EN 16603-32-10:2014
(Main)Space engineering - Structural factors of safety for spaceflight hardware
Space engineering - Structural factors of safety for spaceflight hardware
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.
Raumfahrttechnik - Strukturelle Sicherheitsfaktoren für Raumflughardware
Ingénierie spatiale - Facteurs de sécurité pour les structures spatiales
Vesoljska tehnika - Strukturni varnostni faktorji za strojne dele vesoljskih plovil
Namen standarda EN 16603-32-10 je določiti varnostne dejavnike (FOS), oblikovalne dejavnike in dodatne dejavnike, ki se uporabljajo za dimenzioniranje in verifikacijo načrtovanja strojnih delov vesoljskih plovil, vključno s preskusi preverjanja ustreznosti in sprejemljivosti. Ta standard ni samostojen in se uporablja v povezavi z dokumenti ECSS-E-ST-32, ECSS-E-ST-32-02 in ECSS-E-ST-33-01. Dokument vsebuje naslednje predpostavke: • za določanje mejnih obremenitev, vključno s sipanjem, so uporabljene priznane metodologije, ki se uporabljajo za strojno opremo in stresne analize; • strukturna in mehanska zasnova sistema je primerna za tehnične analize z najsodobnejšimi metodami in skladna s standardnimi praksami letalske in vesoljske industrije. Varnostni dejavniki so določeni tako, da zajamejo izbrano verjetnost ravni obremenitve in predpostavljeno negotovost mehanskih lastnosti ter proizvodnje, ne zajamejo pa pomanjkanja inženirskega truda. Izbira varnostnega dejavnika za program je neposredno povezana z utemeljitvijo načrtovanja, dimenzioniranja in preskušanja v okviru programa. Ker se razvojna logika in s tem povezani cilji glede zanesljivosti razlikujejo za: • znanstvene ali komercialne satelite brez posadke, • nadomestljive rakete, • vesoljska plovila, primerna za prevoz ljudi in • katero koli drugo vesoljsko plovilo brez posadke (npr. transportno vozilo, vesoljsko sondo), so za vsako posebej navedene posebne vrednosti.
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Standards Content (Sample)
2003-01.Slovenski inštitut za standardizacijo. Razmnoževanje celote ali delov tega standarda ni dovoljeno.Vesoljska tehnika - Strukturni varnostni faktorji za strojne dele vesoljskih plovilRaumfahrttechnik - Strukturelle Sicherheitsfaktoren für RaumflughardwareIngénierie spatiale - Facteurs de sécurité pour les structure spatialesSpace engineering - Structural factors of safety for spaceflight hardware49.140Vesoljski sistemi in operacijeSpace systems and operationsICS:Ta slovenski standard je istoveten z:EN 16603-32-10:2014SIST EN 16603-32-10:2014en,fr,de01-november-2014SIST EN 16603-32-10:2014SLOVENSKI
STANDARD
SIST EN 16603-32-10:2014
EUROPEAN STANDARD NORME EUROPÉENNE EUROPÄISCHE NORM
EN 16603-32-10
August 2014 ICS 49.140
English version
Space engineering - Structural factors of safety for spaceflight hardware
Ingénierie spatiale - Facteurs de sécurité pour les structure spatiales
Raumfahrttechnik - Strukturelle Sicherheitsfaktoren für Raumflughardware This European Standard was approved by CEN on 10 February 2014.
CEN and CENELEC members are bound to comply with the CEN/CENELEC Internal Regulations which stipulate the conditions for giving this European Standard the status of a national standard without any alteration. Up-to-date lists and bibliographical references concerning such national standards may be obtained on application to the CEN-CENELEC Management Centre or to any CEN and CENELEC member.
This European Standard exists in three official versions (English, French, German). A version in any other language made by translation under the responsibility of a CEN and CENELEC member into its own language and notified to the CEN-CENELEC Management Centre has the same status as the official versions.
CEN and CENELEC members are the national standards bodies and national electrotechnical committees of Austria, Belgium, Bulgaria, Croatia, Cyprus, Czech Republic, Denmark, Estonia, Finland, Former Yugoslav Republic of Macedonia, France, Germany, Greece, Hungary, Iceland, Ireland, Italy, Latvia, Lithuania, Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Romania, Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey and United Kingdom.
CEN-CENELEC Management Centre: Avenue Marnix 17, B-1000 Brussels © 2014 CEN/CENELEC All rights of exploitation in any form and by any means reserved worldwide for CEN national Members and for CENELEC Members. Ref. No. EN 16603-32-10:2014 E SIST EN 16603-32-10:2014
EN 16603-32-10:2014 (E) 2 Table of contents
Foreword . 4 1 Scope . 5 2 Normative references . 7 3 Terms, definitions and abbreviated terms . 8 3.1 Terms and definitions . 8 3.2 Terms specific to the present standard . 8 3.3 Abbreviated terms. 9 4 Requirements . 10 4.1 Applicability of structural factors of safety . 10 4.1.1 Overview . 10 4.1.2 Applicability . 10 4.1.3 General . 10 4.1.4 Design factor for loads . 10 4.1.5 Additional factors for design . 12 4.2 Loads and factors relationship . 13 4.2.1 General . 13 4.2.2 Specific requirements for launch vehicles . 15 4.3 Factors values . 16 4.3.1 Test factors . 16 4.3.2 Factors of safety . 17 Annex A (informative) Qualification test factor for launch vehicles . 21 Bibliography .
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