Published |
2013-06 |
Edition : 1 |
Number of pages : 75 |
Technical Committee |
49.140
Space systems and operations
|
| ISO/CD 17981 |
Space systems — CubeSat interface |
This document describes internal and external interface of CubeSat. The internal interface includes the interface between components and the interface between a CubeSat platform and a mission payload. The external interface is limited to the umbilical connectors, i.e. access port. The document also describes the items to be included in the datasheet of the CubeSat components and platforms. The datasheet requirements apply to catalogued commercial products ready for sale. The interface between CubeSat and its deployer, i.e. POD, is not included in the scope. This document is applicable to all sizes of CubeSats.
|
Under development |
|
Edition : 1 |
|
Technical Committee |
49.140
Space systems and operations
|
| ISO/TR 18146:2015 |
Space systems — Space debris mitigation design and operation guidelines for spacecraft |
ISO/TR 18146:2015 contains non-normative information on spacecraft design and operational practices for mitigating space debris.
ISO/TR 18146:2015 is a supporting document to the family of international standards addressing space debris mitigation (see 2.2). The purpose of these standards is to minimize the creation of additional space debris by ensuring that spacecraft and launch vehicle orbital stages are designed, operated and disposed of in a manner that prevents them from generating debris throughout their orbital lifetime.
ISO/TR 18146:2015 can be used to guide spacecraft engineers in the application of these space debris mitigation standards. Table 1 lists the main debris mitigation requirements defined in the standards and compares them to equivalent recommendations published by the United Nations and the Inter-Agency Space Debris Coordination Committee.
|
Withdrawn |
2015-10 |
Edition : 1 |
Number of pages : 50 |
Technical Committee |
49.140
Space systems and operations
|
| ISO/TR 18146:2020 |
Space systems — Space debris mitigation design and operation manual for spacecraft |
This document contains information on the design and operational practices for launch vehicle orbital stages for mitigating space debris.
This document provides information to engineers on what are required or recommended in the family of space debris mitigation standards to reduce the growth of space debris by ensuring that spacecraft is designed, operated, and disposed of in a manner that prevents them from generating debris throughout their orbital lifetime.
|
Published |
2020-10 |
Edition : 2 |
Number of pages : 56 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 22538-1:2007 |
Space systems — Oxygen safety — Part 1: Design of oxygen systems and components |
ISO 22538-1:2007 describes a process for the design of oxygen systems and their components. ISO 22538-1:2007 applies equally to ground support equipment, launch vehicles and spacecraft.
|
Published |
2007-09 |
Edition : 1 |
Number of pages : 20 |
Technical Committee |
49.140
Space systems and operations
|
| ISO/TR 18147:2014 |
Space environment (natural and artificial) — Method of the solar energetic protons fluences and peak fluxes determination |
ISO/TR 18147:2014 is intended for calculating the probability for solar energetic particle (SEP) to have an impact on materials, hardware, and biological objects.
ISO/TR 18147:2014 establishes the differential energy spectra for the (0,1/103) MeV SEP fluences and/or peak fluxes in the near-earth space, beyond the earth magnetosphere during the missions any duration under varying solar activity.
If additional prepositions are used, the method establishes the basic fluences and peak fluxes for their determination throughout the heliosphere. When the effect of the particle penetration into the magnetosphere is taken into account, the method establishes the basic fluences and peak fluxes for their determination on the near-earth spacecraft and manned station orbits.
Because the occurrence of SEP is a process a probabilistic nature, fluences and peak fluxes calculation relate to the different levels of probability.
The method is intended for specialists engaged in determination of radiation conditions in space.
|
Published |
2014-04 |
Edition : 1 |
Number of pages : 22 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18197:2015 |
Space systems — Space based services requirements for centimetre class positioning |
ISO 18197:2015 defines the requirements for the wide area centimetre class positioning system by broadcasting augmentation data through satellites as follows.
- Centimetre class positioning
According to the progress of requirements for positioning services such as automatic farming, mapping and others, centimetre class positioning is very useful.
- Wide area positioning
It is quite effective to broadcast augmentation data through satellites for users over wide area such as a square, more than 1,000 km each side, anytime and anywhere. Even if this area is short of data network, additional ground network facilities are not needed. In addition, as ranging signal and augmentation data can be received from satellite broadcasting at the same time, it is unnecessary for user terminals to receive the signal such as transmitted by ground network.
- Real-time property
The user terminals need to resolve the ambiguity in real-time, using augmentation data broadcast from satellites or other means, for the realization of centimetre class positioning. On the other hand, the provider sides have to broadcast augmentation data such that the terminal sides are able to resolve the ambiguity in real-time.
|
Published |
2015-05 |
Edition : 1 |
Number of pages : 31 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18201:2013 |
Space data and information transfer systems — Mission operations reference model |
ISO 18201:2013 defines a Mission Operations (MO) reference model which provides a common basis for coordinating the development of CCSDS Recommended Standards for MO service specifications and serves as a reference to maintain the consistency of these Recommended Standards.
The scope of ISO 18201:2013 is the definition of all concepts and terms that establish a common basis for coordinating the development of CCSDS Recommended Standards for MO service specifications.
|
Published |
2013-06 |
Edition : 1 |
Number of pages : 73 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18202:2013 |
Space data and information transfer systems — Mission operations message abstraction layer |
ISO 18202:2013 defines the Mission Operations (MO) Message Abstraction Layer (MAL) in conformance with the service framework specified in CCSDS 520.0-G-3, Mission Operations Services Concept.
The MO MAL is a framework that provides generic service patterns to the Mission Operation services defined in CCSDS 520.0-G-3. These Mission Operations services are defined in terms of the MAL.
ISO 18202:2013 defines, in an abstract manner, the MAL in terms of:
the concepts that it builds upon;
the basic types it provides;
the message headers required by the layer;
the relationship between, and the valid sequence of, the messages and resulting behaviours.
It does not specify:
individual implementations or products;
the implementation of entities or interfaces within real systems;
the methods or technologies required for communications.
|
Withdrawn |
2013-06 |
Edition : 1 |
Number of pages : 193 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18202:2015 |
Space data and information transfer systems — Mission operations message abstraction layer |
ISO 18202:2015 defines, in an abstract manner, the MAL in terms of:
a) the concepts that it builds upon;
b) the basic types it provides;
c) the message headers required by the layer;
d) the relationship between, and the valid sequence of, the messages and resulting behaviours.
It does not specify:
a) individual implementations or products;
b) the implementation of entities or interfaces within real systems;
c) the methods or technologies required for communications.
|
Published |
2015-12 |
Edition : 2 |
Number of pages : 180 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18238:2015 |
Space systems — Closed loop problem solving management |
ISO 18238:2015 provides basic procedures and requirements of closed loop problem solving against product quality problems including failures, defects, accidents, and other undesirable conditions for organizations.
ISO 18238:2015 is intended to improve the closed loop problem solving management which covers the impact mitigation of the problem, root causes identification and problem containment, and lessons learned.
ISO 18238:2015 is applicable to problem solving management of all space products, starting from engineering development phase.
|
Published |
2015-11 |
Edition : 1 |
Number of pages : 13 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18257:2016 |
Space systems — Semiconductor integrated circuits for space applications — Design requirements |
ISO 18257:2016 specifies the basic design requirements for semiconductor ICs for space applications, including its design process, as well as required tasks and requirements of each stage. Requirements of specific circuit design are not included.
|
Published |
2016-11 |
Edition : 1 |
Number of pages : 24 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18322:2017 |
Space systems — General management requirements for space test centres |
ISO 18322:2017 specifies requirements for when a space test centre needs to demonstrate its competence to consistently provide space testing that meets customer requirements.
It specifies requirements for space test centres, applicable to the test process, test personnel (both, of the customer and the space test centre), test facilities, test environment and any operations related to the test item under responsibility of the space test centre as requested by the customer.
ISO 18322:2017 also defines the requirements for space testing and the development of test facilities.
ISO 18322:2017 was originally prepared with a focus on environmental testing (i.e. thermal vacuum, vibrations, acoustic, Electromagnetic Compatibility (EMC), Radio Frequency (RF), physical properties measurements, etc.).
ISO 18322:2017 applies to space test centres as self-standing organizations, or those belonging to a parent organization. ISO 18322:2017 has been prepared for organizations providing test services for space and launch segment elements and subsystems.
|
Published |
2017-10 |
Edition : 1 |
Number of pages : 23 |
Technical Committee |
49.140
Space systems and operations
;
03.120.20
Product and company certification. Conformity assessment
|
| ISO 18381:2013 |
Space data and information transfer systems — Lossless multispectral and hyperspectral image compression |
ISO 18381:2013 establishes a data compression algorithm applied to digital three-dimensional image data from payload instruments, such as multispectral and hyperspectral imagers, and specifies the compressed data format.
Data compression is used 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 instrument data are specified only to the extent necessary to ensure multi-mission support capabilities. ISO 18381:2013 does not attempt to quantify the relative bandwidth reduction, the merits of the approaches discussed, or the design requirements for encoders and associated decoders.
ISO 18381:2013 addresses only lossless compression of three-dimensional data, where the requirement is for a data-rate reduction constrained to allow no distortion to be added in the data compression/decompression process.
|
Published |
2013-06 |
Edition : 1 |
Number of pages : 54 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18382:2013 |
Space data and information transfer systems — Spacecraft onboard interface services — RFID-based inventory management systems |
ISO 18382:2013 provides recommended practices for the utilization of Radio Frequency Identification (RFID) protocol and communication standards in support of inventory management activities associated with space missions.
The recommended practices contained in ISO 18382:2013 enable member agencies to select the best option(s) available for interoperable RFID-based communications in the support of inventory management applications. The specification of a Recommended Practice facilitates interoperable communications and forms the foundation for cross-support of communication systems between separate member space agencies.
ISO 18382:2013 is targeted towards passive (unpowered) RFID tags transmitting in the 860 MHz ? 960 MHz Ultra High Frequency (UHF) radio band. The recommended practices are applicable to both terrestrial (ground-based) and space-based automated inventory management systems utilizing only passive RFID tags.
Active RFID systems and utilization of RFID tags for precision asset localization are not covered in ISO 18382:2013.
|
Published |
2013-06 |
Edition : 1 |
Number of pages : 46 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18423:2013 |
Space data and information transfer systems — Pseudo-Noise (PN) Ranging Systems |
ISO 18423:2013 provides a Recommendation for Space Data System Standards in the area of transparent and regenerative Pseudo-Noise (PN) ranging systems. The PN ranging system is used to measure the round-trip light time between a ground station and a spacecraft. Regenerative ranging is primarily relevant for low Signal-to-Noise Ratio (SNR) cases like those seen in deep space missions; transparent ranging is more suitable for high SNR cases or when high accuracy ranging is not required.
ISO 18423:2013 defines both transparent and regenerative PN ranging systems for non-data relay satellite users. The specification for PN code components and generation, on-board spacecraft regenerative/transparent processing, ground station processing, and uplink and downlink signal modulation are defined. ISO 18423:2013 does not specify individual implementations or products, implementation of service interfaces within real systems, or the management activities required to configure and control the protocol.
|
Withdrawn |
2013-06 |
Edition : 1 |
Number of pages : 37 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18423:2015 |
Space data and information transfer systems — Pseudo-Noise (PN) Ranging Systems |
ISO 18423:2015 defines both transparent and regenerative PN ranging systems for non?data relay satellite users. The specification for PN code components and generation, on-board spacecraft regenerative/transparent processing, ground station processing, and uplink and downlink signal modulation are defined in this document. This Recommended Standard does not specify a) individual implementations or products, b) implementation of service interfaces within real systems, or c) the management activities required to configure and control the protocol.
|
Published |
2015-08 |
Edition : 2 |
Number of pages : 28 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 19924:2017 |
Space systems — Acoustic testing |
ISO 19924:2017 provides guidance for test providers and interested parties to implement acoustic tests of aerospace systems, subsystems, modules and units for applicable spacecraft programs. ISO 19924:2017 specifies a framework to meet test and process requirements and acts as a supplement to ISO 15864.
The acoustic test system, the technical requirements and the procedures for acoustic tests in reverberant chambers are described. Furthermore, the criteria for the manual test interruption and evaluation are also described.
The technical requirements in ISO 19924:2017 can be tailored to fulfil the objectives of tests.
|
Published |
2017-09 |
Edition : 1 |
Number of pages : 17 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18424:2013 |
Space data and information transfer systems — XML Telemetric and Command Exchange (XTCE) |
ISO 18424:2013 addresses the need for a standardized information model capable of supporting Telemetry/Telecommand (TM/TC) definitions across the widest possible range of space domain activities. The goal is to allow TM/TC definitions to be exchanged between different organizations and systems, often at the boundaries of mission phases, without the need for customized import/export, re-validation, or even re-implementation of mission databases.
The scope of ISO 18424:2013 is limited to the satellite telemetry and commanding meta-data constructs necessary to perform satellite and payload data processing. ISO 18424:2013 includes the meta-data needed to:
Define the structure and sequence of both CCSDS packets and TDM frames;
Define the data manipulation required for packaging and unpacking of individual data items;
Describe command data including command identification, argument specification, and validation criteria;
Define parameter and command encoding;
Define data properties including including default values, validity criteria, and data dependencies.
The scope of ISO 18424:2013 does not extend to:
Data distribution mechanisms or rules;
Command and data protocol specifications;
RF or analog stream characterization;
Data grouping including aggregation and coherent data sets;
Data representation (visualization properties);
Scheduling configuration properties;
Orbital properties;
Displays;
Flight Software.
ISO 18424:2013 addresses only the definition of TM/TC data, but is not a specification for the transfer of live or historical TM/TC data. It is a meta-data specification, not a data specification.
|
Published |
2013-06 |
Edition : 1 |
Number of pages : 86 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18425:2013 |
Space data and information transfer systems — Spacecraft Onboard Interface Services — Subnetwork Packet Service |
ISO 18425:2013 is one of a family of documents specifying the SOIS-compliant services to be provided by onboard subnetworks.
ISO 18425:2013 defines services and service interfaces provided by the SOIS Subnetwork Packet Service. Its scope is to specify the service only and not to specify methods of providing the service over a variety of onboard data links.
ISO 18425:2013 conforms to the principles set out in the Spacecraft Onboard Interface Services Green Book and is intended to be applied together with it. The protocols which provide this service are to be documented for individual links, and this can be in the purview of individual missions, agencies, or CCSDS, depending on future circumstances.
|
Published |
2013-06 |
Edition : 1 |
Number of pages : 27 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18426:2013 |
Space data and information transfer systems — Spacecraft Onboard Interface Services — Subnetwork Memory Access Service |
ISO 18426:2013 is one of a family of documents specifying the SOIS-compliant services to be provided by onboard subnetworks.
ISO 18426:2013 defines services and service interfaces provided by the SOIS Subnetwork Memory Access Service. Its scope is to specify the service only and not to specify methods of providing the service over a variety of onboard data links.
ISO 18426:2013 conforms to the principles set out in the Spacecraft Onboard Interface Services Green Book and is intended to be applied together with it. The protocols which provide this service are to be documented for individual links, and this can be in the purview of individual missions, agencies, or CCSDS, depending on future circumstances.
|
Published |
2013-06 |
Edition : 1 |
Number of pages : 29 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18427:2013 |
Space data and information transfer systems — Spacecraft Onboard Interface Services — Subnetwork Synchronization Service |
ISO 18427:2013 is one of a family of documents specifying the SOIS-compliant services to be provided by onboard subnetworks.
ISO 18427:2013 defines services and service interfaces provided by the SOIS Subnetwork Synchronisation Service. Its scope is to specify the service only and not to specify methods of providing the service over a variety of onboard data links.
ISO 18427:2013 conforms to the principles set out in the Spacecraft Onboard Interface Services Green Book and is intended to be applied together with it. The protocols which provide this service are to be documented for individual links, and this can be in the purview of individual missions, agencies, or CCSDS, depending on future circumstances.
|
Published |
2013-06 |
Edition : 1 |
Number of pages : 23 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18428:2013 |
Space data and information transfer systems — Spacecraft Onboard Interface Services — Subnetwork Device Discovery Service |
ISO 18428:2013 is one of a family of documents specifying the SOIS-compliant services to be provided by onboard subnetworks.
ISO 18428:2013 defines services and service interfaces provided by the SOIS Subnetwork Device Discovery Service. Its scope is to specify the service only and not to specify methods of providing the service over a variety of onboard data links.
ISO 18428:2013 conforms to the principles set out in the Spacecraft Onboard Interface Services Green Book and is intended to be applied together with it. The protocols which provide this service are to be documented for individual links, and this can be in the purview of individual missions, agencies, or CCSDS, depending on future circumstance.
|
Published |
2013-06 |
Edition : 1 |
Number of pages : 23 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18438:2013 |
Space data and information transfer systems — Spacecraft Onboard Interface Services — Subnetwork Test Service |
ISO 18438:2013 is one of a family of documents specifying the SOIS-compliant services to be provided by onboard subnetworks.
ISO 18438:2013 defines services and service interfaces provided by the SOIS Subnetwork Test Service. Its scope is to specify the service only and not to specify methods of providing the service over a variety of onboard data links.
ISO 18438:2013 conforms to the principles set out in the Spacecraft Onboard Interface Services Green Book and is intended to be applied together with it. The protocols which provide this service are to be documented for individual links, and this may be in the purview of individual missions, agencies, or CCSDS, depending on future circumstance.
|
Published |
2013-06 |
Edition : 1 |
Number of pages : 22 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 20206:2015 |
Space data and information transfer systems — IP over CCSDS space links |
ISO 20206:2015 addresses the recommended method for transferring IP Protocol Data Units (PDUs) over CCSDS space links.
|
Published |
2015-08 |
Edition : 1 |
Number of pages : 22 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18440:2013 |
Space data and information transfer systems — Space Link Extension — Internet Protocol for Transfer Services |
The Space Link Extension (SLE) Reference Model identifies a set of SLE Transfer Services that enable missions to send forward space link data units to a spacecraft and to receive return space link data units from a spacecraft. A subset of these services is specified by the SLE Transfer Service Recommended Standards. The SLE Transfer Service Recommended Standards specify:
the operations necessary to provide the transfer service;
the parameter data associated with each operation;
the behaviors that result from the invocation of each operation; and
the relationship between, and the valid sequence of, the operations and resulting behaviors.
However, they deliberately do not specify the methods or technologies required for communications.
ISO 18440:2013 defines a protocol for transfer of SLE Protocol Data Units (PDUs) defined in the SLE Transfer Service Recommended Standards using the Internet protocols TCP (Transmission Control Protocol and IP (Internet Protocol) for data transfer and the Abstract Syntax Notation One (ASN.1) for data encoding. This protocol is referred to as the Internet SLE Protocol One (ISP1).
ISO 18440:2013 defines a protocol for transfer of SLE PDUs between an SLE user and an SLE provider system in terms of:
the procedures used to establish and release associations;
the messages exchanged on an established association;
the procedures used to monitor the status of data communication connections; and
the methods used to ensure that data are converted between different formats and representations on different platforms.
It does not specify:
individual designs, implementations, or products;
the configuration of the data communications infrastructure, including configuration of the TCP and IP protocols;
the means by which addresses (IP addresses and TCP port numbers) are agreed, assigned, and communicated.
ISO 18440:2013 responds to the requirements imposed by the International Standards for SLE transfer services that were available when this International Standard was released. The protocol specified in ISO 18440:2013 conforms to the requirements on data communication services set forth in those International Standards.
|
Withdrawn |
2013-06 |
Edition : 1 |
Number of pages : 73 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18440:2016 |
Space data and information transfer systems — Space link extension — Internet protocol for transfer services |
ISO 18440:2016 defines a protocol for transfer of SLE PDUs between an SLE user and an SLE provider system in terms of:
a) the procedures used to establish and release associations;
b) the messages exchanged on an established association;
c) the procedures used to monitor the status of data communication connections; and
d) the methods used to ensure that data are converted between different formats and representations on different platforms.
It does not specify:
a) individual designs, implementations, or products;
b) the configuration of the data communications infrastructure, including configuration of the TCP and IP protocols;
c) the means by which addresses (IP addresses and TCP port numbers) are agreed, assigned and communicated.
|
Published |
2016-11 |
Edition : 2 |
Number of pages : 67 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18441:2013 |
Space data and information transfer systems — Space Link Extension — Application Program Interface for Transfer Services — Core Specification |
ISO 18441:2013 defines a C++ Application Program Interface (API) for CCSDS Space Link Extension (SLE) Transfer Services, which is independent of any specific technology used for communications between an SLE service user and an SLE service provider.
ISO 18441:2013 defines the Application Program Interface in terms of:
the components that provide the services of the API;
the functionality provided by each of the components;
the interfaces provided by each of the components; and
the externally visible behavior associated with the interfaces exported by the components.
It does not specify:
individual implementations or products;
the internal design of the components; and
the technology used for communications.
ISO 18441:2013 defines those aspects of the Application Program Interface which are common for all SLE service types or for a subset of the SLE service types, e.g. all return link services or all forward link services. It also defines a framework for specification of service type-specific elements of the API. Service-specific aspects of the API are defined by supplemental Recommended Practice documents for SLE return link services and SLE forward link services.
ISO 18441:2013 for the Application Program Interface responds to the requirements imposed on such an API by the CCSDS SLE transfer service Recommended Standards that were available when ISO 18441:2013 was released.
|
Withdrawn |
2013-06 |
Edition : 1 |
Number of pages : 371 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18441:2016 |
Space data and information transfer systems — Space link extension — Application program interface for transfer services — Core specification |
ISO 18441:2016 defines the Application Program Interface in terms of:
a) the components that provide the services of the API;
b) the functionality provided by each of the components;
c) the interfaces provided by each of the components; and
d) the externally visible behavior associated with the interfaces exported by the components.
It does not specify:
ISO 18441:2016 defines those aspects of the Application Program Interface, which are common for all SLE service types or for a subset of the SLE service types, e.g., all return link services or all forward link services. It also defines a framework for specification of service type-specific elements of the API. Service-specific aspects of the API are defined by supplemental Recommended Practice documents for SLE return link services (references [10], [11], and [12]) and SLE forward link services (references [13] and [14]).
ISO 18441:2016 for the Application Program Interface responds to the requirements imposed on such an API by the CCSDS SLE transfer service Recommended Standards that were available when this Recommended Practice was released.
|
Withdrawn |
2016-11 |
Edition : 2 |
Number of pages : 368 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18444:2016 |
Space data and information transfer systems — Space link extension — Application program interface for return operational control fields service |
ISO 18444:2016 defines extensions to the SLE API in terms of:
a) the ROCF-specific functionality provided by API components;
b) the ROCF-specific interfaces provided by API components; and
c) the externally visible behavior associated with the ROCF interfaces exported by the components.
It does not specify:
a) individual implementations or products;
b) the internal design of the components; and
c) the technology used for communications.
ISO 18444:2016 defines only interfaces and behavior that must be provided by implementations supporting the Return Operational Control Fields service in addition to the specification in reference [3].
|
Published |
2016-11 |
Edition : 2 |
Number of pages : 73 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 3164:1979 |
Earth-moving machinery — Laboratory evaluations of roll-over and falling-object protective structures — Specifications for the deflection-limiting volume |
|
Withdrawn |
1979-11 |
Edition : 3 |
Number of pages : 4 |
Technical Committee |
53.100
Earth-moving machinery
|
| ISO 18441:2021 |
Space data and information transfer systems — Space link extension — Application program interface for transfer services — Core specification |
This document defines the Application Program Interface in terms of:
the components that provide the services of the API;
the functionality provided by each of the components;
the interfaces provided by each of the components; and
the externally visible behavior associated with the interfaces exported by the components.
It does not specify:
individual implementations or products;
the internal design of the components; and
the technology used for communications.
This document defines those aspects of the Application Program Interface, which are common for all SLE service types or for a subset of the SLE service types, e.g., all return link services or all forward link services. It also defines a framework for specification of service type-specific elements of the API. Service-specific aspects of the API are defined by supplemental Recommended Practice documents for SLE return link services (references [10], [11], and [12]) and SLE forward link services (references [13] and [14]).
This document for the Application Program Interface responds to the requirements imposed on such an API by the CCSDS SLE transfer service Recommended Standards that were available when this document was released.
|
Published |
2021-06 |
Edition : 3 |
Number of pages : 365 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18442:2013 |
Space data and information transfer systems — Space Link Extension — Application Program Interface for Return All Frames Service |
ISO 18442:2013 specifies extensions to the API needed for support of the Return All Frames (RAF) service defined in CCSDS 911.1-B-2.
ISO 18442:2013 defines extensions to the SLE API in terms of:
the RAF-specific functionality provided by API components;
the RAF-specific interfaces provided by API components; and
the externally visible behavior associated with the RAF interfaces exported by the components.
It does not specify
individual implementations or products;
the internal design of the components; and
the technology used for communications.
ISO 18442:2013 defines only interfaces and behavior that must be provided by implementations supporting the Return All Frames service in addition to the specification in CCSDS 914.0-M-1.
|
Withdrawn |
2013-06 |
Edition : 1 |
Number of pages : 66 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18442:2016 |
Space data and information transfer systems — Space link extension — Application program interface for return all frames service |
ISO 18442:2016 defines extensions to the SLE API in terms of:
a) the RAF-specific functionality provided by API components;
b) the RAF-specific interfaces provided by API components; and
c) the externally visible behavior associated with the RAF interfaces exported by the components.
It does not specify
a) individual implementations or products;
b) the internal design of the components; and
c) the technology used for communications.
ISO 18442:2016 defines only interfaces and behavior that must be provided by implementations supporting the Return All Frames service in addition to the specification in reference [3].
|
Published |
2016-11 |
Edition : 2 |
Number of pages : 58 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18443:2013 |
Space data and information transfer systems — Space Link Extension — Application Program Interface for Return Channel Frames Service |
ISO 18443:2013 specifies extensions to the API needed for support of the Return Channel Frames (RCF) service defined in CCSDS 911.2-B-1.
ISO 18443:2013 defines extensions to the SLE API in terms of:
the RCF-specific functionality provided by API components;
the RCF-specific interfaces provided by API components; and
the externally visible behavior associated with the RCF interfaces exported by the components.
It does not specify:
individual implementations or products;
the internal design of the components; and
the technology used for communications.
ISO 18443:2013 defines only interfaces and behavior that must be provided by implementations supporting the Return Channel Frames service in addition to the specification in CCSDS 914.0-M-1.
|
Withdrawn |
2013-06 |
Edition : 1 |
Number of pages : 67 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18443:2016 |
Space data and information transfer systems — Space link extension — Application program interface for return channel frames service |
ISO 18443:2016 Practice defines extensions to the SLE API in terms of:
a) the RCF-specific functionality provided by API components;
b) the RCF-specific interfaces provided by API components; and
c) the externally visible behavior associated with the RCF interfaces exported by the components.
It does not specify:
a) individual implementations or products;
b) the internal design of the components; and
c) the technology used for communications.
ISO 18443:2016 defines only interfaces and behavior that must be provided by implementations supporting the Return Channel Frames service in addition to the specification in reference [3].
|
Published |
2016-11 |
Edition : 2 |
Number of pages : 63 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18444:2013 |
Space data and information transfer systems — Space Link Extension — Application Program Interface for Return Operational Control Fields Service |
ISO 18444:2013 specifies extensions to the API needed for support of the Return Operational Control Fields (ROCF) service defined in CSDS 911.5-B-1.
ISO 18444:2013 defines extensions to the SLE API in terms of:
the ROCF-specific functionality provided by API components;
the ROCF-specific interfaces provided by API components; and
the externally visible behavior associated with the ROCF interfaces exported by the components.
It does not specify:
individual implementations or products;
the internal design of the components; and
the technology used for communications.
ISO 18444:2013 defines only interfaces and behavior that must be provided by implementations supporting the Return Operational Control Fields service in addition to the specification in CCSDS 914.0-M-1.
|
Withdrawn |
2013-06 |
Edition : 1 |
Number of pages : 76 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18445:2013 |
Space data and information transfer systems — Space Link Extension — Application Program Interface for the Forward CLTU Service |
ISO 18445:2013 specifies extensions to the API needed for support of the Command Link Transmission Unit (CLTU) service defined in CCSDS 912.1-B-2.
ISO 18445:2013 defines extensions to the SLE API in terms of:
the CLTU-specific functionality provided by API components;
the CLTU-specific interfaces provided by API components; and
the externally visible behavior associated with the CLTU interfaces exported by the components.
It does not specify
individual implementations or products;
the internal design of the components; and
the technology used for communications.
ISO 18445:2013 defines only interfaces and behavior that must be provided by implementations supporting the forward CLTU service in addition to the specification in CCSDS 914.0-M-1.
|
Withdrawn |
2013-06 |
Edition : 1 |
Number of pages : 97 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18445:2016 |
Space data and information transfer systems — Space link extension — Application program interface for the forward CLTU service |
ISO 18445:2016 Practice defines extensions to the SLE API in terms of:
a) the CLTU-specific functionality provided by API components;
b) the CLTU-specific interfaces provided by API components; and
c) the externally visible behavior associated with the CLTU interfaces exported by the components.
It does not specify
a) individual implementations or products;
b) the internal design of the components; and
c) the technology used for communications.
ISO 18445:2016 defines only interfaces and behavior that must be provided by implementations supporting the forward CLTU service in addition to the specification in reference [5].
|
Published |
2016-11 |
Edition : 2 |
Number of pages : 103 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18446:2013 |
Space data and information transfer systems — Space Link Extension — Application Program Interface for the Forward Space Packet Service |
ISO 18446:2013 specifies extensions to the API needed for support of the Forward Space Packet Service defined in CCSDS 912.3-B-1.
ISO 18446:2013 defines extensions to the SLE API in terms of:
the FSP-specific functionality provided by API components;
the FSP-specific interfaces provided by API components; and
the externally visible behavior associated with the FSP interfaces exported by the components.
It does not specify:
individual implementations or products;
the internal design of the components; and
the technology used for communications.
ISO 18446:2013 defines only interfaces and behavior that must be provided by implementations supporting the Forward Space Packet service in addition to the specification in ISO/IEC 14882.
|
Withdrawn |
2013-06 |
Edition : 1 |
Number of pages : 154 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18446:2016 |
Space data and information transfer systems — Space link extension — Application program interface for the forward space packet service |
ISO 18446:2016 defines extensions to the SLE API in terms of:
a) the FSP-specific functionality provided by API components;
b) the FSP-specific interfaces provided by API components; and
c) the externally visible behavior associated with the FSP interfaces exported by the components.
It does not specify:
a) individual implementations or products;
b) the internal design of the components; and
c) the technology used for communications.
ISO 18446:2016 defines only interfaces and behavior that must be provided by implementations supporting the Forward Space Packet service in addition to the specification in reference [5].
|
Published |
2016-11 |
Edition : 2 |
Number of pages : 149 |
Technical Committee |
49.140
Space systems and operations
|
| ISO/TS 18667:2018 |
Space systems — Capability-based Safety, Dependability, and Quality Assurance (SD&QA) programme management |
ISO/TS 18667:2018 applies to the design, development, fabrication, test, and operation of commercial, civil, and military space and ground control systems, sites/facilities, services, equipment, and computer software. Criteria is provided for rating the capability of the entire SD&QA programme or an individual SD&QA process to identify, assess, and eliminate or mitigate risks that threaten safety or mission success. The predefined capability rating criteria define the sequence of activities necessary to achieve a measurable improvement in the effectiveness of SD&QA risk management by implementing it in stages. Organizations can evaluate their existing SD&QA programme against the criteria in this document to identify the activities that need to be added, deleted, or modified to achieve the desired technical risk management effort. The phrase "desired technical risk management effort" means the activities and resources used to identify, assess, and eliminate or mitigate technical risks are commensurate with the product's unit-value/criticality and systems engineering life cycle data content/maturity.
|
Published |
2018-02 |
Edition : 1 |
Number of pages : 67 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 19923:2017 |
Space environment (natural and artificial) — Plasma environments for generation of worst case electrical potential differences for spacecraft |
ISO 19923:2017 specifies space plasma environments that lead to the generation of the worst-case surface potential differences for spacecraft. It also specifies how to estimate worst-case potential differences by using the simulation codes provided.
ISO 19923:2017 includes plasma energy and density in GEO, PEO, and MEO. ISO 19923:2017 does not include descriptions of plasma energy and density in LEO because large surface charging in LEO is likely to be due to high-voltage power generation by instrumentation of the spacecraft.
ISO 19923:2017 deals with external surface charging of spacecraft only.
|
Published |
2017-06 |
Edition : 1 |
Number of pages : 14 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 22538-5:2010 |
Space systems — Oxygen safety — Part 5: Operational and emergency procedures |
ISO 22538-5:2010 specifies a set of operational and emergency procedures for the safe storage, handling and transfer of liquid and gaseous oxygen.
|
Published |
2010-07 |
Edition : 1 |
Number of pages : 9 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 18676:2017 |
Space systems — Guidelines for the management of systems engineering |
ISO 18676:2017 presents the guidelines for the management of systems engineering for space systems.
ISO 18676:2017 addresses the systems engineering activities and provides guidelines for interfacing with specific major management subjects (e.g. configuration management, data management, interface management, risk management, requirements management, and integrated logistics support), which are themselves the subject of this document.
ISO 18676:2017 establishes a common reference for all customers and suppliers in the space sector to work with management systems engineering for all space products and projects.
These guidelines emphasize the following aspects of managing space systems engineering:
- the positioning of space systems engineering activities related to the management of space activities;
- the framework for the management of systems engineering;
- the systems engineering management plan (SEMP);
- the system, product and work breakdown structures;
- the phasing, scheduling and recursivity of the systems engineering management;
- reviews, audits and control gates;
- the main activities of systems engineering and the respective management approach.
ISO 18676:2017 is not the scope of this document to describe in detail the standard systems engineering process or project management process for all types of space systems.
|
Published |
2017-11 |
Edition : 1 |
Number of pages : 17 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 19389:2014 |
Space data and information transfer systems — Conjunction data message |
ISO 19389:2014 specifies a standard message format for use in exchanging spacecraft conjunction information between originators of Conjunction Assessments (CAs) and satellite owner/operators and other authorized parties. Such exchanges are used to inform satellite owner/operators of conjunctions between objects in space to enable consistent warning by different organizations employing diverse CA techniques.
ISO 19389:2014 will:
facilitate interoperability and enable consistent warning between data originators who supply CA and the satellite owner/operators who use it;
facilitate automation for the CA processes; and
provide critical information to enable timely CA decisions.
This document includes requirements and criteria that the message format has been designed to meet (see Annex D). Also included are informative descriptions of conjunction information pertinent to performing CA (see Annex E).
ISO 19389:2014 is applicable to satellite operations in all environments in which close approaches and collisions among satellites are concerns. It contains the specification for a Conjunction Data Message (CDM) designed for applications involving conjunction information interchange between originators of CAs and recipients. Conjunction information includes data types such as miss distance, probability of collision, Time of Closest Approach (TCA), and closest approach relative position and velocity. Further information describing the conjunction information contained in this message can be found in section 3 and Annex E.
This message is suited for exchanges that involve manual or automated interaction. The attributes of a CDM make it suitable for use in machine-to-machine interfaces because of the large amount of data typically present. The CDM is self contained. However, additional information could be specified in an Interface Control Document (ICD) written jointly by the service originator and recipients.
It is desirable that CDM originators maintain consistency with respect to the optional keywords provided in their implementations; i.e., it is desirable that the composition of the CDMs provided not change on a frequent basis.
ISO 19389:2014 is applicable only to the message format and content, but not to its transmission nor to the algorithms used to produce the data within. The method of transmitting the message between exchange partners is beyond the scope of this document and could be specified in an ICD.
The methods used to predict conjunctions and calculate the probability of collision, and the definition of the conjunction assessment accuracy underlying a particular CDM, are also outside the scope of ISO 19389:2014 (the interested reader can consult references in Annex F).
|
Published |
2014-07 |
Edition : 1 |
Number of pages : 62 |
Technical Committee |
49.140
Space systems and operations
|
| ISO/TR 19473:2015 |
Space systems — Best practices for orbit elements at payload — LV separation |
ISO/TR 19473:2015 provides the best practices for orbit elements at payload-LV separation. It includes orbit elements and calculation conditions, calculation method of orbit elements and their errors at elliptical orbit insertion of various payloads. The fit between the actual and expected values of orbit elements can be used as a criterion of commercial launch.
There are many different sets of orbit elements. Each is best suited for a particular application. The traditionally used set of orbital elements is called the set of Keplerian elements. ISO/TR 19473:2015 gives the calculation method of Keplerian elements and the transformation method of all the other orbit elements, in order to satisfy different user's need.
Affected by terrestrial gravitational perturbation, lunisolar gravitation perturbation and other factors, orbit elements change slowly after orbit injection. Orbit elements calculation methods after separation are not included in this Technical Report.
The technical communication and specific progress for orbit elements is relatively easy to be agreed on by applying this ISO/TR 19473:2015, which can contribute to avoiding possible disputes.
|
Published |
2015-09 |
Edition : 1 |
Number of pages : 12 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 19683:2017 |
Space systems — Design qualification and acceptance tests of small spacecraft and units |
ISO 19683:2017 provides test methods and test requirements for design qualification and/or acceptance of small spacecraft or units. It provides the minimum test requirements and test methods to qualify the design and manufacturing methods of commercial small spacecraft and their units and to accept the final products.
ISO 19683:2017 places emphasis on achieving reliability against infant mortality after satellite launch to orbit while maintaining low cost and fast delivery.
ISO 19683:2017 is applied to satellites whose development methods are different from the ones used for traditional satellites that have little room for risk tolerance, as shown in Figure 1. The scope of this document encompasses different categories of small spacecraft, so-called mini-, micro, nano-, pico- and femto-, as well as CubeSat, spacecraft. Therefore, for the sake of convenience, the term "small spacecraft" is used throughout this document as a generic term.
ISO 19683:2017 includes CubeSat, as long as it is developed with the untraditional processes.
|
Published |
2017-07 |
Edition : 1 |
Number of pages : 85 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 19826:2017 |
Space systems — Programme management — Management of product characteristics |
ISO 19826:2017 defines management requirements of product characteristics, including their classification, in order to highlight those areas of the product to which specific attention, control or inspections are applied.
ISO 19826:2017 is applicable to direct implementation of space product characteristic management, especially for mechanical parts and fluidic equipment.
|
Published |
2017-02 |
Edition : 1 |
Number of pages : 13 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 19933:2007 |
Space systems — Format for spacecraft launch environment test report |
ISO 19933:2007 provides a specific format to report the test process and results of spacecraft (SC) qualification to the launch environment. The following types of tests are considered:
static load;
modal survey;
sine vibration;
acoustic noise;
random vibration;
shock; and
electromagnetic compatibility (EMC).
The definition of test specifications and test requirements are derived from launch vehicle (LV) user's manuals as defined in ISO 14303. Only those tests that are intended to demonstrate the compliance of a given SC design with its LV environment are taken into consideration.
|
Published |
2007-07 |
Edition : 1 |
Number of pages : 19 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 19971:2018 |
Space systems — Spacecraft and launch vehicle combined operation plan (COP) at launch site — General format |
ISO 19971:2018 provides general format for spacecraft and launch vehicle Combined Operation Plan (COP).
|
Published |
2018-01 |
Edition : 1 |
Number of pages : 15 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 20104:2015 |
Space data and information transfer systems — Producer-Archive Interface Specification (PAIS) |
ISO 20104:2015 is to provide a standard method for formally defining the digital information objects to be transferred by an information Producer to an Archive and for effectively packaging these objects in the form of Submission Information Packages (SIPs). This supports effective transfer and validation of SIP data.
ISO 20104:2015 fits into the context defined by:
? The Reference Model for an Open Archival Information System (OAIS) Recommended Standard (see reference [3]).
? The Producer-Archive Interface Methodology Abstract Standard (PAIMAS) Recommended Standard (see reference [2]).
? The XML Formatted Data Unit (XFDU) Structure and Construction Rules Recommended Standard (see reference [1]).
The PAIMAS Recommended Standard (see reference [2]) defines a methodology based on the four following phases: Preliminary, Formal Definition, Transfer, Validation.
ISO 20104:2015 applies specifically to the implementation of the main part of the Formal Definition Phase and the Transfer Phase, taking into account part of the Validation Phase.
The proposed implementation should help in the automation and management of the Transfer and Validation Phases.
The proposed implementation may also be used, to some extent, for the Preliminary Phase.
ISO 20104:2015 does not exclude other PAIMAS implementation Recommended Standards.
|
Published |
2015-08 |
Edition : 1 |
Number of pages : 94 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 20105:2015 |
Space data and information transfer systems — Operation of CFDP over encapsulation service |
The CCSDS File Delivery Protocol (CFDP?reference [1]) has been designed to support the transfer of files in a variety of mission scenarios. CFDP offers different qualities of service ranging from best effort to fully reliable and has been specifically optimized for long delay, noisy, and disjoint links. CFDP requires a simple minimum service from the underlying protocols, operating over any link providing a packet communication service.
ISO 20105:2015 is to specify how to operate CFDP over the CCSDS Encapsulation Service (reference [2]) as provided for Earth-to-spacecraft, spacecraft-to-Earth, and spacecraft-to-spacecraft communications. It sets out the communications architecture for CFDP operating over the Encapsulation Service. It describes the service expected by CFDP of the underlying layers and reconciles this with the service provided by the Encapsulation Service.
|
Published |
2015-08 |
Edition : 1 |
Number of pages : 14 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 20106:2015 |
Space data and information transfer systems — Mission operations common object model |
ISO 20106:2015 defines, in an abstract manner, the COM in terms of:
a) the operations necessary to provide the service;
b) the parameter data associated with each operation;
c) the required behaviour of each operation;
d) the use of the model.
It does not specify:
a) individual implementations or products;
b) the implementation of entities or interfaces within real systems;
c) the methods or technologies required for communications.
|
Published |
2015-08 |
Edition : 1 |
Number of pages : 56 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 20107:2015 |
Space data and information transfer systems — Spacecraft onboard interface services — Device virtualization service |
ISO 20107:2015 is one of a family of documents specifying the Spacecraft Onboard Interface Services (SOIS)-compliant service to be provided in support of applications.
ISO 20107:2015 defines the SOIS Device Virtualisation Service (DVS). The definition encompasses specification of the service interface exposed to onboard software (user applications and libraries) as well as the conceptual mapping of the DVS primitives to the protocols implementing such services.
The SOIS DVS is for use by onboard software to provide a standard interface between onboard software applications and flight hardware such as sensors and actuators.
|
Withdrawn |
2015-08 |
Edition : 1 |
Number of pages : 22 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 20188:2018 |
Space systems — Product assurance requirements for commercial satellites |
ISO 20188:2018 provides the recommended practices of product assurance (PA) requirements applicable to commercial satellite.
|
Published |
2018-01 |
Edition : 1 |
Number of pages : 34 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 20205:2015 |
Space data and information transfer systems — Spacecraft Onboard Interface Systems — Low Data-Rate Wireless Communications for Spacecraft Monitoring and Control |
ISO 20205:2015 is targeted towards monitoring and control systems, typically low data-rate and low-power wireless-based applications.
|
Published |
2015-08 |
Edition : 1 |
Number of pages : 27 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 20207:2015 |
Space data and information transfer systems — CCSDS Space Link Protocols over ETSI DVB-S2 Standard |
The DVB-S2 standard (reference [1]) proposes advanced modulation techniques (QPSK, 8PSK, 16APSK, and 32APSK) and a wide range of coding rates (from 1/4 to 9/10) with near-Shannon coding schemes (LDPC codes). This high number of modulation and coding schemes allows a wide range of possibilities to satisfy specific mission constraints.
Moreover, to maximize the telemetry system throughput, it appears possible to adapt the transmitted waveform (and the useful data rate) to the variable conditions of the link. The DVB-S2 standard can actually implement Variable Coding and Modulation (VCM) mode, which adapts the transmission scheme to the channel conditions following a predetermined schedule (for example, following a dynamic link budget). When a channel is available to provide feedback (e.g., via a telecommand link), the transmission scheme can be dynamically adjusted using the Adaptive Coding and Modulation (ACM) mode.
The use of the DVB-S2 standard for telemetry makes possible the use of generic Very High Scale Integrated Circuits (VHSIC) Hardware Description Language (VHDL) Intellectual Property (IP) modules for developments. The use of a widely implemented standard simplifies finding transmitting or receiving equipment to check compatibility. Finally, for the ground part, some telecom DVB-S2 receivers or Application Specific Integrated Circuits (ASICs) developed for the telecom market could be reused.
ISO 20207:2015 is an adaptation profile describing how to use the DVB-S2 standard to transmit CCSDS Transfer Frames for telemetry purpose. The interface between CCSDS and DVB-S2 is based on the Attached Synchronization Marker (ASM) and Channel Access Data Unit (CADU) already introduced in reference [2].
DVB-S2 is used in this adaptation profile as a complete and self-sufficient standard, and definitions and specifications taken from DVB-S2 are applicable only in the context of this Recommended Standard. However, individual DVB-S2 functions or components (e.g., VCM/ACM, 8-PSK, and higher-order modulations) might be reused, redefined, and/or respecified by CCSDS in future Recommended Standards.
|
Published |
2015-08 |
Edition : 1 |
Number of pages : 23 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 20208:2015 |
Space data and information transfer systems — Delta-DOR Raw Data Exchange Format |
Delta-DOR (Delta Differential One-Way Ranging) is a Very Long Baseline Interferometry (VLBI) technique that can be used in conjunction with Doppler and ranging data to improve spacecraft navigation by more efficiently determining spacecraft angular position in the plane of sky. It involves the use of multiple ground stations, possibly belonging to different agencies, for simultaneous acquisition of either spacecraft or quasar signals (see reference [D2]).
This Delta-DOR Raw Data Exchange Format (RDEF) Recommended Standard specifies a standard format for use in exchanging Delta-DOR raw data among space agencies. Delta-DOR raw data exchange is required every time the data correlation involves at least one participating station not belonging to the agency responsible for the correlation. ISO 20208:2015 includes specifications on the parameter fields that the data format has been designed to meet. For exchanges where these specifications do not capture the needs of the participating agencies another mechanism may be selected.
|
Published |
2015-08 |
Edition : 1 |
Number of pages : 39 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 20210:2015 |
Space data and information transfer systems — Mission Operations Message Abstraction Layer - JAVA API |
ISO 20210:2015 is the definition of all concepts and terms that establish a Java API for consuming and providing MO services on top of the MAL. The MAL Java API is intended to maximize the portability of the MO components across various underlying MAL implementations and transport protocols.
|
Published |
2015-08 |
Edition : 1 |
Number of pages : 276 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 20211:2015 |
Space data and information transfer systems — Spacecraft Onboard Interface Services — Device Access Service |
ISO 20211:2015 is one of a family of documents specifying the Spacecraft Onboard Interface Services (SOIS)-compliant service to be provided in support of applications.
ISO 20211:2015 is to define services and service interfaces provided by the SOIS Device Access Service (DAS). Its scope is to specify the service only and not to specify methods of providing the service, although use of the SOIS subnetwork services is assumed.
ISO 20211:2015 conforms to the principles set out in the SOIS Green Book (reference [D3]) and is intended to be applied together with it.
|
Withdrawn |
2015-08 |
Edition : 1 |
Number of pages : 22 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 20213:2015 |
Space data and information transfer systems — Spacecraft onboard interface services — Message transfer service |
ISO 20213:2015 is one of a family of documents specifying the Spacecraft Onboard Interface Services (SOIS)-compliant services to be provided in support of onboard applications.
ISO 20213:2015 is to define services and service interfaces provided by the SOIS Message Transfer Service. Its scope is to specify the service only and not to specify methods of providing the service, although use of the SOIS subnetwork services is assumed.
ISO 20213:2015 conforms to the principles set out in the SOIS Green Book (reference [C2]) and should not be applied without first consulting this reference.
|
Withdrawn |
2015-08 |
Edition : 1 |
Number of pages : 31 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 20214:2015 |
Space data and information transfer systems — Security architecture for space data systems |
ISO 20214:2015 is intended as a high-level systems engineering reference to enable engineers to better understand the layered security concepts required to secure a space system. As such, this document is a Security Architecture for Space Data Systems (SASDS).
This architecture uses the views described in the Reference Architecture for Space Data Systems (reference [B1]) developed by the CCSDS Architecture Working Group.
The SASDS will be used:
? to establish an overall CCSDS conceptual framework for the incorporation of security into the data systems of space missions;
? to define common language and representation so that risks, requirements, and solutions in the area of security within space data systems can be readily communicated;
? to provide a source of information for the security architects on a space mission to use to develop the system security design;
? to facilitate development of standards in a consistent way so that any standard can be used with other appropriate standards in a system.
|
Published |
2015-08 |
Edition : 1 |
Number of pages : 39 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 20215:2015 |
Space data and information transfer systems — CCSDS cryptographic algorithms |
The algorithms contained in ISO 20215:2015 are recommended for use on space missions with a requirement for information (e.g., data, voice, and video) confidentiality, authentication, or authenticated confidentiality. The algorithms may be employed on any or all mission communications links such as the forward space link (e.g., telecommand), the return space link (e.g., telemetry, science data), as well as across the ground data network. They could as well be used to ensure confidentiality and authenticity of stored data.
A symmetric algorithm assumes that all communicating entities possess a shared secret (i.e., a ?key') which enables them to encrypt, decrypt, and authenticate information shared among them. The manner in which the shared secret is distributed and managed (key management) is not within the scope of this document. Further information on key management can be found in Space Missions Key Management Concept (reference [B22]).
|
Published |
2015-08 |
Edition : 1 |
Number of pages : 19 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 20216:2015 |
Space data and information transfer systems — Spacecraft onboard interface services — Device data pooling service |
ISO 20216:2015 is one of a family of documents specifying Spacecraft Onboard Interface Services (SOIS)-compliant service to be provided to onboard applications.
ISO 20216:2015 is to define the services and service interfaces provided by the SOIS Device Data Pooling Service (DDPS). Its scope is to specify the service only and not to specify methods of providing the service, although use of the SOIS subnetwork services is assumed.
ISO 20216:2015 conforms to the principles set out in the SOIS Green Book (reference [C2]) and is intended to be applied together with it.
|
Withdrawn |
2015-08 |
Edition : 1 |
Number of pages : 31 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 20217:2015 |
Space data and information transfer systems — Spacecraft onboard interface services — File and packet store services |
ISO 20217:2015 defines the Spacecraft Onboard Interface Services (SOIS) File and Packet Store Services (FPSS). The definition encompasses specification of the service interface exposed to onboard software (user applications and libraries) as well as the conceptual mapping of the FPSS primitives to the protocols implementing such services.
The SOIS File and Packet Store Services are for use by onboard software to:
? Access, and manage files residing in a file store. The files residing in the file store could contain any type of data, including for example telemetry, commands and command sequences, software updates, imagery, and other science observations.
? Access and manage packets residing in a packet store. It should be noted that the packet store may or may not be aware of, and its actions may or may not be informed by, the contents of a packet.
To achieve this, the FPSS comprise the following services:
? File Access Service (FAS);
? File Management Service (FMS);
? Packet Store Access Service (PSAS);
? Packet Store Management Service (PSMS).
It should be noted that the SOIS File and Packet Store Services do NOT define the file and packet stores themselves, but only their minimum provided service. The initialization and configuration of the file and packet stores is out of scope for this document.
|
Withdrawn |
2015-08 |
Edition : 1 |
Number of pages : 118 |
Technical Committee |
49.140
Space systems and operations
|
| ISO/TR 20590:2017 |
Space systems - Debris mitigation design and operation manual for launch vehicle orbital stages |
ISO/TR 20590:2017 contains non-normative information on the design and operational practices for launch vehicle orbital stages for mitigating space debris.
ISO/TR 20590:2017 can be used to guide engineers in the application of the family of space debris mitigation standards (see 4.2) to reduce the growth of space debris by ensuring that launch vehicle orbital stages are designed, operated, and disposed of in a manner that prevents them from generating debris throughout their orbital lifetime.
|
Withdrawn |
2017-02 |
Edition : 1 |
Number of pages : 33 |
Technical Committee |
49.140
Space systems and operations
|
| ISO/TR 20590:2021 |
Space systems — Space debris mitigation design and operation manual for launch vehicle orbital stages |
This document contains information on the design and operational practices for launch vehicle orbital stages for mitigating space debris.
This document provides information to engineers on the requirements and recommendations in the space debris mitigation standards to reduce the growth of space debris by ensuring that launch vehicle orbital stages are designed, operated, and disposed of in a manner that prevents them from generating debris throughout their orbital lifetime.
|
Published |
2021-04 |
Edition : 2 |
Number of pages : 31 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 20618:2015 |
Space data and information transfer systems — Spacecraft onboard interface services — Device enumeration service |
ISO 20618:2015 is one of a family of documents specifying the Spacecraft Onboard Interface Services (SOIS)-compliant service to be provided in support of applications.
The purpose of this document is to define services and service interfaces provided by the SOIS Device Enumeration Service (DES). Its scope is to specify the service only and not to specify methods of providing the service, although use of the SOIS subnetwork services is assumed.
ISO 20618:2015 conforms to the principles set out in the SOIS Green Book (reference [D3]) and is intended to be applied together with it.
|
Withdrawn |
2015-12 |
Edition : 1 |
Number of pages : 41 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 21350:2007 |
Space systems — Off-the-shelf item utilization |
ISO 21350:2007 contains requirements and guidelines for the utilization of off-the-shelf (OTS) items, their selection, acquisition, integration, qualification and implementation related to a space product or system.
Specifically excluded are piece parts and materials, such as electrical, electronic and electromechanical (EEE) parts, thermocouples, rivets, fasteners, connectors, fittings, adhesives, insulation, wiring and plumbing.
|
Published |
2007-09 |
Edition : 1 |
Number of pages : 14 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 20652:2006 |
Space data and information transfer systems — Producer-archive interface — Methodology abstract standard |
ISO 20652:2006 identifies, defines and provides structure to the relationships and interactions between an information producer and an archive. It defines the methodology for the structure of actions that are required from the initial time of contact between the producer and the archive until the objects of information are received and validated by the archive. These actions cover the first stage of the ingest process as defined in the open archival information system (OAIS) reference model (see ISO 14721). ISO 20652:2006 describes parts of the functional entities administration ('negotiate submission agreement') and ingest ('receive submission' and 'quality assurance').
|
Published |
2006-02 |
Edition : 1 |
Number of pages : 79 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 20780:2018 |
Space systems — Fiber optic components — Design and verification requirements |
This document specifies requirements for the design and verification of fibre optic components used in space fibre optic sub-systems. In this document, the requirements are established to assure the reliability and environmental adaptability of fibre optic components in space environmental conditions. These are in a range of applications such as ground systems, unmanned applications and manned systems. This document suggests a set of requirements to be applied to the selection of space fibre optic components.
|
Published |
2018-06 |
Edition : 1 |
Number of pages : 17 |
Technical Committee |
49.140
Space systems and operations
|
| ISO/TR 20891:2020 |
Space systems — Space batteries — Guidelines for in-flight health assessment of lithium-ion batteries |
This document provides detailed information on the various methods of assessing the health status of lithium-ion space batteries in flight and makes recommendations to battery suppliers, spacecraft manufacturers and operators to ease this assessment.
|
Published |
2020-10 |
Edition : 1 |
Number of pages : 54 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 20892:2018 |
Space systems — Launch complexes modernization process — General requirements |
ISO 20892:2017 specifies procedures in the preparation and carrying out of the modernization process of launch complexes and their components. These procedures are devised in case there is a need to make changes in existing configuration of launch complexes.
ISO 20892:2017 establishes the following:
a) modernization stages;
b) modernization performance requirements;
c) functions of the main participants of the modernization process and their interactions.
The requirements specified in this document are used by organizations involved in the modernization of the launch complexes.
ISO 20892:2017 is directly aimed at increasing economic efficiency in terms of the modernization process in creating new vehicles or changing the specification of a launch complex by a service customer, etc., or whether or not there is a need to build a new launch complex.
ISO 20892:2017 is also aimed at providing safety and health requirements for LC personnel, since increased demand for launch complex safety may be one reason to modernize the facility.
ISO 20892:2017 offers a unified approach to the management of the modernization process (preparation and carrying out). Since there are no specific requirements and data, target dates for the carrying out of the modernization process can be flexible.
|
Published |
2018-02 |
Edition : 1 |
Number of pages : 7 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 20893:2021 |
Space systems — Detailed space debris mitigation requirements for launch vehicle orbital stages |
This document defines detailed space debris mitigation requirements and recommendations for the design and operation of launch vehicle orbital stages in Earth orbit.
The requirements defined in this document are applicable for:
— avoiding the release of space debris;
— disposing of a launch vehicle orbital stage after the end of its mission so as to avoid a break-up in orbit;
— disposing of a launch vehicle orbital stage after the end of its mission so as to minimize interference with the protected regions;
— safely re-entering a launch vehicle orbital stage.
|
Published |
2021-02 |
Edition : 1 |
Number of pages : 8 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 20930:2018 |
Space systems — Calibration requirements for satellite-based passive microwave sensors |
This document defines the requirements and verification methods from design to on-orbit operation for Satellite Based Passive Microwave Sensors.
This document covers the requirements for, design, analysis, manufacturing, ground tests and on-orbit self-sensor calibration and validation. In addition, this document includes the conditions considered for on-orbit inter-comparison among sensors as preparation for cross-calibration. This document includes some examples on how to apply the development of passive microwave sensors as shown in Annex A through D.
|
Published |
2018-07 |
Edition : 1 |
Number of pages : 26 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 21350 |
Space systems — Off-the-shelf item utilization |
ISO 21350:2007 contains requirements and guidelines for the utilization of off-the-shelf (OTS) items, their selection, acquisition, integration, qualification and implementation related to a space product or system.
Specifically excluded are piece parts and materials, such as electrical, electronic and electromechanical (EEE) parts, thermocouples, rivets, fasteners, connectors, fittings, adhesives, insulation, wiring and plumbing.
|
Under development |
2023-04 |
Edition : 2 |
|
Technical Committee |
49.140
Space systems and operations
|
| ISO 21351:2005 |
Space systems — Functional and technical specifications |
ISO 21351:2005 provides an overview of the respective purposes and positions of functional and technical specifications, their required contents, and the process for developing these documents.
ISO 21351:2005 is applicable to all types of space systems, all product elements, and projects.
|
Published |
2005-05 |
Edition : 1 |
Number of pages : 17 |
Technical Committee |
49.140
Space systems and operations
|
| ISO/TS 20991:2018 |
Space systems — Requirements for small spacecraft |
This document describes minimum requirements for small spacecraft.
Small spacecraft may employ untraditional spacecraft development and management philosophy. These spacecraft projects are usually budget-limited or mass-limited, which makes a single (exclusive) launch unaffordable.
The scope of this document encompasses different categories of small spacecraft — so-called mini-, micro-, nano-, pico- and femto-, as well as CubeSat, spacecraft. Therefore, for the sake of convenience, the term "small spacecraft" is used throughout this document as a generic term.
Regardless of the development philosophy, there are minimum requirements every spacecraft complies with. This document explicitly states those requirements and also refers to existing applicable standards. In that sense, this document serves as the top document to cover the minimum requirements for various stages of small spacecraft system life-cycle — with emphasis on design, launch, deployment, operation, and disposal phases. In this way, (1) safety, (2) harmlessness to co-passengers and launcher, and (3) debris mitigation, are all assured.
This document is addressed to small spacecraft developers, as well as dispenser providers and/or the launch operators.
|
Published |
2018-07 |
Edition : 1 |
Number of pages : 6 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 21076:2016 |
Space data and information transfer systems — Space communications cross support — Architecture requirements document |
ISO 21076:2016 describes SCCS architecture in terms of the following:
- definitions of all key elements, on ground and in space, that are involved in space communications;
- definitions of concepts that characterize SCCS services;
- requirements on system elements and components that provide secure SCCS services;
- recommended protocol stack configurations for each element type; and
- recommended end-to-end system configurations to provide interoperable and cross-supportable space communications services.
ISO 21076:2016 does not specify:
- the details of how to implement systems that provide SCCS services;
- explicit technologies needed to implement SCCS services;
- application or mission operations protocols except for those used for data transfer;
- mission operations except for those involved in planning, scheduling, and executing space communications;
- spacecraft onboard cross support, except for space communication services.
ISO 21076:2016 contains references to other CCSDS technical engineering and architectural recommendations describing how systems doing space communication cross support should be engineered, deployed, organized, and operated to provide interoperable SCCS services. While this document does not specify detailed internal implementation approaches, which are a private matter, it does recommend specific protocols and protocol stacks, service interfaces, element behaviors, and end-to-end architectures.
Some of the standards that are referenced in this document, especially those relating to the SSI, are still in development. They are included here so the reader gets a clear understanding of how they fit into an overall architecture.
The protocol-related parts of this document make liberal reference to the layers defined in the Open Systems Interconnection (OSI) Basic Reference Model (reference [4]). Subsection 6.2 of the Architecture Description Document (ADD) (reference [D5]) contains a discussion of the OSI stack and the functions associated with each layer.
The technical scope of single-hop cross support is the provision of Data Link Layer (Layer 2) data communications services across the Solar System in support of space mission users, using the interoperable infrastructure of one or more space agencies. Services above the Data Link Layer, such as CCSDS File Delivery Protocol (CFDP), Cross-Support File Service (CXFS), or Delta-Differential One-way Range (DOR), may also be provided. All mission operations application in CCSDS-compliant, interoperable, single-hop deployments are expected to utilize these underlying space link and file communications layers.
The technical scope of the SSI is the provision of internetworked (Layer 3) data communications services across the Solar System in support of space mission users, using the confederated and interoperable infrastructure of one or more space agencies to achieve a level of service that individual agencies would otherwise be unlikely to achieve. All mission operations application in CCSDS-compliant, interoperable, SSI deployments are expected to utilize these underlying space internetworking communications layers.
The temporal scope of this document covers current, single-hop, secure interoperable cross support installations, future deployments of an interoperable and evolving space networking infrastructure, and the transition strategies to evolve from current deployments to a future SSI state. Included in this discussion are mission-driven considerations, such as use of hybrid science/routing missions, as well as identification of optional configurations that are considered acceptable because they are in line with the transition strategies defined in this document.
Any agency that wishes to participate as a peer in the SSI should implement interoperable services and interfaces at least up to the Network Layer, along with related support services, as described in this document and specified in the relevant CCSDS and Internet standards. Agencies that are not yet ready to adopt the SSI themselves, but that wish to offer compliant ground station cross support services that can support SSI services, may also take advantage of this document for guidance on developing Data Link Layer services that will both meet their immediate needs and also interoperate with SSI-enabled missions.
|
Published |
2016-07 |
Edition : 1 |
Number of pages : 146 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 21077:2016 |
Space data and information transfer systems — Digital motion imagery |
The purpose of ISO 21077:2016 is to provide a common reference and framework of standards for digital motion video and imagery, and to provide recommendations for utilization of international standards for sharing or distributing motion video and imagery between spacecraft elements and ground systems.
The scope of ISO 21077:2016 includes traditional real-time streaming video and television, including human and robotic spacecraft-to-spacecraft and spacecraft-to-ground systems, as well as video recorded and distributed later, either as a real-time stream or as a file transfer. In this context, real-time streaming includes all modes where video is sent from a spacecraft in a continuous stream and is intended for immediate use when received, regardless of the latency of the transmission path. Other specialized motion imagery applications, such as high-speed scientific motion imagery and multi-spectral motion imagery, are not addressed in this document. However, if a specialized imagery camera system has a requirement to interface to spacecraft systems in a video mode, it would be required to match these interfaces.
Ground-systems-to-ground-systems video distribution is obviously a key component of the entire video system. However, this is not the primary focus of this document. Currently, there are significant differences in the ways mission video products are exchanged between the various space agencies on the ground. This is the result of differences in network topologies between space agencies, and agreements for video sharing. Those differences preclude there being a standard methodology for delivering video imagery between agencies. Prior to the commencement of video transmission between space agencies, system design reviews and performance testing should be done between the ground systems in use to assure operability when video imagery comes from spacecraft.
|
Withdrawn |
2016-07 |
Edition : 1 |
Number of pages : 33 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 21077:2021 |
Space data and information transfer systems — Digital motion imagery |
The purpose of this document is to provide a common reference and framework of standards for digital motion video and imagery, and to provide recommendations for utilization of international standards for sharing or distributing motion video and imagery between spacecraft elements and ground systems.
The scope of this document includes traditional real-time streaming video and television, including human and robotic spacecraft-to-spacecraft and spacecraft-to-ground systems, as well as video recorded and distributed later, either as a real-time stream or as a file transfer. In this context, real-time streaming includes all modes where video is sent from a spacecraft in a continuous stream and is intended for immediate use when received, regardless of the latency of the transmission path. Other specialized motion imagery applications, such as high-speed scientific motion imagery and multi-spectral motion imagery, are not addressed in this document. However, if a specialized imagery camera system has a requirement to interface to spacecraft systems in a video mode, it would be required to match these interfaces.
Ground-systems-to-ground-systems video distribution is obviously a key component of the entire video system. However, this is not the primary focus of this document. Currently, there are significant differences in the ways mission video products are exchanged between the various space agencies on the ground. This is the result of differences in network topologies between space agencies, and agreements for video sharing. Those differences preclude there being a standard methodology for delivering video imagery between agencies. Prior to the commencement of video transmission between space agencies, system design reviews and performance testing should be done between the ground systems in use to assure operability when video imagery comes from spacecraft.
|
Published |
2021-06 |
Edition : 2 |
Number of pages : 34 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 21080:2016 |
Space data and information transfer systems — Licklider transmission protocol (LTP) for CCSDS |
1.1 Purpose ISO 21080:2016 defines a Recommended Standard for the CCSDS Licklider Transmission Protocol (LTP) and associated service for application in the space environment. LTP provides optional reliability mechanisms on top of an underlying (usually data link) communication service.
1.2 Scope LTP 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.
For space data links, LTP will typically be deployed over a CCSDS data link that supports CCSDS Encapsulation Packets so that one LTP segment can be encapsulated in a single Encapsulation Packet. LTP may also operate over a wide variety of ground-network services including those specified by the CCSDS for cross-support purposes.
|
Published |
2016-07 |
Edition : 1 |
Number of pages : 57 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 21082:2016 |
Mission operations — MAL space packet transport binding and binary encoding |
The scope of ISO 21082:2016 is the specification of the binding in terms of technology mapping to the Space Packet Protocol of:
a) MAL message;
b) MAL Transport Interface.
The MAL Blue Book (reference [2]) specifies the MAL protocol in an abstract way, i.e., without defining the concrete protocol data units. The MAL Space Packet Transport Binding and Binary Encoding specifies:
a) a complete and unambiguous mapping of the MAL message to the Space Packet;
b) a complete and unambiguous mapping of the MAL transport interface to the Space Packet Protocol interface;
c) a complete and unambiguous mapping of the MAL data types to fixed and variable length binary encoding formats.
This Recommended Standard does not specify:
a) individual implementations or products;
b) the implementation of entities or interfaces within real systems.
MO services defined in terms of MAL using the Space Packet Transport Binding as defined in this Recommended Standard are fully interoperable.
|
Published |
2016-07 |
Edition : 1 |
Number of pages : 62 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 21323:2016 |
Space data and information transfer systems — CCSDS Bundle protocol specification |
ISO 21323:2016 is designed to be applicable to any kind of space mission or infrastructure that is communication-resource poor and is subject to long latencies and/or temporary network partitions, regardless of complexity. It is intended that this Recommended Standard become a uniform standard among all CCSDS Agencies. In addition, this specification exists to utilize the underlying service of various internetworking protocols both onboard and in transit between ground and space-based assets.
ISO 21323:2016 is intended to be applied to all systems that claim conformance to the CCSDS Bundle Protocol. It is agnostic to the choice of underlying transmission protocol in that BP can function over AOS, Space Packet, Proximity-1 Space Link Protocol, and various Internet and ground based protocols.
The CCSDS believes it is important to document the rationale underlying the recommendations chosen, so that future evaluations of proposed changes or improvements will not lose sight of previous decisions. The concept and rationale for the use of a bundle protocol in space links may be found in reference [H1].
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Published |
2016-11 |
Edition : 1 |
Number of pages : 84 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 21324:2016 |
Space data and information transfer systems — Space data link security protocol |
The purpose of ISO 21324:2016 is to specify the Space Data Link Security Protocol (hereafter referred as the Security Protocol) for CCSDS data links. This protocol provides a security header and trailer along with associated procedures that may be used with the CCSDS Telemetry, Telecommand, and Advanced Orbiting Systems Space Data Link Protocols (references [1]-[3]) to provide a structured method for applying data authentication and/or data confidentiality at the Data Link Layer.
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Published |
2016-11 |
Edition : 1 |
Number of pages : 61 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 21347:2005 |
Space systems — Fracture and damage control |
ISO 21347:2005 establishes general requirements for the application of fracture control technology to fracture critical items (FCIs) fabricated by metallic, non-metallic or composite materials. It also establishes mechanical damage control requirements for mechanical damage critical items (MDCIs) fabricated by composite materials. These requirements, when implemented on a particular space system, may assure a high level of confidence in achieving safe operation and mission success.
The requirements set forth in ISO 21347:2005 are the minimum fracture control and mechanical damage control requirements for FCIs and MDCIs in general space systems, including launch vehicles and spacecraft. With necessary modifications, these requirements may also be applicable to reusable launch vehicles (RLVs). ISO 21347:2005 is not applicable to the NASA Space Shuttle and its payloads or the International Space Station and its equipment since they already have a set of specific requirements suitable for their special applications.
ISO 21347:2005 is not applicable in processing detected defects.
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Published |
2005-05 |
Edition : 1 |
Number of pages : 20 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 21348:2007 |
Space environment (natural and artificial) — Process for determining solar irradiances |
ISO 21348:2007 specifies the process for determining solar irradiances and is applicable to measurement sets, reference spectra, empirical models, theoretical models, and solar irradiance proxies or indices that provide solar irradiance products representing parts or all of the solar electromagnetic spectrum. Its purpose is to create a standard method for specifying all solar irradiances for use by space systems and materials users.
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Published |
2007-05 |
Edition : 1 |
Number of pages : 12 |
Technical Committee |
49.140
Space systems and operations
|
| ISO 21349:2007 |
Space systems — Project reviews |
ISO 21349:2007 provides process requirements for project reviews as a set of required functions. The requirements and recommendations cover the function inputs, outputs, mechanisms, and controlling conditions. It is intended for use in implementing the review requirements of ISO 14300-1, ISO 14300-2, ISO 15865, and such other space systems and operations standards that require formal reviews.
ISO 21349:2007 specifies the responsibilities of a review board and gives guidance concerning review board composition.
ISO 21349:2007 is applicable to reviews for a project at any level within a larger project, as well as for major milestone reviews at the top level of a major project. It is intended to be used either by an independent developer as a basis for enterprise processes, or as a basis for an agreement between a supplier and a customer.
ISO 21349:2007 also provides normative descriptions of the kinds of reviews that are commonly useful in assuring the success of a space project.
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Published |
2007-07 |
Edition : 1 |
Number of pages : 19 |
Technical Committee |
49.140
Space systems and operations
|