Luft- og romfartsteknikk

ISO 17666:2016 defines, extending the requirements of ISO 14300‑1, the principles and requirements for integrated risk management on a space project. It explains what is needed to implement a project-integrated risk management policy by any project actor, at any level (i.e. customer, first-level supplier, or lower-level suppliers).

It contains a summary of the general risk management process, which is subdivided into four (4) basic steps and nine (9) tasks. The implementation can be tailored to project-specific conditions.

The risk management process requires information exchange among all project domains and provides visibility over risks, with a ranking according to their criticality for the project; these risks are monitored and controlled according to the rules defined for the domains to which they belong.

The fields of application of ISO 17666:2016 are all the space project phases. A definition of project phasing is given in ISO 14300‑1.

When viewed from the perspective of a specific programme or project context, the requirements defined in ISO 17666:2016 are tailored to match the genuine requirements of a particular profile and circumstances of a programme or project.

ISO 27025:2010 defines the quality assurance (QA) requirements for the establishment and implementation of QA programmes for projects covering mission definition, design, development, production and operations of space systems, including disposal.

It is applicable to the customer-supplier relationship for space products to the extent agreed by both parties. The requirements of this International Standard and its associated referenced standards are tailored to the needs and classes of specific projects.

When viewed from the perspective of a specific project context, the requirements defined in ISO 27025:2010 are tailored to match the genuine requirements of a particular profile and circumstances of a project.

ISO 27026:2011 specifies processes, requirements and recommendations for the breakdown of project management structures, collectively called project breakdown structures, in terms of the various specification (i.e. requirements), functional, product, work, cost, business and organizational breakdown structures that are established and implemented to contribute to the success of a space programme, which is often composed of one or more projects.

It is intended to complement and supplement similar project breakdown structure processes, requirements and recommendations contained within ISO 14300-1, which serves as a higher tier International Standard for ISO 27026:2011 and for such other space systems and operations International Standards that require formal project breakdown structures.

ISO 27026:2011 specifies the various types of project breakdown structures and gives processes, requirements and guidance concerning the composition of these breakdown structures.

ISO 27026:2011 is applicable to project breakdown structures for a project, including at the top level of a programme, i.e. level 0. It is intended to be used either by an independent developer as a partial basis for programme processes or as a basis for an agreement between a supplier and a customer.

This document specifies the required characteristics, tests and tooling applicable to male electrical contacts 008, type A, crimp, class S, used in elements of connection according to EN 3155-002. It is used together with EN 3155-001. The associated female contacts are defined in EN 3155-003 and EN 3155-009.

ISO 12261:2016 specifies the dimensions of pan head screws with internal offset cruciform ribbed or unribbed drive, pitch diameter shank and long length MJ threads, in metallic material, coated or uncoated, with strength classes less than or equal to 1 100 MPa.

ISO 12261:2016 is applicable to the compilation of aerospace product standards.

This activity w ill be the parallel development of EN 16603-20-40 and ECSS-E-ST-20-40C. The scope shall cover the areas of existing ASIC and FPGA engineering chapter 5 of ECSS-Q-ST-60-02C, but w ith w ider breadth and greater depth, covering engineering requirements of end-to-end development flow s, from specification of requirements to validation of prototypes, of the follow ing monolithic devices for its use in space: • ASICs (distinguishing digital, analogue and mixed-signal development flow s) • FPGAs (distinguishing three technology families: SRAM, FLASH and anti-fuse technologies) • ASIC and FPGA System-on-Chip embedding processor cores w hich have external “softw are programme” dependencies to be addressed during the SoC development, resulting in SW-HW co-design requirements.

This International Standard specifies test methods for metric self-locking nuts with MJ threads intended for use in

aerospace construction at maximum operating temperatures less than or equal to 425 °C. It describes the test

device and the method for each test.

It applies to self-locking nuts as defined above, provided that the relevant documents (dimensional standard,

drawing, procurement specification, etc.) refer to this International Standard.

This International Standard shall be used in conjunction with ISO 5858.

NOTE This International Standard only specifies tests for ambient and elevated temperature applications. Tests for

applications at less than ambient temperatures, for example cryogenic, shall be as agreed upon between seller and purchaser.

This International Standard defines the general criteria for the development of flight-to-ground umbilical systems

used by a space system. The criteria specified herein is limited to the service arms or equivalent mechanisms,

umbilical carriers and plates, couplings, connectors, withdrawal and retract devices, handling mechanisms and

control systems for mechanisms.

This document mainly specifies minimum requirements for elements of information exchange between UTM service providers(USP) and different users to support relevant UTM services between them, while the protocol requirements and transmission requirements of UTM actors at the operational level are not included.

This document specifies the characteristics of self-locking, shank nuts, in NI-PH2601, silver plated, for aerospace applications. Classification: 1 550 MPa 1 / 600 °C 2 . 1 Correspond to the minimum tensile stress which the nut is able to withstand at ambient temperature without breaking or cracking when tested with a bolt of a higher strength class. 2 Maximum test temperature of the parts.