M/496 - Space Industry (phase 3)

This standard defines 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 standard includes:
•   verification planning requirements,
•   definition of a route to conform to the requirements,
•   design and test margin requirements,
•   design and test requirements, and
•   informative annexes that provide guidelines on the design and test processes.
This standard 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 standard 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. This standard does not include breakdown processes caused by collisional processes, such as plasma formation.
This standard is applicable to all space missions.
NOTE    Multipactor in multi-carrier operation is currently being investigated. Hence, please be aware that this document provides only recommendations to multi-carrier operation. These recommendations are provisional and will be reviewed in future versions.
This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.

Like the other ENs of the whole series, this EN deals with the use of GNSS-based positioning terminals (GBPT) in road Intelligent Transport Systems (ITS). GNSS-based positioning means that the system providing position data, more precisely Position, Velocity and Time (PVT) data, comprises at least a GNSS receiver and, potentially, for performance improvement, other additional sensor data or sources of information that can be hybridized with GNSS data.
This new EN proposes testing procedures, based on the replay of data recorded during field tests, to assess the basic performances of any GBPT for a given use case described by an operational scenario. These tests address the basic performance features Availability, Continuity, Accuracy and Integrity of the PVT information, but also the Time-To-First-Fix (TTFF) performance feature, as they are described in EN 16803-1, considering that there is no particular security attack affecting the SIS during the operation. This EN does not cover the assessment tests of the timing performances other than TTFF, which do not need field data and can preferably be executed in the lab with current instruments.
"Record and Replay" (R&R) tests consist in replaying in a laboratory environment GNSS SIS data, and potentially additional sensor data, recorded in specific operational conditions thanks to a specific test vehicle. The dataset comprising GNSS SIS data and potential sensor data resulting from these field tests, together with the corresponding metadata description file, is called a "test scenario". A dataset is composed of several data files.
This EN 16803-3 addresses the "Replay" part of the test scenario data set. It does not address the "Record" part, although it describes as informative information the whole R&R process. This "Record" part will be covered by EN 16803-4 under preparation.
Although the EN 16803 series concerns the GNSS-based positioning terminals and not only the GNSS receivers, the present release of this EN addresses only the replay process of GNSS only terminals. The reason is that the process of replaying in the lab additional sensor data, especially when these sensors are capturing the vehicle’s motion, is generally very complex and not mature enough to be standardized today. It would need open standardized interfaces in the GBPT as well as standardized sensor error models and is not ready to be standardized. But, the procedure described in the present EN has been designed to be extended to GBPT hybridizing GNSS and vehicle sensors in the future.
This EN 16803-3 does not address R&R tests when specific radio frequency signals simulating security attacks are added to the SIS. This case is specifically the topic of EN 16803-3.
Once standardized assessment tests procedures have been established, it is possible to set minimum performance requirements for various intelligent transport applications but it makes sense to separate the assessment tests issue from minimum performance requirements, because the same test procedure may be applicable to many applications, but the minimum performance requirements typically vary from one application to another. So, this EN does not set minimum performance requirements for any application.

This document shall be considered as a complementary standard to EN 16803-2 that is intended to assessment of the performances of a GBPT placed in real-life or simulated road environments. This document is instead specifically targeting security attacks such as interferences, jamming, meaconing or spoofing. This document cannot be applied independently from EN 16803-2 that describes in details the general methodology of the assessment procedure.
This document provides normative information necessary to replay in the lab standardized scenarios specifically dedicated to security tests applied to GNSS.
Depending on the case (jamming or spoofing), these scenarios are composed of data sets combining either real life recorded SIS and jamming signals or simulated SIS and spoofing signals. The reason for that will be explained in Clause 6.
Although a high-level categorization of GNSS attacks is given in Annex A, a comprehensive and detailed categorization of possible GNSS attacks is out of the scope of this document.
It is not the aim of this EN to standardize the record procedure neither to define the specific requirements for the generation of the attack scenarios. The record procedure itself and its quality framework for accredited GNSS-specialized laboratories (Lab-A), with the detailed definition of standardized attack scenarios, will be totally and precisely described in EN 16803-4 (under preparation). The list of attack scenarios will have to be regularly updated considering the evolution of GNSS technologies, emerging threats, and countermeasures.

EN 16803-1 addresses the final stage of the performance management approach, i.e. the assessment of the whole Road ITS system performance equipped with a given Positioning System, using the Sensitivity analysis method.
EN 16803-1 addresses the identification and the definition the positioning performance features and metrics required for Positioning System assessment.
This document gives definitions of the various items to be considered when specifying an Operational scenario and provides a method to compare finely two environments with respect to their effects on GNSS positioning performance.
This document gives definition of the most important terms used all along the document and describes the architecture of a Road ITS system based on GNSS as it is intended in this standard.
This document does not address:
-   the performance metrics to be used to define the Road ITS system performance requirements, highly depending on the use case and the will of the owner of the system;
-   the performance requirements of the various kinds of Road ITS systems;
-   the tests that are necessary to assess Positioning System performances (Record and Replay tests for this purpose will be addressed by prEN 16803-2 and prEN 16803-3.

The scope of the SpaceFibre standard is the detailed specification a very high-speed serial link protocol stack reaching from link level Quality layer  down to the Physical layer. The higher layers like packet, network and higher level protocols are the same as for SpaceWire and specified in the respective standards ECSS-E-ST-50-12C and ECSS-E-ST-50-51C to 53C.

This activity will be the update of EN16603-20-06 (published 2014).
This activity was started in ECSS to implement as urgent classified Change Requests.

This standard specifies the requirements, also known as "relifing requirements", for the planned, intentional storage, control, and removal from storage of electronic, electrical and electromechanical parts which are intended to be used for space applications.
This standard covers the relifing of all components as defined by ECSS-Q-ST-60 and ECSS-Q-ST-60-13.
The relifing process is a lot quality control activity.  The inspections and tests defined do not constitute an up-screening or up-grading of components to a higher level of quality than procured to.
In line with ECSS-Q-ST-60, this standard differentiates between classes of components through different sets of standardization requirements.
The classes provide levels of trade-off between assurance and risk. The highest assurance and lowest risk is provided by Class 1 and the lowest assurance and highest risk by Class 3. Procurement costs are typically highest for Class 1 and lowest for Class 3. Mitigation and other engineering measures can decrease the total cost of ownership differences between the three classes. The project objectives, definition and constraints determine which class or classes of components are appropriate to be utilised within the system and subsystems.
-   Class 1 components are described in Clause 4, 5 and 6
-   Class 2 components are described in Clause 4, 5 and 6
-   Class 3 components are described in Clause 4, 5 and 7
The requirements of this document apply to all parties involved at all levels in the integration of EEE components into space segment hardware and launchers.
This standard is applicable to all EEE parts covered by ECSS-Q-ST-60 and used in space programmes.
This standard is not applicable to dice.
This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.

This Standard establishes the basic rules and general principles applicable to the electrical, electronic, electromagnetic, microwave and engineering processes. It specifies the tasks of these engineering processes and the basic performance and design requirements in each discipline.
It defines the terminology for the activities within these areas.
It defines the specific requirements for electrical subsystems and payloads, deriving from the system engineering requirements laid out in ECSS-E-ST-10 “Space engineering – System engineering general requirements”.
This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.

This Standard specifies star sensor performances as part of a space project. The Standard covers all aspects of performances, including nomenclature, definitions, and performance requirements for the performance specification of star sensors.
The Standard focuses on:
- performance specifications (including the impact of temperature, radiation and straylight environments);
- robustness (ability to maintain functionalities under non nominal environmental conditions).
Other specification types, for example mass and power, housekeeping data and data structures, are outside the scope of this Standard.
This Standard also proposes a standard core of functional interfaces defined by unit suppliers and avionics primes in the context of Space AVionics Open Interface aRchitecture (SAVOIR) initiative.
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.
This standard may be tailored for the specific characteristics and constraints of a space project in conformance with ECSS-S-ST-00.

The objective is to analyse the security issues that can occur at the GNSS SIS level. In order to do so, a full taxonomy of the GNSS SIS attacks are proposed and GNSS SIS attack security model are elaborated and classified. Security metrics for the validation of the GBPT robustness performances are defined.
The proposed methodology for this technical report consists in three distinct steps that are described hereunder:
I. The first step consists in providing a full taxonomy of the possible GNSS Signal in Space attacks (voluntary or not) to be considered and identify their impact at GBPT level;
II. The second step consists in regrouping narrow sets of previouslyidentified GNSS SIS attacks into security attack models. For each security attack model, an assessment of the dangerousness based on beforehand identified key parameters and methodology will be provided;
III. The third step consists in providing definition of performance objectives, security control, security metrics, and a specific procedure for a robustness evaluation of a GBPT against the identified security attack models at step II.
The results will benefit to the EN16803-3 "Assessment of security performances of GNSS based positioning terminals"

1.1   Purpose:
The "Scheduling and Commanding Messages" (SCM) specifies a standard format for observing system commanding and scheduling. This document aims to ease the planning and operation processes and to reduce the effors from researchers that use several different observing systems and/or simulation software products.
The SCM establishes a common language for exchanging information on planning, scheduling, and executing observations of celestial objects. In the end this will:
a)   Facilitate interoperability and enable consistent warning between data originators who supply celestial observations and the entities or researchers who use it; and
b)   Facilitate the automation of observation processes.
1.2   Applicability:
The SCM is applicable to ground-based activities related to the planning, scheduling, and execution of the observations of celestial objects. It is used by planning software, scheduling software, telescope commanding software. It is applicable for optical telescopes.

1.1   Purpose:
The Observing System Data Message (OSDM) is a standard message format to be used in the exchange of optical telescope, laser ranging station, and radar (observing systems) information between Space situational Awareness (SSA) data providers, owners/operators of observing systems, and other parties. These messages can inform SSA data providers, which are the consumers of observing system output data, on the parameters of the observing systems.
The OSDM standard will:
a)   enable consistent data exchange between observation data providers and SSA systems;
b)   facilitate data exchange automation and ingestion of observation data from different providers;
c)   facilitate SSA system architecture performance simulations; and
d)   provide a quick way to estimate the expected performance from one observing system.
1.2   Applicability:
The Observing System Data Message standard is applicable to all SSA activities, especially Space Surveillance and Tracking (SST) and near-Earth objects (NEO), and other fields where the acquisition of astrometric and photometric data plays a role (e.g. space debris, observational astronomy). The standard contains a message designed to contain observing system parameters exchanged between producers and consumers of astrometric and/or photometric data. These data include observing system name, location, type (optical/radar), operator and tracking/survey performance.
The OSDM is suitable for both manual and automated interaction, but will not contain a large amount of data. The message is self contained and can be paired with several Tracking Data Messages (TDM – specified reference [1]), FITS images (specified in reference [2]), or other formats containing the observation data.
The OSDM standard only applies to the message format, structure and content. The exchange method is beyond the scope of the standard, and it is due to be specified in an ICD, though an ICD is not always required. The methods used to produce the data in the message are also beyond the scope of the standard.
1.3   Document structure:
Clause 5 provides an overview of the OSDM.
Clause 6 described the structure and content of the 'keyword = value' (KVN) version of the OSDM.
Clause 7 described the strucuture and content of the XML version of the OSDM.
Clause 8 describes the data and syntax of OSDM messages, in both KVN and XML.
Annex A lists agreed values for some of the OSDM keywords.
Annex B presents some examples of OSDMs.

The document defines the requirements for the interfaces of simulation models between simulation
environments.

In general terms, the scope of the consolidation of the electrical interface
requirements for electrical (hold down and release or deployment) actuators in
the present ECSS-E-ST-20-21 and the relevant explanation in the handbook
ECSS-E-HB-20-21 is to allow a more recurrent approach both for actuator
electronics (power source) and electrical actuators (power load) offered by the
relevant manufacturers, at the benefit of the system integrators and of the
Agency, thus ensuring:
• better quality,
• stability of performances, and
• independence of the products from specific mission targets.
A recurrent approach enables manufacturing companies to concentrate on
products and a small step improvement approach that is the basis of a high
quality industrial output.

The purpose of this Standard is to define the Factors Of Safety (FOS), Design Factor and additional factors to be used for the dimensioning and design verification of spaceflight hardware including qualification and acceptance tests.
This standard is not self standing and is used in conjunction with the ECSS-E-ST-32, ECSS-E-ST-32-02 and ECSS-E-ST-33-01 documents.
Following assumptions are made in the document:
-   that recognized methodologies are used for the determination of the limit loads, including their scatter, that are applied to the hardware and for the stress analyses;
-   that the structural and mechanical system design is amenable to engineering analyses by current state-of-the-art methods and is conforming to standard aerospace industry practices.
Factors of safety are defined to cover chosen load level probability, assumed uncertainty in mechanical properties and manufacturing but not a lack of engineering effort.
The choice of a factor of safety for a program is directly linked to the rationale retained for designing, dimensioning and testing within the program. Therefore, as the development logic and the associated reliability objectives are different for:
-   unmanned scientific or commercial satellite,
-   expendable launch vehicles,
-   man-rated spacecraft, and
-   any other unmanned space vehicle (e.g. transfer vehicle, planetary probe)
specific values are presented for each of them.
Factors of safety for re-usable launch vehicles and man-rated commercial spacecraft are not addressed in this document.
For all of these space products, factors of safety are defined hereafter in the document whatever the adopted qualification logic: proto-flight or prototype model.
For pressurized hardware, factors of safety for all loads except internal pressure loads are defined in this standard. Concerning the internal pressure, the factors of safety for pressurised hardware can be found in ECSS-E-ST-32-02. For loads combination refer to ECSS-E-ST-32-02.
For mechanisms, specific factors of safety associated with yield and ultimate of metallic materials, cable rupture factors of safety, stops/shaft shoulders/recess yield factors of safety and limits for peak Hertzian contact stress are specified in ECSS-E-ST-33-01.
Alternate approach
The factors of safety specified hereafter are applied using a deterministic approach i.e. as generally applied in the Space Industry to achieve the structures standard reliability objectives. Structural safety based on a probabilistic analysis could be an alternate approach but it has to be demonstrated this process achieves the reliability objective specified to the structure. The procedure is approved by the customer.
This standard may be tailored for the specific characteristics and constraints of a space project in conformance with ECSS-S-ST-00.

This document regards the test procedures for assessment of robustness to security attacks.
Starting from the definition of security attacks taxonomy and security metrics, this TR aims to:
1. Specify test facilities to be used in the tests of GPBT. This comprises both hardware and software equipment.
2. Define relevant test scenarios applicable to security performances. Also the field test needed for validation of scenarios will be properly described.
3. Define end-to-end test procedures comprising experimental validation of the whole test chain.
The results will benefit to the operational basis of EN16803-3 "Assessment of security performances of GNSS based
positioning terminals".

The purpose is to define the tests to be performed in order to evaluate the performances of road applications’ GNSS-based positioning terminal (GBPT). To fully define the tests, this task will address the test strategy, the facilities to be used, the test scenarios (e.g. environments and characteristics, which shall allow the comparison of different tests), and the test procedures. The defined tests and process will be validated by performing various in-field tests. The defined tests focus essentially on accuracy, integrity and availability as required in the statement of work included in the invitation to tender.
This document will benefit to:
- The consolidation of EN 16803-1: "Definitions and system engineering procedures for the establishment and assessment of performances"
- The elaboration of EN 16803-2: "Assessment of basic performances of GNSS-based positioning terminals"
- The elaboration of EN 16803-3: "Assessment of security performances of GNSS based positioning terminals".

This standard specifies requirements for the durability testing of coatings most commonly used for space applications, i.e.:
-   Thin film optical coatings
-   Thermo-optical and thermal control coatings (the majority are paints, metallic deposits and coatings for stray light reduction)
-   Metallic coatings for other applications (RF, electrical, corrosion protection)
This standard covers testing for both ground and in-orbit phases of a space mission, mainly for satellite applications.
This standard applies to coatings within off the shelf items
This standard specifies the types of test to be performed for each class of coating, covering the different phases of a space project (evaluation, qualification and acceptance)
This standard does not cover:
-   The particular qualification requirements for a specific mission
-   Specific applications of coatings for launchers (e.g. high temperature coatings)
-   Specific functional testing requirements for the different coating classes
-   Test requirements for long term storage
-   Solar cell cover glass coatings
-   Surface treatments and conformal coatings applied on EEE parts

This Standard defines the quality assurance (QA) requirements for the establishment and implementation of a Quality Assurance
programme for products of space projects. Discipline related qualification activities are complemented in standards specific to those
disciplines (e.g. ECSS-E-ST-32-01 for fracture control).
For software quality assurance, the software product assurance standard, ECSS-Q-ST-80 is applicable.
This Standard is applicable to all space projects.
This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.
For the tailoring of this standard the following information is provided:
- A table providing the pre-tailoring per "Product types" in clause 6
- A table providing the pre-tailoring per "Project phase" in Annex J

This Standard defines the requirements for the control of nonconformances.
This Standard applies to all deliverable products and supplies, at all levels, which fail to conform to project requirements.
This Standard is applicable throughout the whole project lifecycle as defined in ECSS-M-ST-10.
This standard may be tailored for the specific characteristics and constrains of a space project in conformance with ECSS-S-ST-00.

This Standard specifies the physical interconnection media and data communication protocols to enable the reliable sending of data at high­speed (between 2 Mb/s and 400 Mb/s) from one unit to another. SpaceWire links are full­duplex, point­to­point, 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.
This Standard covers the following protocol levels:
•   Physical level: Defines connectors, cables, cable assemblies and printed circuit board tracks.
•   Signal level: Defines signal encoding, voltage levels, noise margins, and data signalling rates.
•   Character level: Defines the data and control characters used to manage the flow of data across a link.
•   Exchange level: Defines the protocol for link initialization, flow control, link error detection and link error recovery.
•   Packet level: Defines how data for transmission over a SpaceWire link is split up into packets.
•   Network level: Defines the structure of a SpaceWire network and the way in which packets are transferred from a source node to a destination node across a network. It also defines how link errors and network level errors are handled.
This Standard may be tailored for the specific characteristics and constraints of a space project in conformance with ECSS-S-ST-00.

This standard specifies requirements for the durability testing of coatings most commonly used for space applications, i.e.:
-   Thin film optical coatings
-   Thermo-optical and thermal control coatings (the majority are paints, metallic deposits and coatings for stray light reduction)
-   Metallic coatings for other applications (RF, electrical, corrosion protection)
This standard covers testing for both ground and in-orbit phases of a space mission, mainly for satellite applications.
This standard applies to coatings within off the shelf items
This standard specifies the types of test to be performed for each class of coating, covering the different phases of a space project (evaluation, qualification and acceptance)
This standard does not cover:
-   The particular qualification requirements for a specific mission
-   Specific applications of coatings for launchers (e.g. high temperature coatings)
-   Specific functional testing requirements for the different coating classes
-   Test requirements for long term storage
-   Solar cell cover glass coatings
-   Surface treatments and conformal coatings applied on EEE parts

This document constitutes the main deliverable from WP1.1 of the GP-START project. It is devoted to a thorough review of the metrics defined in EN 16803-1 and proposes a performance classification for GNSS-based positioning terminals within designed for road applications. It will serve as one of the inputs to the elaboration of prEN 16803-2:2019 and prEN 16803-3:2019.
This document should serve as a starting point for discussion within CEN/CENELEC/JTC 5/WG1 on a consolidated set of performance metrics and associated classification logic. The proposals and conclusions appearing in this document are therefore only preliminary.

This Standard defines the quality assurance (QA) requirements for the establishment and implementation of a Quality Assurance
programme for products of space projects. Discipline related qualification activities are complemented in standards specific to those
disciplines (e.g. ECSS-E-ST-32-01 for fracture control).
For software quality assurance, the software product assurance standard, ECSS-Q-ST-80 is applicable.
This Standard is applicable to all space projects.
This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.
For the tailoring of this standard the following information is provided:
- A table providing the pre-tailoring per "Product types" in clause 6
- A table providing the pre-tailoring per "Project phase" in Annex J

This Standard defines the requirements for the control of nonconformances.
This Standard applies to all deliverable products and supplies, at all levels, which fail to conform to project requirements.
This Standard is applicable throughout the whole project lifecycle as defined in ECSS-M-ST-10.
This standard may be tailored for the specific characteristics and constrains of a space project in conformance with ECSS-S-ST-00.

This Standard specifies the physical interconnection media and data communication protocols to enable the reliable sending of data at high­speed (between 2 Mb/s and 400 Mb/s) from one unit to another. SpaceWire links are full­duplex, point­to­point, 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.
This Standard covers the following protocol levels:
•   Physical level: Defines connectors, cables, cable assemblies and printed circuit board tracks.
•   Signal level: Defines signal encoding, voltage levels, noise margins, and data signalling rates.
•   Character level: Defines the data and control characters used to manage the flow of data across a link.
•   Exchange level: Defines the protocol for link initialization, flow control, link error detection and link error recovery.
•   Packet level: Defines how data for transmission over a SpaceWire link is split up into packets.
•   Network level: Defines the structure of a SpaceWire network and the way in which packets are transferred from a source node to a destination node across a network. It also defines how link errors and network level errors are handled.
This Standard may be tailored for the specific characteristics and constraints of a space project in conformance with ECSS-S-ST-00.

This document constitutes the main deliverable from WP1.1 of the GP-START project. It is devoted to a thorough review of the metrics defined in EN 16803-1 and proposes a performance classification for GNSS-based positioning terminals within designed for road applications. It will serve as one of the inputs to the elaboration of prEN 16803-2:2019 and prEN 16803-3:2019.
This document should serve as a starting point for discussion within CEN/CENELEC/JTC 5/WG1 on a consolidated set of performance metrics and associated classification logic. The proposals and conclusions appearing in this document are therefore only preliminary.

This document is written in the frame of WP1.3 of GP-START project. It discusses several models to provide synthetic data for PVT tracks and the ways to analyse and compare the tracks to ensure these are similar to the reality.

This document is written in the frame of WP1.3 of GP-START project. It discusses several models to provide synthetic data for PVT tracks and the ways to analyse and compare the tracks to ensure these are similar to the reality.

This standard contains planetary protection requirements, including:
-   Planetary protection management requirements;
-   Technical planetary protection requirements for robotic and human missions (forward and backward contamination);
-   Planetary protection requirements related to procedures;
-   Document Requirements Descriptions (DRD) and their relation to the respective reviews.
This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.

This standard contains planetary protection requirements, including:
-   Planetary protection management requirements;
-   Technical planetary protection requirements for robotic and human missions (forward and backward contamination);
-   Planetary protection requirements related to procedures;
-   Document Requirements Descriptions (DRD) and their relation to the respective reviews.
This standard may be tailored for the specific characteristic and constraints of a space project in conformance with ECSS-S-ST-00.

This European Standard defines Technology Readiness Levels (TRLs). It is applicable primarily to space system hardware, although the definitions could be used in a wider domain in many cases.
The definition of the TRLs provides the conditions to be met at each level, enabling accurate TRL assessment.

This European Standard defines Technology Readiness Levels (TRLs). It is applicable primarily to space system hardware, although the definitions could be used in a wider domain in many cases.
The definition of the TRLs provides the conditions to be met at each level, enabling accurate TRL assessment.

This document defines the primary space debris mitigation requirements applicable to all elements of systems launched into, or passing through, near-Earth space, including launch vehicle orbital stages, operating spacecraft and any objects released as part of normal operations or disposal actions.
The requirements contained in this document are intended to reduce the growth of space debris by ensuring that spacecraft and launch vehicle orbital stages are designed, operated and disposed of in a manner that prevents them from generating debris throughout their orbital lifetime.
This document is the top-level standard in a family of standards addressing debris mitigation. It will be the main interface for the user, bridging between the primary debris mitigation requirements and the lower-level implementation standards that will ensure compliance.
This document does not cover launch phase safety for which specific rules are defined elsewhere.
This document identifies the clauses and requirements modified with respect to ISO 24113, Space systems - Space debris mitigation requirements, Second edition 2011-05-15 for application in ECSS.

This standard addresses the qualification and procurement of printed circuit boards, which are necessary for all type of space projects.

This standard addresses the qualification and procurement of printed circuit boards, which are necessary for all type of space projects.

This document defines the primary space debris mitigation requirements applicable to all elements of systems launched into, or passing through, near-Earth space, including launch vehicle orbital stages, operating spacecraft and any objects released as part of normal operations or disposal actions.
The requirements contained in this document are intended to reduce the growth of space debris by ensuring that spacecraft and launch vehicle orbital stages are designed, operated and disposed of in a manner that prevents them from generating debris throughout their orbital lifetime.
This document is the top-level standard in a family of standards addressing debris mitigation. It will be the main interface for the user, bridging between the primary debris mitigation requirements and the lower-level implementation standards that will ensure compliance.
This document does not cover launch phase safety for which specific rules are defined elsewhere.
This document identifies the clauses and requirements modified with respect to ISO 24113, Space systems - Space debris mitigation requirements, Second edition 2011-05-15 for application in ECSS.

This Standard defines the requirements for the use of explosives on all spacecraft and other space products including launch vehicles. It addresses the aspects of design, analysis, verification, manufacturing, operations and safety.
This standard may be tailored for the specific characteristics and constraints of a space project in conformance with ECSS-S-ST-00.

This Standard defines the technical requirements and quality assurance provisions for the manufacture and verification of high-reliability electronic circuits based on surface mounted device (SMD) and mixed technology.
The Standard defines acceptance and rejection criteria for high-reliability manufacture of surface-mount and mixed-technology circuit assemblies intended to withstand normal terrestrial conditions and the vibrational g loads and environment imposed by space flight.
The proper tools, correct materials, design and workmanship are covered by this document. Workmanship standards are included to permit discrimination between proper and improper work.
The assembly of leaded devices to through-hole terminations and general soldering principles are covered in ECSS-Q-ST-70-08.
Requirements related to printed circuit boards are contained in ECSS-Q-ST-70 10, ECSS-Q-ST-70-11 and ECSS-Q-ST-70-12 . The mounting and supporting of devices, terminals and conductors prescribed herein applies to assemblies at PCB level designed to continuously operate over the mission within the temperature limits of -55 C to +85 C.
For temperatures outside this normal range, special design, verification and qualification testing is performed to ensure the necessary environmental survival capability.
Special thermal heat sinks are applied to devices having high thermal dissipation (e.g. junction temperatures of 110 C, power transistors) in order to ensure that solder joints do not exceed 85 C.
Verification of SMD assembly processes is made on test vehicles (surface mount verification samples). Temperature cycling ensures the operational lifetime for spacecraft. However, mechanical testing only indicates SMD reliability as it is unlikely that the test vehicle represents every flight configuration.
This Standard does not cover the qualification and acceptance of the EQM and FM equipment with surface-mount and mixed-technology.
The qualification and acceptance tests of equipment manufactured in accordance with this Standard are covered by ECSS-E-ST-10-03.
This standard may be tailored for the specific characteristics and constraints of a space project, in accordance with ECSS-S-ST-00.

This Standard specifies the requirements applicable to the concept definition, design, analysis, development, production, test verification and in­orbit operation of space mechanisms on spacecraft and payloads in order to meet the mission performance requirements.
This version of the standard has not been produced with the objective to cover also the requirements for mechanisms on launchers. Applicability of the requirements contained in this current version of the standard to launcher mechanisms is a decision left to the individual launcher project.
Requirements in this Standard are defined in terms of what shall be accomplished, rather than in terms of how to organise and perform the necessary work. This allows existing organizational structures and methods to be applied where they are effective, and for the structures and methods to evolve as necessary without rewriting the standards. Complementary non ECSS handbooks and guidelines exist to support mechanism design.
This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.

This Standard specifies the requirements applicable to the concept definition, design, analysis, development, production, test verification and in­orbit operation of space mechanisms on spacecraft and payloads in order to meet the mission performance requirements.
This version of the standard has not been produced with the objective to cover also the requirements for mechanisms on launchers. Applicability of the requirements contained in this current version of the standard to launcher mechanisms is a decision left to the individual launcher project.
Requirements in this Standard are defined in terms of what shall be accomplished, rather than in terms of how to organise and perform the necessary work. This allows existing organizational structures and methods to be applied where they are effective, and for the structures and methods to evolve as necessary without rewriting the standards. Complementary non-ECSS handbooks and guidelines exist to support mechanism design.
This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.

This Standard defines the requirements for the use of explosives on all spacecraft and other space products including launch vehicles. It addresses the aspects of design, analysis, verification, manufacturing, operations and safety.
This standard may be tailored for the specific characteristics and constraints of a space project in conformance with ECSS-S-ST-00.

This Standard defines the technical requirements and quality assurance provisions for the manufacture and verification of high-reliability electronic circuits based on surface mounted device (SMD) and mixed technology.
The Standard defines acceptance and rejection criteria for high-reliability manufacture of surface-mount and mixed-technology circuit assemblies intended to withstand normal terrestrial conditions and the vibrational g loads and environment imposed by space flight.
The proper tools, correct materials, design and workmanship are covered by this document. Workmanship standards are included to permit discrimination between proper and improper work.
The assembly of leaded devices to through-hole terminations and general soldering principles are covered in ECSS-Q-ST-70-08.
Requirements related to printed circuit boards are contained in ECSS-Q-ST-70 10, ECSS-Q-ST-70-11 and ECSS-Q-ST-70-12 . The mounting and supporting of devices, terminals and conductors prescribed herein applies to assemblies at PCB level designed to continuously operate over the mission within the temperature limits of -55 C to +85 C.
For temperatures outside this normal range, special design, verification and qualification testing is performed to ensure the necessary environmental survival capability.
Special thermal heat sinks are applied to devices having high thermal dissipation (e.g. junction temperatures of 110 C, power transistors) in order to ensure that solder joints do not exceed 85 C.
Verification of SMD assembly processes is made on test vehicles (surface mount verification samples). Temperature cycling ensures the operational lifetime for spacecraft. However, mechanical testing only indicates SMD reliability as it is unlikely that the test vehicle represents every flight configuration.
This Standard does not cover the qualification and acceptance of the EQM and FM equipment with surface-mount and mixed-technology.
The qualification and acceptance tests of equipment manufactured in accordance with this Standard are covered by ECSS-E-ST-10-03.
This standard may be tailored for the specific characteristics and constraints of a space project, in accordance with ECSS-S-ST-00.

This Standard specifies:
•   Requirements for the following crimping wire terminations intended for high reliability electrical connections for use on customer
spacecraft and associated equipment operating under high vacuum, thermal cycling and launch vibration:
•   removable contacts, single wires
•   removable contacts, multiple wires
•   coaxial connectors, ferrules
•   lugs and splices.
NOTE    These are the most common used crimping wire termination and are represented in Figure 1 1.
•   The general conditions to be met for the approval of terminations other than the above mentioned ones.
NOTE    Additional forms of crimps, not covered in this standard, are listed (not exhaustively) in the informative Annex A.
•   Product assurance provisions for both the specific and the generic terminations mentioned above.
•   Training and certification requirements for operators and inspectors (clause 5.5.2), additional to those specified in ECSS Q ST-20.
This standard may be tailored for the specific characteristics and constraints of a space project, in conformance with ECSS-S-ST-00.

This ECSS Standard describes the procedures to be used to clean to a level of cleanliness beyond the scope of the ECSS-Q-ST-70-01, and to control the cleanliness level of flight hardware prior to and following a posteriori to the application of the ultracleaning process. The intended objective of the ultracleaning process is to remove all surface contamination (particulates, biologic material cell debris and chemical molecular contamination) on flight hardware, with no specific limit in geometric dimension or contamination levels. This includes removal of biological material for avoidance of false positive results during investigation of extra-terrestrial samples or environments.

The purpose of this NWIP is to produce an ECSS standard for the Exchange of Thermal Model Data for Space Applications. The standard will be based on a draft standard resulting from an activity performed by ESA only in 2013/2014 called "Standard for Exchange of Thermal Model Data for Space Applications".
The content of the standard is already defined in draft form under the name "STEP-TAS" ("STEP-based draft application protocol for Thermal Analysis for Space"). This protocol has been implemented in a number of thermal analysis tools and is successfully used in both ESA and non-ESA space projects. The maturity of the protocol is therefore well-established.
The global objective of this document is to define and describe the standard protocol for Exchange of Thermal Model Data for Space Applications, previously known as STEP-TAS protocol.

This Standard specifies:
•   Requirements for the following crimping wire terminations intended for high reliability electrical connections for use on customer
spacecraft and associated equipment operating under high vacuum, thermal cycling and launch vibration:
•   removable contacts, single wires
•   removable contacts, multiple wires
•   coaxial connectors, ferrules
•   lugs and splices.
NOTE    These are the most common used crimping wire termination and are represented in Figure 1 1.
•   The general conditions to be met for the approval of terminations other than the above mentioned ones.
NOTE    Additional forms of crimps, not covered in this standard, are listed (not exhaustively) in the informative Annex A.
•   Product assurance provisions for both the specific and the generic terminations mentioned above.
•   Training and certification requirements for operators and inspectors (clause 5.5.2), additional to those specified in ECSS Q ST-20.
This standard may be tailored for the specific characteristics and constraints of a space project, in conformance with ECSS-S-ST-00.

The purpose of this NWIP is to produce an ECSS standard for the Exchange of Thermal Model Data for Space Applications. The standard will be based on a draft standard resulting from an activity performed by ESA only in 2013/2014 called "Standard for Exchange of Thermal Model Data for Space Applications".
The content of the standard is already defined in draft form under the name "STEP-TAS" ("STEP-based draft application protocol for Thermal Analysis for Space"). This protocol has been implemented in a number of thermal analysis tools and is successfully used in both ESA and non-ESA space projects. The maturity of the protocol is therefore well-established.
The global objective of this document is to define and describe the standard protocol for Exchange of Thermal Model Data for Space Applications, previously known as STEP-TAS protocol.

This ECSS Standard describes the procedures to be used to clean to a level of cleanliness beyond the scope of the ECSS-Q-ST-70-01, and to control the cleanliness level of flight hardware prior to and following a posteriori to the application of the ultracleaning process. The intended objective of the ultracleaning process is to remove all surface contamination (particulates, biologic material cell debris and chemical molecular contamination) on flight hardware, with no specific limit in geometric dimension or contamination levels. This includes removal of biological material for avoidance of false positive results during investigation of extra-terrestrial samples or environments.

This document is the top-level document of the EN 16000 Series of European Space Standards. It gives a general introduction into European Space Standards and their use in space programmes and projects.
Its purpose is to provide users with an overview of the European Space Standards System (that is based on the ECSS System), together with an introduction to the various branches of applicability and to the disciplines covered by these set of Standards and the processes involved in generating and using these standards.
As an introduction into space programmes, space projects actors and their customer-supplier relationships are described.
The branches are:
-   EN 16001 Series: Space system and Space project management
-   EN 16002 Series: Space product assurance
-   EN 16003 Series: Space engineering
-   EN 16004 Series: Space sustainability
Application of the ECSS System for space projects in the customer-supplier chain is explained and a practical tailoring method is described together with methods for collecting and processing user feedback.
Finally top-level requirements are defined for implementation of the ECSS system in space projects/programmes.
This standard is applicable to all the procurements of space products.
With effect from the date of approval, this Standard announces the adoption of the external document on a restricted basis for use in the European Cooperation for Space Standardization (ECSS) system.
This standard may be tailored for the specific characteristic and constraints of a space project in conformance with clause 7 of this standard.