49.140 - Space systems and operations
ICS 49.140 Details
Space systems and operations
Raumfahrtsysteme. Raumfahrtoperationen
Systemes spatiaux, développement et mise en oeuvre
Vesoljski sistemi in operacije
General Information
e-Library Subscription
Create subscription and get permanent access to documents within 49.140 - Space systems and operations
Currently subscription includes documents marked with .We are working on making all documents available within the subscription.
This document presents the requirements and recommendations for the management of systems engineering for space systems. This document addresses the systems engineering activities and provides guidelines for interfacing with specific major management subjects (e.g. configuration management, data management, interface management, risk management, requirements management, and integrated logistics support). This document establishes a common reference for all customers and suppliers in the space sector to work with management of systems engineering for all space products and projects. This document does not describe in detail the standard systems engineering process or project management process for all types of space systems.
- Standard16 pagesEnglish languagesale 15% off
This document defines requirements and recommendations to be used for the management of cybersecurity in space systems. Space systems include manned and unmanned spacecraft, launcher, payload, experiment, ground equipment and any other space facilities. This document describes the processes, techniques, and responsibilities for managing the cybersecurity, ways to prevent and mitigate accidents and incidents. This document addresses systems engineering activities and provides requirements and recommendations for security engineering. This document establishes a common reference for the space sector to work to manage the systems engineering issues related to cybersecurity for all space products, services and projects. This document doesn't describe in detail the systems engineering processes or related project management processes, or detailed requirements or processes for cybersecurity.
- Technical specification8 pagesEnglish languagesale 15% off
This document contains internationally accepted descriptions of the main phenomena of space weather, including its sources and effects upon space systems. This document is applicable for a variety of engineering and scientific domains. It is applicable to space system operations include ground-based, on-orbit, and deep space automated satellite operations. It can be applied by developers of software systems for space systems, designers of space systems, and launchers of space systems.
- Technical report29 pagesEnglish languagesale 15% off
This document provides technical methods to calculate the precipitation efficiency and liability of a flight model by measuring the screening effectiveness of thermal cycles. This document is applicable to the recurring production unit and other hardware assembly levels, as either an option to reduce or a method to tailor the baseline number of cycles for thermal vacuum and thermal cycle acceptance tests.
- Standard16 pagesEnglish languagesale 15% off
This document specifies a procedure for determining the loading level of a qualification test of a launch vehicle structure and takes into account all the minimum allowable strength characteristics necessary for these structures.
- Standard6 pagesEnglish languagesale 15% off
This document describes the effective vertical cut-off rigidities of charged particles for near-Earth space and establishes principal requirements for their calculation based on different models of Earth’s geomagnetic field.[1] The techniques are useful for determination of penetrating into the Earth's magnetosphere by charged particle fluxes, as well as for test and estimations of the impact on spacecrafts and other equipment in the near-Earth space.
- Standard14 pagesEnglish languagesale 15% off
This document provides requirements for the determination of maximum stress and corresponding margin of safety under loading and defines criteria for static strength failure modes, such as rupture, collapse and detrimental yielding. This document does not cover critical-conditions-induced fatigue, creep and crack growths. Notwithstanding these limitations in scope, the results of stress calculations based on the requirements of this document are applicable to other critical condition analysis. This document is applicable to the determination of the stress/strain distribution and margins of safety in launch vehicles and spacecraft load-bearing elements design. Liquid propellant engine structures, solid propellant engine nozzles and the solid propellant itself are not covered, but liquid propellant tanks, pressure vessels and solid propellant cases are within the scope of this document. In accordance with the requirements of this document, the models, methods and procedures for stress calculation can also be applicable to the displacements and deformation calculation, as well as the calculation of loads, applied to substructures and structural elements under consideration. When this document is applied, it is assumed that temperature distribution has been determined and is used as input data.
- Standard14 pagesEnglish languagesale 15% off
This document describes a process for the long-duration orbit lifetime prediction of orbit lifetime for spacecraft, launch vehicles, upper stages and associated debris in LEO-crossing orbits after mission phase (including any mission lifetime extensions). The document also clarifies: a) modelling approaches and resources for solar and geomagnetic activity modelling; b) resources for atmosphere model selection; c) approaches for spacecraft ballistic coefficient estimation.
- Standard48 pagesEnglish languagesale 15% off
This document specifies design and minimum verification requirements for lithium-ion batteries from the perspectives of performance, safety and logistics. This document is applicable to battery assemblies for space vehicles and component cells of batteries, which are critical devices to be harmonized with standards and regulations for other industries. In addition, this document is applicable to component cells which are not designed for space vehicles but can be used in space.
- Standard55 pagesEnglish languagesale 15% off
This document specifies four standard message formats for use in transferring spacecraft orbit information between space agencies and commercial or governmental spacecraft operators: The Orbit Parameter Message (OPM), the Orbit Mean-Elements Message (OMM), the Orbit Ephemeris Message (OEM), and the Orbit Comprehensive Message (OCM). Such exchanges are used for: a) pre-flight planning for tracking or navigation support; b) scheduling tracking support; c) carrying out tracking operations (sometimes called metric predicts); d) performing orbit comparisons; e) carrying out navigation operations such as orbit propagation and orbit reconstruction; f) assessing mutual physical and electromagnetic interference among satellites orbiting the same celestial body (primarily Earth, Moon, and Mars at present); g) performing orbit conjunction (collision avoidance) studies; and h) developing and executing collaborative maneuvers to mitigate interference or enhance mutual operations. This document includes sets of requirements and criteria that the message formats have been designed to meet. For exchanges in which these requirements do not capture the needs of the participating agencies and satellite operators, another mechanism may be selected. This document is an international standard published under the auspices of CCSDS and International Standards Organization (ISO) Technical Committee 20, Subcommittee 13, developed jointly and in concert with the ISO TC20/SC14. As such, this CCSDS standard is also properly labeled as ISO 26900. The recommended Orbit Data Message format is ASCII (reference REF R_ISO_IEC_8859_1_1998 \h [4] 08D0C9EA79F9BACE118C8200AA004BA90B02000000080000001600000052005F00490053004F005F004900450043005F0038003800350039005F0031005F0031003900390038000000 ). This document describes both ‘Keyword = Value Notation’ (KVN) as well as Extensible Markup Language (XML) (reference REF R_505x0b3XMLSpecificationforNavigationDa \h[5] 08D0C9EA79F9BACE118C8200AA004BA90B02000000080000002800000052005F00350030003500780030006200330058004D004C00530070006500630069006600690063006100740069006F006E0066006F0072004E0061007600690067006100740069006F006E0044000000 ) formatted messages. Selection of KVN or XML format should be mutually agreed between message exchange partners. NOTE – As currently specified, an OPM, OMM, or OEM file is to represent orbit data for a single spacecraft, and the OCM is to represent orbit data for either a single spacecraft or single parent spacecraft of a parent/child spacecraft deployment scenario. It is possible that the architecture may support multiple spacecraft per file; this could be considered in the future.
- Standard225 pagesEnglish languagesale 15% off
This document defines the primary space debris mitigation requirements applicable to all elements of systems launched into, or passing through, near-Earth space, including launch vehicle orbital stages, operating spacecraft and any objects released as part of normal operations or disposal actions.
The requirements contained in this document are intended to reduce the growth of 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.
This document is the top-level standard in a family of standards addressing debris mitigation. It will be the main interface for the user, bridging between the primary debris mitigation requirements and the lower-level implementation standards that will ensure compliance.
This document does not cover launch phase safety for which specific rules are defined elsewhere.
This document identifies the clauses and requirements (including notes and clarifications) modified or added with respect to the standard ISO 24113, Space systems - Space debris mitigation requirements, Third edition 2019-07 (referred to as ISO 24113:2019) for application of the European Space standard based on ECSS.
- Standard20 pagesEnglish languagesale 10% offe-Library read for1 day
This standard specifies a comprehensive set of engineering requirements for the
successful development of digital, analogue and mixed analogue-digital signal
custom designed integrated circuits, such as application specific integrated
circuits (ASICs), field programmable gate arrays (FPGAs) and Intellectual
Property Cores (IP Cores), from now on referred to with the single and generic
term DEVICEs.
Microelectronics systems created by more than one DEVICE die but that are
interconnected and packaged together as a single DEVICE are not considered
single monolithic DEVICEs. However ECSS-ST-20-40 is to be applied to (a) the
development of each individual monolithic die, (b) also for their integration onto
a multi-die single DEVICE considering those dice as IP Cores.
This standard may be tailored for the specific characteristic and constraints of a
space project in conformance with ECSS-S-ST-00. A pre-tailoring based on the
actual DEVICE type and criticality category of the DEVICE is addressed in
clause 5.1.2.
This standard does not cover requirements for the selection, control, procurement
or usage of DEVICEs for space projects nor DEVICE ESCC qualification
requirements, as those requirements are covered by ECSS-Q-ST-60C EEE
components standard and the ESCC generic specification No. 9000 respectively.
Nevertheless, this standard contemplates the possibility for the DEVICE to
undergo ESCC qualification after the DEVICE customer acceptance as an ECSS
qualified DEVICE, and thus a DEVICE ESCC Detail Specification and DEVICE
Radiation Test Plan and Report are optional expected outputs.
- Standard139 pagesEnglish languagesale 10% offe-Library read for1 day
This Standard establishes the basic rules and general principles applicable to the
electrical, electronic, electromagnetic, microwave and engineering processes. It
specifies the tasks of these engineering processes and the basic performance and
design requirements in each discipline.
It defines the terminology for the activities within these areas.
It defines the specific requirements for electrical subsystems and payloads,
deriving from the system engineering requirements laid out in ECSS-E-ST-10
“Space engineering – System engineering general requirements”.
This standard may be tailored for the specific characteristics and constrains of a
space project in conformance with ECSS-S-ST-00.
- Standard135 pagesEnglish languagesale 10% offe-Library read for1 day
This document provides requirements that are either unique or particularly relevant to large constellations of spacecraft operating in the LEO protected region throughout their life cycle, including planning, designing, testing, operating and disposal activities. The requirements in this document are applicable to large constellation owners. While some are directly applicable to the constellation owners, others are allocated to the manufactures or operators under the responsibility of the constellation owners.
- Technical specification10 pagesEnglish languagesale 15% off
This document specifies lessons learned principles and guidelines that are applicable in all space project activities (management, technical, quality, cost and schedule). The application of this document is intended to be included in the supplier quality management system, but can be tailored in individual contracts as agreed by the customer and supplier, depending on: — the content of each project (size, technological level and novelty, particular organization, participants, etc.); — the interest and usefulness of the related information. The lessons learned information can result from any situation which can be encountered in similar contexts for future projects, i.e.: — undesirable experiences to be avoided; — strategies, rules, principles of design, validation, tests and operations proved to be successful or necessary. This document neither endorses nor recommends the transmission of company proprietary information to external entities as part of a lessons learned process. Implementing a formal lessons learned process as outlined in this document makes it possible to capture and benefit from this information. The lessons learned activity is an important contribution to the processing of the preventive and corrective actions specified in ISO 9001, ISO 17666, ISO 14620-1 and ISO 23460. This document also provides lessons learned processes and suggested lessons learned forms.
- Standard13 pagesEnglish languagesale 15% off
This activity w ill be the parallel development of EN 16603-20-40 and ECSS-E-ST-20-40C.
The scope shall cover the areas of existing ASIC and FPGA engineering chapter 5 of ECSS-Q-ST-60-02C, but w ith w ider breadth and greater depth, covering engineering requirements of end-to-end development flow s, from specification of requirements to validation of prototypes, of the follow ing monolithic devices for its use in space:
• ASICs (distinguishing digital, analogue and mixed-signal development flow s)
• FPGAs (distinguishing three technology families: SRAM, FLASH and anti-fuse technologies)
• ASIC and FPGA System-on-Chip embedding processor cores w hich have external “softw are programme” dependencies to be addressed during the SoC development, resulting in SW-HW co-design requirements.
- Standard139 pagesEnglish languagesale 10% offe-Library read for1 day
This document defines the primary space debris mitigation requirements applicable to all elements of unmanned systems launched into, or passing through, near-Earth space, including launch vehicle orbital stages, operating spacecraft and any objects released as part of normal operations.
- Standard20 pagesEnglish languagesale 10% offe-Library read for1 day
This document specifies the space programme/project management requirements, applicable through a top-down approach in a contractual relationship between customers and suppliers.
- Standard34 pagesEnglish languagesale 15% off
Scope remains unchanged.
This Standard establishes the basic rules and general principles applicable to the electrical, electronic, electromagnetic, microwave and engineering processes. It specifies the tasks of these engineering processes and the basic performance and design requirements in each discipline.
It defines the terminology for the activities within these areas.
It defines the specific requirements for electrical subsystems and payloads, deriving from the system engineering requirements laid out in EN 16603-10 (equivalent of ECSS-E-ST-10 "Space engineering - System engineering general requirements".)
- Standard135 pagesEnglish languagesale 10% offe-Library read for1 day
This document defines the product assurance (PA) policy, objectives, principles, and requirements for the establishment and implementation of PA programmes for space programmes covering mission definition, design, development, production and operations of space products, including disposal. The PA discipline covers: PA management, quality assurance, safety assurance, dependability (reliability, availability and maintainability), assurance of software and hardware products, as well as parts (including electrical, electromechanical and electronic components, and mechanical parts), materials and processes assurance. This document defines their respective objectives, policies, and principles to achieve the stated overall PA objectives throughout the complete life cycle of the products. This document applies to space products.
- Standard10 pagesEnglish languagesale 15% off
This Standard specifies the general requirements for the qualification, procurement, storage and delivery of photovoltaic assemblies, solar cell assemblies, bare solar cells, coverglasses and protection diodes suitable for space applications.
This standard does not cover the particular qualification requirements for a specific mission.
This Standard primarily applies to qualification approval for photovoltaic assemblies, solar cell assemblies, bare solar cells, coverglasses and protection diodes, and to the procurement of these items.
This standard is limited to crystaline Silicon and single and multi-junction GaAs solar cells with a thickness of more than 50 m and does not include thin film solar cell technologies and poly-crystaline solar cells.
This Standard does not cover the concentration technology, and especially the requirements related to the optical components of a concentrator (e.g. reflector and lens) and their verification (e.g. collimated light source).
This Standard does not apply to qualification of the solar array subsystem, solar panels, structure and solar array mechanisms.
- Standard230 pagesEnglish languagesale 10% offe-Library read for1 day
This document defines the quality assurance (QA) requirements for the establishment and implementation of product QA programmes for projects covering mission definition, design, development, production and operations of space systems, including disposal. It is applicable to the customer-supplier relationship for space products to the extent agreed by both parties.
- Standard50 pagesEnglish languagesale 15% off
This document specifies a method for determining the identity and quantity of volatile off-gassed compounds from materials and assembled articles utilized in manned, pressurized spacecraft.
- Standard14 pagesEnglish languagesale 15% off
This document specifies two test methods for determining the flammability of electrical-wire insulation and accessory materials by exposure to an external ignition source in a static environment (test A) and in a gas-flow environment (test B). These tests determine if a wire insulation material, when exposed to a standard ignition source, will self-extinguish and not transfer burning debris which can ignite adjacent materials.
- Standard22 pagesEnglish languagesale 15% off
This document specifies a method for the determination of the flammability of aerospace materials by upward flame propagation. This test determines if a material, when exposed to a standard ignition source, will self-extinguish and not transfer burning debris which can ignite adjacent materials.
- Standard25 pagesEnglish languagesale 15% off
This document describes the technology for simulating space environments such as vacuum, cold black, and heat flux, as well as the compositions and functions of a thermal vacuum chamber (TVC). This kind of facility defined in this document is suitable for thermal vacuum tests (TVT) and thermal balance tests (TBT) on spacecraft-system level as well as on large-spacecraft-component level.
- Technical report43 pagesEnglish languagesale 15% off
This document defines the general criteria for the development of flight-to-ground umbilical systems used by a space system. These criteria apply to the service arms or equivalent mechanisms, umbilical carriers and plates, couplings, connectors, withdrawal and retract devices, handling mechanisms and control systems for mechanisms, as well as the prevention of accidental cross-connection.
- Standard15 pagesEnglish languagesale 15% off
This Standard specifies the general requirements for the qualification, procurement, storage and delivery of photovoltaic assemblies, solar cell assemblies, bare solar cells, coverglasses and protection diodes suitable for space applications.
This standard does not cover the particular qualification requirements for a specific mission.
This Standard primarily applies to qualification approval for photovoltaic assemblies, solar cell assemblies, bare solar cells, coverglasses and protection diodes, and to the procurement of these items.
This standard is limited to crystaline Silicon and single and multi-junction GaAs solar cells with a thickness of more than 50 m and does not include thin film solar cell technologies and poly-crystaline solar cells.
This Standard does not cover the concentration technology, and especially the requirements related to the optical components of a concentrator (e.g. reflector and lens) and their verification (e.g. collimated light source).
This Standard does not apply to qualification of the solar array subsystem, solar panels, structure and solar array mechanisms.
- Standard230 pagesEnglish languagesale 10% offe-Library read for1 day
This document establishes basic requirements for interface control documents (ICD) writing and interface control procedures for the following items included in the launch system: payload, launch vehicle, ground support equipment (according to ISO 14625) and launch site (buildings with utility systems), specifically: a) ICD between the ground support equipment and the payload; b) ICD between the ground support equipment and the launch vehicle; c) ICD between items of the ground support equipment; d) ICD between the ground support equipment and the launch site. This document is applicable to organizations developing ground support equipment and to operators performing space activity.
- Standard16 pagesEnglish languagesale 15% off
This standard defines the requirements for selection, control, procurement and
usage of EEE commercial components for space projects.
This standard is applicable to commercial parts from the following families:
• Ceramic capacitors chips
• Solid electrolyte tantalum capacitors chips
• Discrete parts (transistors, diodes, optocouplers)
• Fuses
• Magnetic parts
• Microcircuits
• Resistors chips
• Thermistors
In addition for families of EEE components not addressed by the present ECSS
standard, it can be used as guideline on case by case basis.
The requirements of this document are applicable to all parties involved at all
levels in the integration of EEE commercial components into space segment
hardware and launchers.
This standard may be tailored for the specific characteristics and constrains of a
space project in conformance with ECSS-S-ST-00
- Standard106 pagesEnglish languagesale 10% offe-Library read for1 day
This Standard specifies the processing and quality assurance requirements for
brazing processes for space flight applications. Brazing is understood as the
joining and sealing of materials by means of a solidification of a liquid filler
metal.
The term brazing in this standard is used as equivalent to soldering, in cases that
the filler materials have liquidus temperatures below 450 °C.
Brazing and soldering are allied processes to welding and this standard is
supplementing the standard for welding ECSS-Q-ST-70-39.
This standard does not cover requirements for:
• Joining processes by adhesive bonding (ECSS-Q-ST-70-16),
• Soldering for electronic assembly purposes (ECSS-Q-ST-70-61),
• Soldering used in hybrid manufacturing (ESCC 2566000).
The standard covers but is not limited to the following brazing processes:
• Torch brazing,
• Furnace brazing,
• Dip Brazing and Salt-bath brazing,
• Induction Brazing.
This Standard does not detail the brazing definition phase and brazing pre-
verification phase, including the derivation of design allowables.
This standard may be tailored for the specific characteristic and constraints of a
space project in conformance with ECSS-S-ST-00.
- Standard39 pagesEnglish languagesale 10% offe-Library read for1 day
This standard defines the requirements for selection, control, procurement and usage of EEE components for space projects.
This standard differentiates between three classes of components through three different sets of standardization requirements (clauses) to be met.
The three classes provide for three levels of trade-off between assurance and risk. The highest assurance and lowest risk is provided by class 1 and the lowest assurance and highest risk by class 3. Procurement costs are typically highest for class 1 and lowest for class 3. Mitigation and other engineering measures may decrease the total cost of ownership differences between the three classes. The project objectives, definition and constraints determine which class or classes of components are appropriate to be utilised within the system and subsystems.
a. Class 1 components are described in Clause 4.
b. Class 2 components are described in Clause 5
c. Class 3 components are described in Clause 6.
The requirements of this document apply to all parties involved at all levels in the integration of EEE components into space segment hardware and launchers.
- Standard103 pagesEnglish languagesale 10% offe-Library read for1 day
This document provides the test requirements of three typical separation test methods, which are the combined separation test, the horizontal separation test, the individual falling separation test, for the separation between the launch vehicle (LV) and the spacecraft (or between stages of a prototype LV model). It also provides the requirements for the separation test unit, test data, test timing and sequence, pre-test simulation, test environment, exception handling, test results assessment, test documentation, test facilities, test installation, preliminary adjustment of the test setup, measurement and data acquisition. This document is applicable to test providers and interested parties to implement the separation test between the launch vehicle and the spacecraft.
- Standard32 pagesEnglish languagesale 15% off
This document specifies processes, requirements and recommendations for the breakdown of project management structures, collectively called project breakdown structures, in terms of the various specification (i.e. requirements), functional, product, work, cost, business and organizational breakdown structures that are established and implemented to contribute to the success of a space programme, which is often composed of one or more projects. It specifies the various types of project breakdown structures and gives processes, requirements and guidance concerning the composition of these breakdown structures. This document is applicable to project breakdown structures for a project, including at the top level of a programme, i.e. level 0, as indicated in ISO 14300-1. It is intended to be used either by an independent developer as a partial basis for programme processes or as a basis for an agreement between a supplier and a customer. This document also provides descriptions of the kinds of project breakdown structures that are commonly useful in contributing to the success of a space project. Other project breakdown structures not described in this document also often contribute to the success of a space project.
- Standard13 pagesEnglish languagesale 15% off
The Scope of the Standard remains unchanged.
This standard defines the requirements for selection, control, procurement and usage of EEE components for space projects.
This standard differentiates between three classes of components through three different sets of standardization requirements (clauses) to be met.
The three classes provide for three levels of trade-off between assurance and risk. The highest assurance and lowest risk is provided by class 1 and the lowest assurance and highest risk by class 3. Procurement costs are typically highest for class 1 and lowest for class 3. Mitigation and other engineering measures may decrease the total cost of ownership differences between the three classes. The project objectives, definition and constraints determine which class or classes of components are appropriate to be utilised within the system and subsystems.
a. Class 1 components are described in Clause 4.
b. Class 2 components are described in Clause 5
c. Class 3 components are described in Clause 6.
The requirements of this document apply to all parties involved at all levels in the integration of EEE components into space segment hardware and launchers.
- Standard103 pagesEnglish languagesale 10% offe-Library read for1 day
2021-04-21: This EN is based on ECSS-Q-ST-60-13C Rev.1
- Standard106 pagesEnglish languagesale 10% offe-Library read for1 day
2021-04-21: This EN is based on ECSS-Q-ST-70-40C
- Standard39 pagesEnglish languagesale 10% offe-Library read for1 day
This document specifies class codes to classify global navigation satellite system (GNSS) receivers. The class codes represent how signals transmitted from radionavigation satellites are processed. This document applies to all types of GNSS receiver devices. The class codes in this document are not applicable to the following items: — condition of radionavigation satellites; — radio propagation environment including multipath, masking and obstacle; — additional antenna of a receiver device; — additional application software in a receiver device.
- Standard17 pagesEnglish languagesale 15% off
This document specifies test equipment and techniques used to identify interactions resulting from exposure of a material to an aerospace fluid. It is applicable for determining interactive reactions between propellants and materials used in the design, construction, and operation of propellant storage, transfer, and flight systems.
- Standard10 pagesEnglish languagesale 15% off
This document specifies the requirements for a dependability (reliability, availability and maintainability) assurance programme for space projects. It defines the dependability requirements for space products as well as for system functions implemented in software, and the interaction between hardware and software. This document is applicable to all programme phases.
- Standard18 pagesEnglish languagesale 15% off
This document provides spacecraft (SC) organizations with the general format for presenting the interface requirement document (IRD) for launch vehicle services. The IRD provides a list of the major technical requirements spacecraft agencies provide to launch vehicle (LV) agencies when submitting an application for launch services. The IRD addresses the definition of the SC mission, the mechanical and electrical interfaces, the overall environment requirements (mechanical, thermal, cleanliness, radio-electrical), the SC development and test programme and, finally, launch range facilities and support requirements. This document is applicable to all existing commercial LV and related launch facilities so as to permit SC contractors to prepare a single interface requirement document for a given SC mission, independently of the LV contractor to be selected. The IRD, as defined in this document, includes the basic SC input data needed by LV agencies to prepare the interface control document defined in ISO 15863.
- Standard23 pagesEnglish languagesale 15% off
This document defines the primary space debris mitigation requirements applicable to all elements of unmanned systems launched into, or passing through, near-Earth space, including launch vehicle orbital stages, operating spacecraft and any objects released as part of normal operations.
- Standard12 pagesEnglish languagesale 15% off
This document specifies process requirements for project reviews as a set of required functions. It establishes requirements and recommendations on the function inputs, outputs, mechanisms and controlling conditions. This document specifies the responsibilities of a review board and gives guidance concerning review board composition. This document also provides descriptions of the kinds of reviews that are commonly useful in assuring the success of a space project. This document is applicable to status reviews for a project at any level within a larger project, as well as for major milestone reviews at the top level of a major project. It is intended to be used either by an independent developer as a basis for enterprise processes, or as a basis for an agreement between a supplier and a customer. It is intended for use in implementing the review requirements of ISO 14300-1, and ISO 14300-2, ISO 15865 and such other space systems and operations standards that require formal reviews.
- Standard19 pagesEnglish languagesale 15% off
This document contains requirements and guidelines for the utilization of off-the-shelf (OTS) items, their selection, acquisition, integration, qualification and implementation related to a space product or system. This document doesn't cover piece parts and materials, such as electrical, electronic and electromechanical (EEE) parts, thermocouples, rivets, fasteners, connectors, fittings, adhesives, insulation, wiring and plumbing.
- Standard15 pagesEnglish languagesale 15% off
This document provides methods and specifies general requirements for spacecraft level thermal balance tests (TBT) and thermal vacuum tests (TVT). It also provides basic requirements for test facilities, test procedures, test malfunction interruption emergency handling and test documentation. The methods and requirements can be used as a reference for subsystem-level and unit-level test article.
- Standard30 pagesEnglish languagesale 15% off
- Standard30 pagesEnglish languagesale 15% off
- Standard30 pagesEnglish languagesale 15% off
This document describes the main magnetospheric large-scale current systems and the magnetic field in the Earth's magnetosphere and provides the main requirements to the model of the magnetospheric magnetic field. Ionospheric currents are not considered in this document. The document also provides a working example of the model and establishes the parameters of magnetospheric large-scale current systems which are changing in accordance with conditions in the space environment. The document can be used to develop the new models of magnetospheric magnetic field. Such models are useful in investigating physical processes in the Earth's magnetosphere as well as in calculations, developing, testing and estimating the results of exploitation of spacecrafts and other equipment operating in the space environment.
- Standard17 pagesEnglish languagesale 15% off
This document identifies the clauses and requirements modified with respect to the standards CCSDS 232.1-B-2, Communications Operation Procedure-1, Issue 2, September 2010 for application in ECSS.
NOTE The recently published technical corrigendum has modified CCSDS 232.1-B-2. However, the changes are not affecting the Adoption Notice.
- Standard11 pagesEnglish languagesale 10% offe-Library read for1 day
This document identifies the clauses and requirements modified w ith respect to the standard CCSDS 131.0-B-3, TM Synchronization and Channel Coding, Issue 3, September 2017 for application in ECSS.
- Standard19 pagesEnglish languagesale 10% offe-Library read for1 day
This document identifies the clauses and requirements modified w ith respect to the standard CCSDS 131.0-B-3, TM
Synchronization and Channel Coding, Issue 3, September 2017 for application in ECSS.
- Standard11 pagesEnglish languagesale 10% offe-Library read for1 day
This Standard specifies the requirements for the development of the endtoend data communications system for spacecraft.
Specifically, this standard specifies:
- The terminology to be used for space communication systems engineering.
- The activities to be performed as part of the space communication system engineering process, in accordance with the ECSS-E-ST-10 standard.
- Specific requirements on space communication systems in respect of functionality and performance.
The communications links covered by this Standard are the spacetoground and spacetospace links used during spacecraft operations, and the communications links to the spacecraft used during the assembly, integration and test, and operational phases.
Spacecraft endtoend communication systems comprise components in three distinct domains, namely the ground network, the space link, and the space network. This Standard covers the components of the space link and space network in detail. However, this Standard only covers those aspects of the ground network that are necessary for the provision of the endtoend communication services.
NOTE Other aspects of the ground network are covered in ECSS-E ST 70.
This Standard may be tailored for the specific characteristics and constraints of a space project in conformance with ECSS-S ST 00.
- Standard79 pagesEnglish languagesale 10% offe-Library read for1 day