ISO 16091:2002 describes the set of management requirements needed to identify and provide logistic support, so the customer can operate and maintain a product in its operational environment for the expected lifetime.
These requirements also aim, throughout the product life cycle, at implementing everything pertinent to the control of the risks considered as critical regarding the operational objectives.
The management requirements are applicable to those activities necessary to design, develop, deliver, deploy and manage an organized and structured set of materials and software, services, processes and information dedicated to support the system throughout its life cycle.
ISO 16091:2002 specifies management, studies, production activities, information management processes and tasks to meet the customer's need for logistic support.
When viewed from the perspective of a specific programme or project context, the requirements defined in ISO 16091:2002 should be tailored to match the genuine requirements of a particular profile and circumstances of a programme or project.

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This Standard is part of a collection of European Space Standards dealing with management. It defines the process of tailoring, applicable to all space standards for management, product assurance and engineering as a guideline. This Standard defines the objectives, principles, methods and processes of tailoring, which are necessary for the establishment of project requirement documents.

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This standard is designed to facilitate the elaboration of a management system which is cost effective, appropriate to the project in which it is implemented, compatible with the actor's existing structures and which has the flexibility to adapt to changing needs throughout all the phases of an evolving project, and to new projects.

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EN 14607 Part 6 of Space engineering - Mechanical defines the requirements for the discipline of pyrotechnics engineering.
This part defines the standards to be applied for the use of pyrotechnics on all spacecraft and other space products including launch vehicles. It addresses the aspects of design, analysis, verification, manufacturing, operations and safety.
As any pyrotechnic item used for flight can function only once, it can never be fully tested before its crucial mission operation. The required confidence can only be established indirectly by the testing of identical items. Test results and theoretical justification are essential for demonstration of fulfilment of the requirements. The requirement for repeatability shows that product assurance plays a crucial role in support of technical aspects.
The failure or unintentional operation of a pyrotechnic item can be catastrophic for the whole mission and life threatening. Specific requirements can exist for the items associated with it. As all pyrotechnic functions are to be treated similarly, collective control needs to be applied in the manner of a subsystem.
When viewed from the perspective of a specific project context, the requirements defined in this document should be tailored to match the genuine requirements of a particular profile and circumstances of a project.
NOTE   Tailoring is a process by which individual requirements of specifications, standards and related documents are evaluated, and made applicable to a specific project by selection, and in some exceptional cases, modification of existing or addition of new requirements.

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This standard establishes the requirements for the verification of a space system product. It specifies the fundamental concepts of the verification process, the criteria for defining the verification strategy and the rules for the implementation of the verification programme. It includes also in annex A and B the description of the required documentation (i.e. DRDs) and some guidelines on specific aspects of the verification process such as the Model Philosophy definition.

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This document defines the requirements to perform functional analysis and the information output of that analysis. It applies to all types and combinations of space systems, projects and products. It also applies to project phases 0, A, B and C and at all levels.
When viewed from the perspective of a specific project context, the requirements defined in this document should be tailored to match the genuine requirements of a particular profile and circumstances of a project.
NOTE  Tailoring is a process by which individual requirements of specifications, standards and related documents are evaluated and made applicable to a specific project by selection, and in some exceptional cases, modification of existing or addition of new requirements.

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EN 14607 Part 7 of Space engineering - Mechanical defines the mechanical engineering requirements for mechanical parts.
This document defines the requirements applicable to the selection, design, verification and application of mechanical parts to promote the use of high­quality non­critical mechanical parts that achieve robust functionality and satisfy the mission performance requirements.
This document defines a pragmatic approach to the selection of parts by the mechanical and design engineer on the basis of their effect on the integrity of the equipment and to streamline the selection of space­proven rather than non space­proven parts during the design of a new equipment in order to select the least number of different parts to satisfy the mission requirements.
It defines performance, design, test, product assurance and support activity requirements for the use of mechanical parts in space applications.
When viewed from the perspective of a specific project context, the requirements defined in this document should be tailored to match the genuine requirements of a particular profile and circumstances of a project.
NOTE   Tailoring is a process by which individual requirements of specifications, standards and related documents are evaluated, and made applicable to a specific project by selection, and in some exceptional cases, modification of existing or addition of new requirements.

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ISO 14620-1:2002 defines the safety programme and the technical safety requirements that are implemented in order to comply with the safety policy as defined in ISO 14300-2. It is intended to protect flight and ground personnel, the launch vehicle, associated payloads, ground support equipment, the general public, public and private property, and the environment from hazards associated with space systems. Launch site operations are described by ISO 14620-2.
The safety policy is applied by implementing a system safety programme, supported by risk assessment, which can be summarized as follows: hazardous characteristics (system and environmental hazards) and functions with potentially hazardous failure effects are identified and progressively evaluated by iteratively performing systematic safety analyses; the potential hazardous consequences associated with the system characteristics and functional failures are subjected to a hazard reduction sequence whereby hazards are eliminated from the system design and operations, hazards are minimized, and hazard controls are applied and verified; the risks that remain after the application of a hazard elimination and reduction process are progressively assessed and subjected to risk assessment, in order to show compliance with safety targets, support design trades, identify and rank risk contributors, support apportionment of project resources for risk reduction, assess risk reduction progress, and support the safety and project decision-making process (e.g. waiver approval, residual risk acceptance); the adequacy of the hazard and risk control measures applied are formally verified in order to support safety validation and risk acceptance; safety compliance is assessed by the project and safety approval obtained from the relevant authorities.
ISO 14620-1:2002 is applicable to all space projects where during any project phase there exists the potential for hazards to personnel or the general public, space flight systems, ground support equipment, facilities, public or private property, or the environment.
The imposition of these requirements on the project suppliers' activities requires that the customer's project product assurance and safety organization also respond to these requirements in a manner which is commensurate with the project's safety criticality.
When viewed from the perspective of a specific programme or project context, the requirements defined in ISO 14620-1:2002 should be tailored to match the genuine requirements of a particular profile and circumstances of a programme or project.

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This standard, which is informative in nature, contains the basic rules and overall principles to be applied to all engineering activities during performance of a space project. It addresses the establishment, based on customer needs, of mission objectives, requirements and specifications for space systems, and the design, definition, production, verification, operation, and eventual disposal of the systems themselves.

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This document addresses the utilization of telecommand packets and telemetry source packets for the purposes of remote monitoring and control of subsystems and payloads.

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This standard defines the Product Assurance (PA) policy, objectives, principles and rules for the establishment and implementation of PA programmes for projects covering mission definition, design, development, production and operations of space products including disposal. The PA discipline covers: PA management, quality assurance, safety assurance, reliability, availability and maintainability assurance, software product assurance, EEE components, materials, mechanical parts and processes.

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The purpose of this standard is to define the requirements and statements applicable to materials, mechanical parts and processes to satisfy the mission performance requirements. This standard covers the following requirement domains: - management, including organisation, reviews, acceptance status and documentation control; - selection criteria and rules; - evaluation, validation/qualification testing; - procurement and receiving inspection; - utilisation criteria and rules. The relationship between activities and programme phases is defined in annex A.

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EN 14607 Part 8 of Space engineering - Mechanical defines the mechanical engineering requirements for materials.
This document also encompasses the effects of the natural and induced environments to which materials used for space applications can be subjected.
This document defines requirements for the establishment of the required mechanical and physical properties of the materials including the effects of the environmental conditions, material selection, procurement, production and verification. Verification includes destructive and non­destructive test methods. Material procurement and control is closely related to required quality assurance procedures and detailed references to EN 13291-3 are made.
When viewed from the perspective of a specific project context, the requirements defined in this document should be tailored to match the genuine requirements of a particular profile and circumstances of a project.
NOTE   Tailoring is a process by which individual requirements of specifications, standards and related documents are evaluated, and made applicable to a specific project by selection, and in some exceptional cases, modification of existing or addition of new requirements.

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This European Standard defines the quality assurance (QA) requirements for the operation, maintenance, management and configuration control of test centres for space applications. It also defines the requirements for the treatment of test specimens and the development of test facilities.
This European Standard applies to test centres as self-standing organizations, or those belonging to a parent organization. Separate procedures are not required in the latter case if activities are controlled by the implementation of parent organization procedures.
When viewed in a specific project context, the requirements defined in this European Standard should be tailored to match the genuine requirements of a particular profile and circumstances of a project.

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Within the frame of the overall engineering standards for space missions, this European Standard contains the basic rules, principles and requirements to be applied to the engineering of the ground segment and mission operations, which form an integral part of the overall system implementing a space mission.
This European Standard includes development of ground segment, operations preparation activities, mission planning activities, mission evaluation activities, the conduct of operations proper, and all post-operational activities. The ground segment comprises the ground systems (i.e. all ground facilities, hardware and software) and all operational aspects such as personnel and related data repositories required on ground to perform mission operations.
For reasons of recognized commonality, ground segment within the meaning of this European Standard includes those elements and facilities required for the purpose of implementing the mission and fulfilling the missions requirements while the relevant space segments are in-orbit. It covers ground elements used for purposes of assembly, integration and verification of the space segment, to the extent needed for ground segment end-to-end verification activities. It also covers elements integrated into the ground segment after completion of space segment AIT; space segment AIT proper being considered outside the scope of this Standard.
It does not however cover the spacecraft activities and facilities interfacing the launch service segment. Furthermore, while this European Standard is applicable to all classes of missions it does not consider aspects that are specific to manned space missions.

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Within the frame of the overall engineering standards for space missions, this European Standard contains the basic rules, principles and requirements to be applied to the engineering of the ground segment and mission operations, which form an integral part of the overall system implementing a space mission.
This European Standard includes development of ground segment, operations preparation activities, mission planning activities, mission evaluation activities, the conduct of operations proper, and all post-operational activities. The ground segment comprises the ground systems (i.e. all ground facilities, hardware and software) and all operational aspects such as personnel and related data repositories required on ground to perform mission operations.
For reasons of recognized commonality, ground segment within the meaning of this European Standard includes those elements and facilities required for the purpose of implementing the mission and fulfilling the missions requirements while the relevant space segments are in-orbit. It covers ground elements used for purposes of assembly, integration and verification of the space segment, to the extent needed for ground segment end-to-end verification activities. It also covers elements integrated into the ground segment after completion of space segment AIT; space segment AIT proper being considered outside the scope of this Standard.
It does not however cover the spacecraft activities and facilities interfacing the launch service segment. Furthermore, while this European Standard is applicable to all classes of missions it does not consider aspects that are specific to manned space missions.

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This European Standard applies to all product types which exist or operate in space and defines the natural environment for all space regimes. It also defines general models and rules for determining the local induced environment.
Project­specific or project­class­specific acceptance criteria, analysis methods or procedures are not defined.
The natural space environment of a given item is that set of environmental conditions defined by the external physical world for the given mission (e.g. atmosphere, meteoroids and energetic particle radiation). The induced space environment is that set of environmental conditions created or modified by the presence or operation of the item and its mission (e.g. contamination, secondary radiations and spacecraft charging). The space environment also contains elements which are induced by the execution of other space activities (e.g. debris and contamination).

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This European Standard details a test in which pressure-sensitive tapes are used to assess the suitability of, for example, coatings, paints, films and other thin materials, proposed for use on spacecraft and associated equipment.
The following materials and assemblies are covered by this test method:
-   organic coating, e.g. varnishes, paints and plastic films;
-   metallic finishes on, for example, printed circuit boards, second-surface mirrors, thermal radiators, plastic films;
-   adhesive layers;
-   composite thin films;
-   small assemblies, e.g. solar cells having attached glass covers.

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The present document "Project phasing and planning" is part of a collection of space standards belonging to the management branch. Its purpose is to define the principles and requirements to be observed during the management of the project phasing and planning. Each requirement and its purpose is described together with the expected output. The requirements specified herein apply to and affect the customer and supplier at all levels, when the capability to design and supply conforming product needs to be demonstrated.

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The present document "Project Organisation", is part of a collection of space standards belonging to the management branch. The purpose of this space standard (ECSS-M-20) is to define the project organisation standards required to provide satisfactory and coherent control of space projects. The requirements specified herein apply to, and affect the supplier and customer at all levels, when the capability to design and supply conforming product needs to be demonstrated. These requirements, as tailored in the related project requirements document are applicable to any actor of a space project.

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The present document "Project breakdown structures" is part of a collection of space standards belonging to the management branch. In order to create the reference system for project management necessary for implementation of a project and ensure consistency, the project shall be broken down into a unique, orderly and exhaustive manner, to allow unambiguous identification of the associated products and models, as well as the tasks and resources necessary. The aim of this space standard is to define the principles to be respected for setting up, using and adapting the breakdown structures and implementing them into a project.

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This European Standard contains the definition of all common terms used in European space standards. Terms specific to a particular space standard are defined in that standard.

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Several classes of material depend on a chemical reaction for their application and their final properties are sensitive to the exact composition of the reactants. The final properties vary with the reactants’ age and storage condition.
This European Standard specifies the procedure to be used for the control of limited shelf­life materials employed in the fabrication of spacecraft and associated equipment.

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This European Standard sets forth the criteria to be used in the selection of materials for spacecraft and associated equipment and facilities so that failure resulting from stress-corrosion is prevented.
Three categories of materials are listed in Tables 1, 2 and 3 of this Standard. They represent metal alloys with a high, moderate and low resistance to stress-corrosion cracking.
The stress-corrosion susceptibility of alloys included in this Standard was determined at ambient temperature
-   by means of laboratory tests in which specimens were either sprayed with salt water or periodically immersed and withdrawn;
-   by exposing specimens in sea coast or mild industrial environments;
-   by subjecting fabricated hardware to service conditions.
Use of the criteria established herein should, therefore, be limited to designs for service involving similar exposure conditions.
Weldments present a special problem in designing for resistance to stress-corrosion cracking. In addition to the susceptibility of the parent metals, it is also necessary to consider the filler metal and the microstructural effects of heat introduced by the welding operations and subsequent heat treatments. Because of the additional variables that shall be considered, susceptibility data are not as extensive for weldments as for alloys in mill form. Design criteria for weldments in this Standard are limited to aluminium alloys, selected stainless steels in the 300 series and other specific alloys listed in Table 1.
This Standard is intended to provide general criteria to be used in designing for resistance to stress-corrosion cracking. Specific test data and other detailed information are not included.

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This European Standard defines a test procedure for the determination of the release of trace contaminants by non-metallic materials under a set of closely controlled conditions. The test procedure covers both individual materials and assembled articles.
This Standard describes a test to provide data for aid in the evaluation of the suitability of assembled articles and materials for use in a space vehicle crew compartment. The data obtained are in respect of the nature and quantity of organic and inorganic volatile contaminants evolved when subjected to the crew compartment environment.

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This European Standard specifies a multi­test procedure for the determination of the flammability char-acteristics of non­metallic materials under a set of closely controlled conditions. The test procedure cov-ers both individual materials and materials used in configuration. This standard describes a series of tests to provide data for aid in the evaluation of the suitability of materials for use in a space vehicle crew compartment. The data obtained are in respect to the ease of ignition and the flame propagation char-acteristics of materials.

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This specification defines the basic requirements for the verification and approval of automatic machine wave soldering for use in spacecraft hardware. The process requirements for wave soldering of double-sided and multilayer boards are also defined.

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This European Standard specifies a thermal vacuum test to determine the outgassing properties of materials proposed for use in the fabrication of spacecraft and associated equipment, for vacuum facilities used for flight hardware tests and for certain launcher hardware.
This standard covers the following:
-   critical design parameters of the test system;
-   critical test parameters such as temperature, time, pressure;
-   material sample preparation;
-   conditioning parameters for samples and collector plates;
-   presentation of the test data;
-   acceptance criteria;
-   certification of test systems and their operators by audits and round robin tests.
The test described in this standard is applicable for all unmanned spacecraft, launchers, payloads, and experiments. The test is also valid for external hardware of inhabited space systems and for hardware to be used in terrestrial vacuum test facilities.
The acceptance criteria for a material, based upon the outgassing test data, depends upon the application and location of the material and can be more severe than the standard requirements as given in 7.2.

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This European Standard details a thermal cycling test under vacuum for the screening of materials and processes intended for use in the fabrication of spacecraft and associated equipment. The test determines the ability of these or other articles to withstand changes of ambient temperature under vacuum.
Typical materials or assemblies that can be evaluated by means of this test method are listed below. This is not an exhaustive list and other products or items can be tested:
-   adhesives;
-   adhesive bonded joints;
-   coatings (paint, thermal and protective);
-   insulating materials;
-   metallic bonded joints;
-   metallic samples, finished by plating or chemical conversion;
-   metallized plastic films;
-   organic or non-organic bonding;
-   plated surfaces;
-   potting compounds;
-   pressure-sensitive tapes;
-   printed circuit boards;
-   reinforced structural laminates;
-   sealants;
-   soldered or welded joints.

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EN 14607 Part 1 of Space engineering - Mechanical specifies requirements for the discipline of thermal engineering.
This document specifies the requirements for the definition, analysis, design, manufacture, verification and in­service operation of thermal control subsystems of spacecraft and other space products.
This document applies to the thermal engineering activities of all spacecraft and space related products for all thermal aspects and temperature levels for space products.
For this document, the complete temperature scale is divided into three ranges defined as follows:
- Cryogenic temperature range, below 120 K;
- Conventional temperature range, between 120 K and 420 K;
- High temperature range, above 420 K.
The core part of this document concerns the conventional temperature range; complementary information, requirements and definitions for the cryogenic and high temperature range respectively are provided in annexes B and C.
When viewed from the perspective of a specific project context, the requirements defined in this document should be tailored to match the genuine requirements of a particular profile and circumstances of a project.
NOTE   Tailoring is a process by which individual requirements of specifications, standards and related documents are evaluated, and made applicable to a specific project by selection, and in some exceptional cases, modification of existing or addition of new requirements.
This document is applicable to:
- thermal engineering activities of all space and space related products, covering all thermal engineering aspects involved in the achievement of the required thermal performance, particularly: design, verification, manufacturing and in service operations;
- thermal control subsystem and to relevant parts of all space products.

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This European Standard specifies the hazard analysis requirements of EN ISO 14620-1:2002, 6.4.2; it specifies the principles, process, implementation, and requirements of hazard analysis.
It is applicable to all European space projects where during any project phase there exists the potential for hazards to personnel or the general public, space flight systems, ground support equipment, facilities, public or private property or the environment.

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This standard defines the Quality Assurance (QA) requirements for the establishment and implementation of QA programmes for projects covering mission definition, design, development, production and operations of space systems, including disposal. This standard is applicable to the customer/supplier relationship of space products to the extent agreed by both parties. The requirements of this standard should be tailored to the needs and classes of specific projects. For software quality assurance the software PA standard ECSS-Q-80 is applicable.

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EN 14607 Part 5.1 of Space engineering - Mechanical defined the requirements for the discipline liquid and electric propulsion for spacecraft
This document belongs to the propulsion field of the mechanical discipline, as defined in EN 13292, and defines the regulatory aspects applicable to elements and processes for liquid, including cold gas, and electrical propulsion for spacecraft. It specifies the activities to perform in the engineering of such propulsion systems, their applicability, and defines the requirements for the engineering aspects: functional, configurational, interfaces, physical, environmental, quality factors, operational and verification.
General requirements relating to Mechanical Engineering are defined in EN 14607 Part 1.
This document applies only to liquid, including cold gas, and electrical propulsion systems used in spacecraft and to related mechanical parts. Solid propulsion for spacecraft, and solid and liquid propulsion for launchers are not covered by this document.
Other forms of propulsion currently under development (e.g. nuclear, nuclear-electric, solar-thermal and hybrid propulsion) are not presently covered by this document.
When viewed in a specific project context, the requirements defined in this document should be tailored to match the genuine requirements of a particular profile and circumstances of a project.
NOTE   Tailoring is a process by which individual requirements of specifications, standards and related documents are evaluated and made applicable to a specific project, by selection and in some exceptional cases, modification of existing or addition of new requirements.

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This European Standard defines the control system for nonconformances related to any aspect of a space project, including EEE component nonconformances, software problems, operational nonconformances and anomalies.
This Standard applies to all deliverables, at all levels, which fail to conform to specified requirements and design baselines.
This Standard is applicable throughout
·    procurement, production, qualification, integration and test phases,
·    acceptance, delivery and transportation phases,
·    launch preparation phase and flight/launch readiness,
·    operational validation/qualification phase,
·    operational phase, and
·    refurbishment phase.
This Standard defines also requirements for the interfaces with third party internal nonconformance reporting and processing.
Engineering changes are not a subject of this Standard.

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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.

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This European Standard defines the space software engineering process and its interfaces with the space project management standards (EN 13290) and space product assurance standards (EN 13291) and explains how they apply in the software engineering process.
This Standard is applicable to all the elements of a space system, including the space segment, the launch service segment and the ground segment.
This Standard covers all aspects of space software engineering including requirements definition, design, production, verification and validation, and transfer, operations and maintenance.
The scope of this Standard is the software developed as part of a space project, i.e. "Space system product software". It is not intended to cover software developments out of scope with the system of space standards. An example is the development of commercial software packages, where software is developed for a (large) volume market and not just for a single customer, and the main requirement analysis consists of market analysis, combined with a marketing strategy.
Other classes of software products not covered are: management information systems (e.g. finance, planning), technical information systems (e.g. CAD/CAM, analysis packages) and supporting software products for documentation systems, database systems, spread­sheets. These usually result from the procurement or adaptation of existing commercial products, and not part of the space system development. Such software products are, however, often part of a supporting infrastructure for space systems.
When viewed from the perspective of a specific project context, the requirements defined in this Standard should be tailored to match the genuine requirements of a particular profile and circumstances of a project.

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This European Standard,
a) specifies standard environmental and performance test requirements for a space system and its constituents;
b) specifies the test requirements for products and systems that are generally applicable to all projects;
c) specifies the documentation associated with testing activities;
d) is applicable to all types and combinations of project, organization and product;
e) is applicable to space systems and its constituents; and
f) covers each stage of verification by testing, for a space system from development to post-landing.
This European Standard does not specify acceptance criteria, specifications or procedures for any particular project or class of projects. In addition this Standard does not apply to software testing, hardware below equipment levels, nor covers the following:

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ISO 17666:2003 extends the requirements of ISO 14300-1, the principles and requirements for integrated risk management on a space project. It explains what is needed to implement a project-integrated risk management policy by any project actor, at any level (i.e. customer, first-level supplier, or lower-level suppliers).
ISO 17666:2003 contains a summary of the general risk management process, which is subdivided into four (4) basic steps and nine (9) tasks. The implementation can be tailored to project-specific conditions.
The risk management process requires information exchange among all project domains and provides visibility over risks, with a ranking according to their criticality for the project. These risks are monitored and controlled according to the rules defined for the domains to which they belong.
ISO 17666:2003 is applicable to all space project phases, as defined in ISO 14300-1.
When viewed from the perspective of a specific programme or project context, the requirements defined in ISO 17666:2003 should be tailored to match the genuine requirements of a particular profile and circumstances of a programme or project.

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This European Standard provides means for identifying and structuring all of the activities and information required in a project review. It identifies the information outputs and follow­up activities necessary to complete the review process. It also provides a check­list of activities and information required for each of the major project reviews identified in the European space management standards.
This standard does not prescribe a particular review procedure or organizational structure to be applied, in order to respect the customer's own rules and regulations.
When viewed from the perspective of a specific project context, the requirements defined in this standard should be tailored to match the genuine requirements of a particular profile and circumstances of a project.
NOTE   Tailoring is a process by which individual requirements of specifications, standards and related documents are evaluated and made applicable to a specific project by selection, and in some exceptional cases, modification of existing or addition of new requirements.

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The present document "Cost and schedule management", is part of a collection of space standards belonging to the management branch. The requirements specified herein apply to, and affect the customer and supplier at all levels, when the capability to design and supply conforming product needs to be demonstrated. These requirements, as tailored in related project requirements document, are applicable to any actor of a space project.

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The present document "information/documentation management" is part of the collection of space standards. Its purpose is to define the principles and requirements to be observed during the management of project information (including documentation). This standard applies to all the documents and the information contained therein, irrespective of media in which they are stored and/or transmitted. The requirements specified herein apply to and affect the customer and supplier at all levels, when the capability to design and supply conforming product needs to be demonstrated.

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The present document "Configuration management" is part of a collection of space standards belonging to the management branch. The purpose of this space standard is to define the principles and requirements that shall be respected with regard to the management of the configuration of products within a space project. This management standard defines all the rules for a proper configuration management. The requirements specified herein apply to, and affect the supplier and customer at all levels, when the capability to design and supply conforming product needs to be demonstrated.

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Part 2 of Space engineering - Mechanical defines the mechanical engineering requirements for structural engineering.
This document specifies the requirements to consider in all engineering aspects of structures: requirement definition and specification, design, development, verification, production, in­service and eventual disposal.
The document applies to all general structural subsystem aspects of space including: launch vehicles, transfer vehicles, re­entry vehicles, spacecraft, landing probes and rovers, sounding rockets, payloads and instruments, and structural parts of all subsystems.
When viewed from the perspective of a specific project context, the requirements defined in this document should be tailored to match the genuine requirements of a particular profile and circumstances of a project.
NOTE   Tailoring is a process by which individual requirements of specifications, standards and related documents are evaluated, and made applicable to a specific project by selection, and in some exceptional cases, modification of existing or addition of new requirements.

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This standard specifies the fracture control requirements to be imposed on space systems.
The requirements contained in this standard, when implemented, also satisfy the requirements applicable to the NASA STS and ISS as defined in the NASA document NSTS 1700.7 (incl. the ISS Addendum). Since this standard and the NASA document NSTS 1700.7 (incl. the ISS Addendum) are subject to different independent approval authorities, and recognizing that possible changes to documents may occur in the future, the user of this standard is advised to confirm the current status.
NOTE  The definitions used in this standard are based on ECSS nomenclature and are given in clause 3. The NASA nomenclature differs in some cases from that used by ECSS. When STS-specific requirements and nomenclature are included, they are identified as such.

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This document specifies the requirements and recommendations for the design and test of RF components and equipment to achieve acceptable performance with respect to multipaction-free operation in service in space. The document includes:
¾   verification planning requirements;
¾   definition of a route to conform to the requirements;
¾   design and test margin requirements;
¾   design and test requirements; and
¾   informative annexes that provide guidelines on the design and test processes.
This document is intended to result in the effective design and verification of the multipaction performance of the equipment and consequently in a high confidence in achieving successful product operation.
This document covers multipaction events occurring in all classes of RF satellite components and equipment at all frequency bands of interest. Operation in single carrier CW and pulse modulated mode are included, as well as multi-carrier operations. document does not include breakdown processes caused by collisional processes, such as plasma formation.
This document is applicable to all space missions.
When viewed in a specific project context, the requirements defined in this document should be tailored to match the genuine requirements of a particular profile and circumstances of a project.
NOTE   Tailoring is a process by which individual requirements of specifications, standards and related documents are evaluated and made applicable to a specific project, by selection and in some exceptional cases, modification of existing or addition of new requirements.

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