M/237 - Equipment space industry

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

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.

This standard defines the safety programme and the technical safety requirements that shall be implemented in order to comply with the ECSS Safety Policy as defined in ECSS-Q-00. 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 European space systems.

The present document, "Integrated Logistic Support", is part of a collection of space standards belonging to the management branch. This standard describes the set of management requirements aimed at the identification and provision of logistical support, such that the consumer can operate and maintain a product in its operational conditions, for the expected lifetime.

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.

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.

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.

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.

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:
3   verification planning requirements;
3   definition of a route to conform to the requirements;
3   design and test margin requirements;
3   design and test requirements; and
3   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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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

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.

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.

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.

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.

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.

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.

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.

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).

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.

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.

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.

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.

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.

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.

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.

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).

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.

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.

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.

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.

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.

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.

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.

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.