BS EN 16603-32-10:2020 - Space engineering. Structural factors of safety for spaceflight hardware

BS EN 16603-32-10:2020

Space engineering. Structural factors of safety for spaceflight hardware

Status : Current   Published : June 2020



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.

Standard NumberBS EN 16603-32-10:2020
TitleSpace engineering. Structural factors of safety for spaceflight hardware
Publication Date25 June 2020
Normative References(Required to achieve compliance to this standard)EN 16603-10-02, EN 16603-32, EN 16603-32-02, EN 16601-00-01, EN 16603-10-03
Informative References(Provided for Information)EN 16601-00
ReplacesBS EN 16603-32-10:2014
International RelationshipsEN 16603-32-10:2020
Draft Superseded By19/30400435 DC
DescriptorsSystemology, Dimensional space requirements, Approval testing, Qualification approval, Space technology, Astronomy, Factor of safety, Computer hardware, Design, Safety measures, Verification, Safety, Space sciences
Title in FrenchIngénierie spatiale. Coefficients de sécurité de la structure pour les matériels spatiaux
Title in GermanRaumfahrttechnik. Strukturelle Sicherheitsfaktoren für Raumflughardware
ISBN978 0 539 05911 3
File Size915 KB

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