This Standard defines the basic requirements for evaluation, qualification and maintenance of qualification of space PCB suppliers for different types of printed circuit boards. This Standard is applicable to the following type of boards: rigid printed boards (single-sided, double-sided,multilayer, sequential- laminated multilayer and metal core); flexible printed boards (single-sided and double-sided); rigid-flex printed boards (multilayer and sequential-laminated multilayer); high frequency printed boards; special printed boards.

ECSS Q-70-11A, Space Engineering, Procurement of printed circuit boards-23 Nov 2001. This Standard defines the requirements imposed on both the customer and the qualified PCB supplier for PCB procurement. This Standard also details the basic requirements for procurement of PCBs as well as the minimum requirements for the different types of PCBs. This Standard is applicable for the following type of boards: rigid printed boards (single-sided, double-sided,multilayer, sequential- laminated multilayer and metal core); flexible printed boards (single-sided and double-sided); rigid-flex printed boards (multilayer and sequential-laminated multilayer); high frequency printed boards;and special printed boards.

ECSS-E-10-03A, SPACE ENGINEERING TESTING. This Standard, 1. provides standard environmental and performance test requirements for a space system and its constituents. 2. defines the test requirements for products and systems that are generally applicable to all projects. It also defines the documentation associated with testing activities. 3. applies to all types and combinations of project, organization and product. 4. is applicable to space systems and its constituents as defined in ECSS-E-00 “Space engineering - Policy and principles”. 5. covers each stage of verification by testing, as defined by ECSS-E-10-02, for a space system from development to post-landing.

ECSS-E-10-04A, SPACE ENGINEERING, SPACE ENVIRONMENT (21 JAN 2000)., This 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. Project-specific or project-class-specific 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).

ECSS-E-10A, SPACE ENGINEERING, SYSTEM ENGINEERING (19 APR 1996)., This standard is intended to guide the development of Systems (including hardware, software, man–in–the–loop, facilities and services) for space applications.It specifies implementation requirements for the responsible System Engineering organization consistent with the assumption that the System Engineering process defined in Standard ECSS–E–10–01 is to be applied.Specific objectives of this standard are to : a. Assist in defining, performing, managing, and evaluating System Engineering efforts to ensure that the programme has a firm organisational basis, able in principle to minimise technical risk due to uncertain understanding of scope. b. Facilitate minimisation of cost through avoidance of repeated organisational work, conversion between different practices and dispersions due to conflicts of interpretation of approaches to System Engineering tasks. c. Capture the key aspects of the Space Standardization initiatives to : better integrate requirements; implement multidisciplinary teamwork including suppliers; establish the requirements early; establish clear measurements of system responsiveness; focus on process control rather than inspection; encourage risk management rather than risk avoidance; increase teamwork and cooperation.

ECSS-E-20A, Space Engineering Electrical and Electronic. This Standard establishes the basic rules and general principles applicable to the electrical, electronic, electromagnetic, microwave and optical 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, derivingfrom the system engineering requirements laid out in the Space System Engineering Standard ECSS-E-10.

ECSS-E-30 PART 2A, SPACE ENGINEERING, MECHANICAL - PART 2, STRUCTURAL. Part 2 of ECSS--E--30 in the engineering branch of ECSS Standards defines the mechanical engineering requirements for structural engineering. This Standard defines the requirements to be considered in all engineering aspects of structures: requirementdefinition and specification, design, development, verification, production, in-service and eventual disposal. The Standard applies to all general structural subsystemaspects of space products and in particular:Launch vehicles, transfer vehicles, re-entry vehicles, spacecraft, landing probes and rovers, sounding rockets, payloads and instruments, structural parts of all subsytems. 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.

ECSS-E-30 Part 5B (DRAFT), Space engineering Mechanical - Part 5: Propulsion. This Standard contains normative provisions for: solid propulsion for launchers and spacecraft, liquid propulsion for launchers, liquid propulsion for spacecraft, and electric propulsion for spacecraft.

ECSS-E-30 (PART 6A), SPACE ENGINEERING MECHANICAL - PART 6, PYROTECHNICS. Part 6 of ECSS--E--30 in the engineering branch of ECSS series of standards 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 itemused 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 wholemission 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 Standard should be tailored to match the genuine requirements of a particular profile and circumstances of a project.

ECSS-E-30 PART 7, SPACE ENGINEERING MECHANICAL - PART 7, MECHANICAL PARTS. Part 7 of ECSS--E--30 in the engineering branch of ECSS Standards defines mechanical engineering requirements for mechanical parts. This Standard defines the requirements and statements applicable to the selection, design, verification and application of mechanical parts to promote the use of high-quality non-critical mechanical parts that achieve robust functionality and satisfy the mission performance requirements. This Standard 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 space-proven 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 the content and extent of the mechanical parts and the requirements for its performance, design and test, product assurance and support activities. 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.

ECSS-E-30-01A, SPACE ENGINEERING, FRACTURE CONTROL. 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. 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.

ECSS-E-40 Part 1B, Space engineering Software - Part 1: Principles and requirements. This software engineering Standard concerns the “product software”, i.e. software that is part of a space system product tree and developed as part of a space project. This Standard is applicable, to the extent defined by the tailoring process, 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, transfer, operations and maintenance.

ECSS-E-40 Part 2B, Space engineering Software — Part 2: Document requirements definitions (DRDs). Part 2 of ECSS--E--40 “Space engineering -- Software” defines the content of the document requirements definitions (DRDs) for space software product, in order to organize into documents all the expected outputs of the requirements contained in of ECSS--E--40 Part 1 “Space engineering -- Software” and in ECSS--Q--80 “Space product assurance -- Software product assurance”.

ECSS-E-50-12A, SPACE ENGINEERING, SPACEWIRE - LINKS, NODES, ROUTERS, AND NETWORKS (24 JAN 2003)., This Standard specifies the physical interconnection media and data communication protocols to enable the reliable sending of data at high-speed (between 2 Mb/s and 400 Mb/s) from one unit to another. SpaceWire links are full-duplex, point-to-point, serial data communication links. The scope of this Standard is the physical connectors and cables, electrical properties, and logical protocols that comprise the SpaceWire data link. SpaceWire provides a means of sending packets of information from a source node to a specified destination node. SpaceWire does not specify the contents of the packets of information.

ECSS-E-60A, SPACE ENGINEERING, CONTROL ENGINEERING (14 SEP 2004)., This Standard deals with control systems developed as part of a space project. It is applicable to all the elements of a space system, including the space segment, the ground segment and the launch service segment. The standard covers all aspects of space control engineering including requirements definition, analysis, design, production, verification and validation, transfer, operations and maintenance. It defines the scope of the space control engineering process and its interfaces with management and product assurance, and explains how they apply to the control engineering process.

ECSS-E-70 Part 1A, SPACE ENGINEERING GROUND SYSTEMS AND OPERATIONS PART 1, PRINCIPLES AND REQUIREMENTS. Within the frame of the overall engineering standards for space missions, this Standard contains the basic rules, principles and requirements to be applied to the engineering of the ground segment and mission operations,which form anintegral part of the overall system implementing a space mission. This 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 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 Standard is applicable to all classes of missions it does not consider aspects that are specific to manned space missions.

ECSS-E-70 Part 2A, Space engineering - Ground systems and operations — Part 2: Document requirements definitions (DRDs). Part 2 of ECSS--E--70 “Space engineering — Ground systems and operations” defines the content of the document requirements definitions (DRDs) which are called up by other ECSS Standards and specifically referenced in ECSS--E--70 Part 1: “Principles and requirements”.

ECSS-M-00-02A, SPACE PROJECT MANAGEMENT TAILORING OF SPACE STANDARDS. This Standard is part of a collection of ECSS Standards belonging to the management branch. It defines the process of tailoring, applicable to all standards in the M--, Q--, and E-- branches of ECSS as a guideline. This Standard defines the objectives, principles, methods and processes of tailoring, which are necessary for the establishment of project requirement documents.

ECSS-M-00-03A, SPACE PROJECT MANAGEMENT RISK MANAGEMENT. This Standard defines, extending the requirements of ECSS--M--00, 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. This Standard contains a summary of the general risk management process, which is sub-divided 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 between all project domains, and provides visibility over risks,with a ranking according to their criticality for the project; these risks have to be monitored and controlled according to the rules defined for the domain to which they belong. The fields of application of this Standard are all the space project phases defined in ECSS--M--30.

ECSS-M-10 SPACE PROJECT MANAGEMENT PROJECT BREAKDOWN STRUCTURES. The present document, ‘Project Breakdown Structures’, is part of a collection of ECSS 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 ECSS standard is to define the principles to be respected for setting up, using and adapting the breakdown structures and implementing them into a project. 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.

ECSS–M–20A, SPACE PROJECT MANAGEMENT PROJECT ORGANISATION. The present document, ‘Project Organisation’, is part of a collection of ECSS standards belonging to the management branch. The purpose of this ECSS 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.

ECSS-M-30-01A, SPACE PROJECT MANAGEMENT ORGANIZATION AND CONDUCT OF REVIEWS. This Standard provides means for identifying and structuring all of the activities and information required in a project review. It identifies the information outputs and follow-up activities necessary to complete the review process. It also provides a check-list of activities and information required for each of themajor project reviews identified in the ECSS 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.

ECSS-M-30A, SPACE PROJECT MANAGEMENT PROJECT PHASING AND PLANNING. The present document, ‘Project Phasing and Planning’, is part of a collection of ECSS 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. These requirements are tailored in related Project Requirements Documents, and are applicable to any actor of a space project. This project phasing and planning document covers all the phases of the project.

ECSS-M-40A, SPACE PROJECT MANAGEMENT CONFIGURATION MANAGEMENT. The present document, ‘Configuration Management’, is part of a collection of ECSS standards belonging to the management branch. The purpose of this ECSS 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. These requirements, as tailored in the related Project Requirements Document, are applicable to any actor of a Space Project.

ECSS-M-40B, Space Project Management, Configuration Management. The present standard “Configuration management”, is part of a collection of ECSS Standards belonging to the Management branch. The scope of this standard is to describe the processes and provide the requirements for managing the configuration of products within a space programme or project.

ECSS-M-50A, Space Project Management,Information/documentation management. The present document ‘Information/Documentation Management’ is part of the collection of ECSS 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. These requirements, as tailored in related Project Requirements Documents, are applicable to any actor of a Space Project. Information management shall be implemented during all the phases of the project.

ECSS-M-60A, SPACE PROJECT MANAGEMENT COST AND SCHEDULE MANAGEMENT. The present document, ‘Cost and Schedule Management’, is part of a collection of ECSS 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.

ECSS-M-70A, SPACE PROJECT MANAGEMENT INTEGRATED LOGISTICS SUPPORT. The present document, ‘Integrated Logistic Support’, is part of a collection of ECSS 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. 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 objective (See also ECSS–M–00). The management requirements are applicable to those activities necessary to design, develop, deliver, deploy and manage an organised and structured set of materials and software, services, processes and information dedicated to support the Supported System throughout its life cycle.

ECSS-Q-20-09B, Space Product Assurance, Non-conformance control system. This Standard defines the control system for nonconformances related to any product, including EEE components nonconformances, software problems and operational nonconformances and anomalies. This Standard applies to all deliverable products and supplies, at all levels,which fail to conform to specification 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 or launch readiness, operational validation or qualification phase, operational phase, and refurbishment phase. his Standard defines also requirements for the interfaces with company internal nonconformance reporting and processing. Engineering changes are not subject of this Standard.

ECSS-Q-40B, Space Product Assurance, Safety. This Standard defines the safety programme and the technical safety requirements that are 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.

ECSS-Q-60-01A, European Preferred Parts List EPPL and Its Management. This Standard contains the European preferred parts list (EPPL) and provides the rules for establishing the list of preferred and suitable components to be used by European manufacturers of spacecraft hardware and associated equipment. The operating rules for management, administration and maintenance of the EPPL are defined in annex A of this Standard.

ECSS-Q-60-02A, Space product assurance, ASIC and FPGA development. This Standard defines a comprehensive set of requirements for the user development of digital, analog and mixed analog-digital custom designed integrated circuits, such as application specific integrated circuits (ASICs) and field programmable gate arrays (FPGAs). The user development includes all activities beginning with setting initial requirements and ending with the validation and release of prototype devices.

ECSS-Q-70-01A, SPACE PRODUCT ASSURANCE CLEANLINESS AND CONTAMINATION CONTROL (11 DEC 2002)., The objective of this Standard is to ensure a successful mission by the definition of acceptable contamination levels for space system elements, their achievement, and maintenance, throughout performance assessment versus contamination,facilities and tools definition for contamination control and monitoring, materials and processes selection, and planning of activities.

ECSS-Q-70-02A, SPACE PRODUCT ASSURANCE, THERMAL VACUUM OUTGASSING TEST FOR THE SCREENING OF SPACE MATERIALS (26 MAY 2000)., This Standard describes 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.

ECSS-Q-70-03A, SPACE PRODUCTS ASSURANCE, BLACK ANODIZING OF METALS WITH INORGANIC DYES (7 APR 2006)., The thermal control onboard spacecraft is mainly passive. It is based on the thermo-optical properties of the surfaces, namely emissivity and absorbance. The ratio of these two properties defines the equilibrium temperature of the surface. This Standard aims at providing the thermal-optical properties given by a surface treatment applied on a metallic surface to achieve an emissivity versus absorbance ratio close to unity, as requested for many applications.

ECSS-Q-70-04A, SPACE PRODUCT ASSURANCE THERMAL CYCLING TEST FOR THE SCREENING OF SPACE MATERIALS (4 OCT 1999)., Thermal cycling test under vacuum for the screening of space materials and processes intended for use i the fabrication of spacecraft an associated equipment. The test determines the ability of these or other articles to withstand changes of ambient temperature under vacuum.

ECSS-Q-70-05A, SPACE PRODUCT ASSURANCE, DETECTION OF ORGANIC CONTAMINATION OF SURFACES BY INFRARED SPECTROSCOPY (31 AUG 2005)., This Standard defines the test procedures for detecting organic contamination on surfaces using direct and indirect methods with the aid of infrared spectroscopy.

ECSS-Q-70-07A, SPACE PRODUCT ASSURANCE VERIFICATION AND APPROVAL OF AUTOMATIC MACHINE WAVE SOLDERING FOR USE IN SPACECRAFT HARDWARE (20 JAN 1998)., The process requirements for wave soldering of double-sided and multilayer boards are also defined.

ECSS-Q-70-08A, SPACE PRODUCT ASSURANCE, THE MANUAL SOLDERING OF HIGH-RELIABILITY ELECTRICAL CONNECTIONS (6 AUG 1999)., The main part of this Standard is based on recommendations from the National Aeronautics and Space Administration, and European soldering technology experts. Modifications have been incorporated into the text to provide for the specific requirement of low-outgassing electrical systems which are required by scientific and application satellites. Other additions have been made in the light of recent technological advances and results of metallurgical test pro grammes. The methods and workmanship contained in this document are considered to be fully approved for normal spacecraft requirements.

ECSS-Q-70-09A, SPACE PRODUCT ASSURANCE, MEASUREMENT OF THERMAL-OPTICAL PROPERTIES OF THERMAL CONTROL MATERIALS (29 AUG 2003)., The thermo-optical properties of materials are of importance to enable the calculation of the thermal housekeeping and radiative heat transfer. This Standard describes the methodology, instruments, equipment and samples, used to calculate the thermo-optical properties of thermal-control materials, i.e. solar absorptance [αs or αp] and the infrared emittance [εh or εn]. In general this procedure has been written in connection with instruments and equipment available at ONERA, INTESPACE and ESTEC; however, any contractor is encouraged to built up his own instrument or equipment provided the accuracy of the results is equivalent to the one specified herein.

ECSS-Q-70-10A, SPACECRAFT PRODUCT ASSURANCE, QUALIFICATION OF PRINTED CIRCUIT BOARDS (23 NOV 2001)., This Standard defines requirements for evaluation, qualification and maintenance of qualification of space PCB suppliers for different types of printed circuit boards.

ECSS-Q-70-11A, SPACECRAFT PRODUCT ASSURANCE, PROCUREMENT OF PRINTED CIRCUIT BOARDS (23 NOV 2001)., This Standard defines the requirements imposed on both the customer and the qualified PCB supplier for PCB procurement. This Standard also details the basic requirements for procurement of PCBs as well as the minimum requirements for the different types of PCBs.

ECSS-Q-70-13A, SPACE PRODUCT ASSURANCE MEASUREMENT OF THE PEEL AND PULL-OFF STRENGTH OF COATINGS (4 OCT 1999). This 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.

ECSS-Q-70-18A, SPACE PRODUCT ASSURANCE, PREPARATION, ASSEMBLY, AND MOUNTING OF RF COAXIAL CABLES (31 AUG 2001)., This Standard defines the technical requirements and quality assurance provi- sions for the assembly and mounting of high-reliability, radio-frequency (RF) coaxial-cable interconnections for use as transmission lines in spacecraft and associated equipment. In general, these assemblies are designed for low-loss, stable operation from the relatively low frequencies through the higher frequencies in the microwave regions. These transmission-line cables should not be confused with low-frequency cables with conductive sheaths (usually copper braid), which are used in applications where shielding of the centre conductors from the surrounding electrical ambient is required. The interconnection of those shielded cables is covered in ECSS-Q-70-08.

ECSS-Q-70-20A, SPACE PRODUCT ASSURANCE, DETERMINATION OF THE SUSCEPTIBILITY OF SILVER-PLATED COPPER WIRE AND CABLE TO "RED-PLAGUE" CORROSION (19 DEC 2000)., Silver-plated copper conductors are suitable for general spacecraft use, but it is essential that the plating is of uniform thickness of at least 2 μm. Localized damage due to wire or cable fabrication processes (e.g. stranding, braiding, application of insulation jackets) can result in spots in the plating where the thickness is less that 1 μm.Wire strands supporting silver platings less than 1 μmthick are susceptible to red-plague corrosion. The deleterious effects to be anticipated as a result of testing wires and cables to the requirements of this Standard, which is accelerated by means of oxygen, high humidity and elevated temperature, include corrosion of all defective silver-plated conductor materials and shielding braid or the strands of internal conductors. Silver-plated copper wires or cables that are tested and successfully pass the acceptance criteria as defined in this Standard are considered not to suffer from degradation by red-plague corrosion during ten-year controlled storage periods and normal spacecraft service lifetimes.

ECSS-Q-70-21A, SPACE PRODUCT ASSURANCE, FLAMMABILITY TESTING FOR THE SCREENING OF SPACE MATERIALS (4 OCT 1999). This Standard defines a multi-test procedure for the determination of the flammability characteristics of non-metallic materials under a set of closely controlled conditions. The test procedure covers 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 characteristics of materials.

ECSS-Q-70-22A, SPACE PRODUCT ASSURANCE, THE CONTROL OF LIMITED SHELF-LIFE MATERIALS (21 JAN 2000)., This Standard defines the procedure to be used for the control of limited shelf-life materials employed in the fabrication of spacecraft and associated equipment.

ECSS-Q-70-25A, SPACE PRODUCT ASSURANCE, APPLICATION OF THE BLACK COATING AEROGLAZE Z306 (30 JUL 1999).,This Standard defines the process for producing a low outgassing matt black coating to spacecraft or associated equipment, by means of the application of Aeroglaze Z306 (formerly Chemglaze Z306) black polyurethane paint on P123 three part epoxy primer.

ECSS-Q-70-26A, SPACE PRODUCT ASSURANCE CRIMPING OF HIGH-RELIABILITY ELECTRICAL CONNECTIONS (13 FEB 2001). The methods used for preparing and assembling the parts to be joined by crimping, and the selection, calibration, use and verification of the crimping tools are part of this Standard.

ECSS-Q-70-28A, SPACE PRODUCT ASSURANCE, REPAIR AND MODIFICATION OF PRINTED CIRCUIT BOARD ASSEMBLIES FOR SPACE USE (21 JUN 2002)., The repair and modification procedures detailed in this Standard are designed to maintain the rigorous standards set by the customer for the manufacture and assembly of space-quality printed circuit boards. This Standard is confined to the repair and modification of single-sided, double- sided and multi-layer printed circuit board assemblies. However, rework may be necessary on defective solder joints as a consequence of the repair or modification process. Unassembled (bare) printed circuit boards are not covered by this Stan- dard.

ECSS-Q-70-29A, SPACE PRODUCT ASSURANCE, OFFGASSING PRODUCTS (30 JUL 1999)., 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.

ECSS-Q-70-30A, SPACE PRODUCT ASSURANCE, WIRE-WRAPPING OF HIGH-RELIABILITY ELECTRICAL CONNECTIONS (4 OCT 1999)., This Standard specifies the methods for preparing and assembling the parts to be joined by wire wrapping, and the selection, calibration, use and certification of the wire wrapping tools.

ECSS-Q-70-33A, SPACE PRODUCT ASSURANCE, THE APPLICATION OF THE THERMAL CONTROL COATING PSF120FD (30 JUN 1999)., This Standard defines the process by which PSG120FD white, zinc-oxide-pigmented,silicone-based coating (paint) is used to produce a low outgassing, thermal control coating on spacecraft items.

ECSS-Q-70-34A, SPACE PRODUCT ASSURANCE, THE APPLICATION OF THE BLACK ELECTRICALLY CONDUCTIVE COATING AEROGLAZE H322 (30 JUL 1999)., The most critical use of paints in satellites is in the thermal-control subsystem. Electrically conductive thermal-control paints are utilized to avoid charging-up and discharges in geostationary orbit. One such paint is Aeroglaze H322 (formerly Chemglaze H322), a proprietary black electrically conductive coating manufactured by Lord Corporation Ltd. Lesonal 01--66050 primer ismanufactured by LesonalGmbH,Germany. The coating is normally used without a primer. Exceptions are in particularly severe conditions such as low temperatures or where the coating is applied on very smooth surfaces (i.e. aluminized side of aluminized Kapton).

ECSS-Q-70-35A, SPACE PRODUCT ASSURANCE, THE APPLICATION OF THE BLACK ELECTRICALLY CONDUCTIVE CONDUCTIVE COATING AEROGLAZE L300 (30 JUL 1999)., The most critical use of paints in satellites is in the thermal control subsystem. Electrically conductive thermal-control paints are utilized to avoid charging-up and discharges in geostationary orbit. One such paint is Aeroglaze L300 (formerly Chemglaze L300), a proprietary, black, electrically conductive coating manufactured by Lord Corporation Ltd.

ECSS-Q-70-36A, SPACE PRODUCT ASSURANCE, MATERIAL SELECTION FOR CONTROLLING STRESS-CORROSION CRACKING (20 JAN 1998)., This document 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 will be prevented. Three categories ofmaterials are listed in Tables 1, 2 and 3 of this document. They represent metal alloys with a high, moderate and low resistance to stress-cor- rosion cracking. The stress-corrosion susceptibility of alloys included in this document was deter- mined at ambient temperature D by means of laboratory tests in which specimens were either sprayed with salt water or periodically immersed and withdrawn; D by exposing specimens in sea coast or mild industrial environments; D 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.

ECSS-Q-70-37A, SPACE PRODUCT ASSURANCE, DETERMINATION OF THE SUSCEPTIBILITY OF METALS TO STRESS-CORROSION CRACKING (20 JAN 1998)., This document defines the preferred way to determine the susceptibility ofmetals and weldments to stress-corrosion cracking by alternate immersion in 3,5 % so- dium chloride under constant load. The results obtained from test programmes made according to this specification are used to classify alloys, weldments and their individual heat treatment condi- tions. When sufficient stress-corrosion data exists the alloy designations may be submitted for inclusion into the various tables contained in ECSS-Q-70-36.

ECSS-Q-70-38A, SPACE PRODUCT ASSURANCE HIGH-RELIABILITY SOLDERING FOR SURFACE-MOUNT AND MIXED TECHNOLOGY (26 OCT 2007)., This Standard prescribes requirements for electrical connections of leadless and leaded surface mounted devices (SMD) on spacecraft and associated equipment, utilizing a range of substrate assemblies and employing solder as the interconnection media.

ECSS-Q-70-45A (DRAFT), SPACE PRODUCT ASSURANCE, STANDARD METHODS FOR MECHANICAL TESTING OF METALLIC MATERIALS (28 JUL 2003)., This Standard defines the requirements for mechanical testing of metallic materials to be used in the fabrication of spacecraft hardware. This Standard establishes the requirements for most relevant test methods carried out to assess the tensile, fatigue and fracture properties of metallic materials. It does not give a complete review of all the existing test methods for the evaluation of mechanical properties of metallic materials. Furthermore, this Standard gives the requirements and guidelines for the evaluation, presentation and reporting of test results.

ECSS-Q-70-46A (DRAFT), SPACE PRODUCT ASSURANCE, REQUIREMENTS FOR MANUFACTURING AND PROCUREMENT OF THREADED FASTENERS (12 JAN 2004)., This Standard defines the minimum requirements for manufacturing, provision, inspection and quality control of high-quality threaded fastening devices (bolts, nuts, studs and screws) hereafter referred to as threaded fasteners or fasteners, used in space hardware. This Standard does not include a complete review of the factors relevant to the fabrication of high quality threaded fasteners. It provides guidelines to the customer and the supplier in the definition of the technical requirements and quality control procedures to be applied in the fabrication and supply of threaded fasteners for spacecraft applications. NOTE Fasteners for spacecraft applications are those aerospace standard fasteners (i.e. in accordance with LN,DIN or other national or international aerospace standards), or those fasteners meeting or exceeding the requirements in ISO 4759-1 for “Product grade A”, which also fulfil the requirements for space applications as specified in the present document

ECSS-Q-70-71A REV. 1, SPACE PRODUCT ASSURANCE DATA FOR SELECTION OF SPACE MATERIALS AND PROCESSES. General requirements for materials and their associated processes are provided in this Standard along with the environmental requirements for materials application in space. Annex A (informative) contains guidelines for each class of material used in the declared materials list (DML) in ECSS--Q--70 and factors to be considered for process selection. Annex B (informative) contains data sheets for materials that can be considered for use in space applications i.e. materials that were used successfully for some applications in space systems and associated equipment. Data sheets contain: property data -- either from manufacturers or determined by test, and comments onmaterial application in space conditions. The data sheets are grouped by their DML material class, using the class number, e.g. Class 1: Aluminium and Al-- alloys; and Class 10: Adhesives, coatings and varnishes.

ECSS-Q-70B, SPACE PRODUCT ASSURANCE, MATERIALS, MECHANCIAL PARTS, AND PROCESSES (14 DEC 2004)., 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 also defines the documentation requirements and the procedures relevant to obtaining approval for the use of materials, mechanical parts and processes in the fabrication of space systems and associated equipment. This Standard covers the following: management, including organization, reviews, acceptance status and documentation control; selection criteria and rules; evaluation, validation and qualification, or verification testing; procurement and receiving inspection; utilization criteria and rules. The relationship between activities and programme phases is defined in Annex A. The provisions of this Standard apply to all factors involved at all levels in the production of space systems. These can include manned and unmanned spacecraft, launchers, satellites, payloads, experiments, electrical ground support equipment, mechanical ground support equipment, and their corresponding organizations.

ECSS-Q-80B (Draft 1), Space product assurance, Software product assurance. This Standard defines a set of software product assurance requirements to be used for the development and maintenance of software for space systems. Space systems include manned and unmanned spacecraft, launchers, payloads, experiments and their associated ground equipment and facilities. Software includes the software component of firmware. This Standard also applies to the development of non-deliverable software which affects the quality of the deliverable product or service provided by a space system, if the service is implemented by software.

ECSS-S-00A, ECSS SYSTEM DESCRIPTION AND IMPLEMENTATION. This document serves as a reference for the application of ECSS Standards to all categories of space projects by providing a description of the ECSS System and the method of implementation. The implementation of ECSS Standards relies upon the fact that they are tailorable to different project requirements and apply to all phases and activities from the beginning to the end of a project, including mission analysis and disposal.

ESA-ATV-1700.7B, SAFETY REQUIREMENTS FOR PAYLOADS/CARGOS ON BOARD THE ATV (NOV 2004 - ISSUE 1). This document establishes the safety requirements applicable to payloads/cargos transported to the ISS in the pressurized module of the European Automated Transfer Vehicle.

ESSB-AS V1.4, ESA APPROVED STANDARDS (VER. 1.4), ISSUED BY THE ESA STANDARDIZATION STEERING BOARD (ESSB) (4 NOV 2003).

ESSB-AS V1.4, ESA APPROVED STANDARDS (VERSION 1.4) ISSUED BY THE ESA STANDARDIZATION STEEERING BOARD (ESSB).

SCI-A/2004/175/AO, SOLAR ORBITER PAYLOAD DEFINITION DOCUMENT - ISSUE 4 - REV. 1 (8 AUG 2005). This Payload Definition Document (PDD) is a compilation of the Solar Orbiter reference payload requirements and of their related reference design. The PDD plays a key role in defining the resources required by the Solar Orbiter instruments and in providing the information necessary to conduct the mission assessment study and the preliminary spacecraft design.

SOL-EST-IF-005, SOLAR ORBITER EXPERIMENT INTERFACE DOCUMENT - PART A (9OCT07). In May 2002, the new ESA Science Programme (Cosmic Vision 2020) was defined and presented to SPC. This programme contains groups of scientific missions related either technically or programmatically. One such mission group comprises: • The Bepi Colombo mission to Mercury which includes two orbiting spacecraft, • The Solar Orbiter mission which will permit close-up and high-latitude studies of the Sun. At its 105th meeting held on 5-6 November 2003, in response to the SSAC proposal concerning the reconstruction of the ESA Science Programme, the SPC decided to maintain Solar Orbiter in the Cosmic Vision Programme 2003-2013. The 107th meeting of ESA's Science Programme Committee on 7-8 June 2004 endorsed the recommendations of the SSWG and SSAC and confirmed the place of Solar Orbiter in the Cosmic Vision programme. This was reconfirmed at the SPC meeting on 8-9 February, 2006 with the assumption of the implementation of a May 2015 launch. At its meeting in May 2006, the SPC directed the Science programme Directorate to proceed with a Call for Letters of Intent for the payload complement, to optimize the mission in terms of science requirements and industrial implementation and to seek international cooperation, so as to bring the mission back into an acceptable cost envelope to ESA and maintain the possibility for a launch in 2015. These activities were carried out as directed by the SPC from June 2006 to October 2007. The Call for Letters of Intent elicited 23 responses, covering all scientific measurements and providing inputs to instrument accommodation studies that were performed with Industry. Industrial studies were also carried out to optimize the spacecraft design and advance critical technologies. ESA and NASA cooperated to define a joint mission composed of ESA’s Solar Orbiter and NASA’s Inner Heliospheric Sentinels projects which will have coordinated instrument Announcement of Opportunities. The science objectives of the joint mission were established by a Joint Science and Technology Definition Team. The outcome of these activities will be reviewed in November 2007 when the SPC is asked to decide how and whether to proceed with the mission. The Experiment Interface Document (EID) will be first released with the instrument AO. The purpose of the document is to ensure that: • The Principal Investigators (PIs) design, build and verify their instruments within the technical constraints imposed by the Solar Orbiter spacecraft and compatible with the Solar Orbiter programme constraints. • The Solar Orbiter Prime Contractor designs, builds and verifies the spacecraft such that the instruments can be successfully integrated into the system. • The spacecraft can be successfully launched and operated to achieve the scientific objectives of the Solar Orbiter mission. The EID consists of two parts; A and B. The EID-A contains the interface specifications that are applied to the design of the instrument as defined in the EID Part B written by the Principal Investigator. Part A defines the Solar Orbiter technical and programmatic requirements all Solar Orbiter PI’s have to comply with. The EID-B defines the PI response to the technical requirements in part A specifying in detail the interface information applicable to a particular experiment. Part B will form the sole formal and binding document for all technical and programmatic agreements between the ESA Solar Orbiter Project Office and each Solar Orbiter Principal Investigator. The EID A and B shall be placed under formal configuration and change control once signed and thus any change requires formal agreement between ESA and the PI. The EID A and B will become applicable documents to the Solar Orbiter prime contractor.

SOL-EST-IF-0050, SOLAR ORBITER - EXPERIMENT INTERFACE DOCUMENT - PART A - ISSUE 1 - REV 0 (9 OCT 2007). The Experiment Interface Document (EID) will be first released with the instrument AO. The purpose of the document is to ensure that: The Principal Investigators (PIs) design, build and verify their instruments within the technical constraints imposed by the Solar Orbiter spacecraft and compatible with the Solar Orbiter programme constraints. • The Solar Orbiter Prime Contractor designs, builds and verifies the spacecraft such that the instruments can be successfully integrated into the system. • The spacecraft can be successfully launched and operated to achieve the scientific objectives of the Solar Orbiter mission. The EID consists of two parts; A and B. The EID-A contains the interface specifications that are applied to the design of the instrument as defined in the EID Part B written by the Principal Investigator. Part A defines the Solar Orbiter technical and programmatic requirements all Solar Orbiter PI’s have to comply with. The EID-B defines the PI response to the technical requirements in part A specifying in detail the interface information applicable to a particular experiment. Part B will form the sole formal and binding document for all technical and programmatic agreements between the ESA Solar Orbiter Project Office and each Solar Orbiter Principal Investigator. The EID A and B shall be placed under formal configuration and change control once signed and thus any change requires formal agreement between ESA and the PI. The EID A and B will become applicable documents to the Solar Orbiter prime contractor.

TEC-EES-03-034/JS. The Space Environment can cause severe problems for any space system including the Solar Orbiter on its mission to the innermost regions of the solar system. Proper assessment of the potential effects is an essential part of the engineering process leading to the construction of any element of the spacecraft. It is important that this is taken into account from the earliest phases of a project when consideration is given to mass budget, protection, component selection policy, etc. As the design of an element is developed, further engineering iteration is normally necessary with more detailed analysis. This document is intended to assist the developers of instruments for the Solar Orbiter in assessing the effects of the space environment on their systems. The document is based on the ECSS-E-10-04 Space Environment Standard, from which most of the background information has been taken (ECSS is a cooperative effort of the European Space Agency, National Space Agencies and European industry associations for the purpose of developing and maintaining common standards). The ECSSE- 10-04 standard can also be accessed via the WWW site http://www.estec.esa.nl/wmwww/wma/.