SIST 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 EN 16603-32-10 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.
Raumfahrttechnik - Strukturelle Sicherheitsfaktoren für Raumflughardware
Ingénierie spatiale - Facteurs de sécurité pour les structure 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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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 . 23
Figures Figure 4-1: Logic for Factors of Safety application . 14 Figure 4-2: Analysis tree . 15
SIST EN 16603-32-10:2014
EN 16603-32-10:2014 (E) 3 Tables Table 4-1: Relationship among (structural) factors of safety, design factors and additional factors . 14 Table 4-2: Test factor values . 16 Table 4-3: Factors of safety for metallic, FRP, sandwich, glass and ceramic structural parts . 18 Table 4-4: Factors of safety for joints, inserts and connections . 19 Table 4-5: Factors of safety for buckling . 20 Table 4-6: Factors of safety for pressurized hardware . 20
SIST EN 16603-32-10:2014
EN 16603-32-10:2014 (E) 4 Foreword This document (EN 16603-32-10:2014) has been prepared by Technical Committee CEN/CLC/TC 5 “Space”, the secretariat of which is held by DIN. This standard (EN 16603-32-10:2014) originates from ECSS-E-ST-32-10C Rev.1. This European Standard shall be given the status of a national standard, either by publication of an identical text or by endorsement, at the latest by February 2015, and conflicting national standards shall be withdrawn at the latest by February 2015. Attention is drawn to the possibility that some of the elements of this document may be the subject of patent rights. CEN [and/or CENELEC] shall not be held responsible for identifying any or all such patent rights. This document has been developed to cover specifically space systems and has therefore precedence over any EN covering the same scope but with a wider domain of applicability (e.g. : aerospace). According to the CEN-CENELEC Internal Regulations, the national standards organizations of the following countries are bound to implement this European Standard: 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 the United Kingdom. SIST EN 16603-32-10:2014
EN 16603-32-10:2014 (E) 5 1 Scope 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 SIST EN 16603-32-10:2014
EN 16603-32-10:2014 (E) 6 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. SIST EN 16603-32-10:2014
EN 16603-32-10:2014 (E) 7 2 Normative references The following normative documents contain provisions which, through reference in this text, constitute provisions of this ECSS Standard. For dated references, subsequent amendments to, or revision of any of these publications, do not apply. However, parties to agreements based on this ECSS Standard are encouraged to investigate the possibility of applying the more recent editions of the normative documents indicated below. For undated references, the latest edition of the publication referred to applies.
EN reference Reference in text Title EN 16601-00-01 ECSS-S-ST-00-01 ECSS system – Glossary of terms EN 16603-10-02 ECSS-E-ST-10-02 Space engineering – Verification EN 16603-10-03 ECSS-E-ST-10-03 Space engineering – Testing EN 16603-32 ECSS-E-ST-32 Space engineering –
Structural general requirements EN 16603-32-02 ECSS-E-ST-32-02 Space engineering – Structural design and verification of pressurized hardware SIST EN 16603-32-10:2014
EN 16603-32-10:2014 (E) 8 3 Terms, definitions and abbreviated terms 3.1 Terms and definitions For the purpose of this Standard, the terms and definitions from ECSS-S-ST-00-01, ECSS-E-ST-10-02, ECSS-ST-E-10-03, and ECSS-E-ST-32 apply. 3.2 Terms specific to the present standard 3.2.1
local design factor (KLD) factor used to take into account local discontinuities and applied in series with FOSU or FOSY 3.2.2
margin policy factor (KMP) factor, specific to launch vehicles, which includes the margin policy defined by the project 3.2.3
model factor (KM) factor which takes into account the representativity of mathematical models
3.2.4
project factor (KP) factor which takes into account at the beginning of the project the maturity of the design and its possible evolution and programmatic margins which cover project uncertainties or some growth potential when required 3.2.5
prototype test test performed on a separate flight-like structural test article 3.2.6
protoflight test test performed on a flight hardware 3.2.7
test factors (KA and KQ) factors used to define respectively the acceptance and the qualification test loads 3.2.8
ultimate design factor of safety (FOSU) multiplying factor applied to the design limit load in order to calculate the design ultimate load SIST EN 16603-32-10:2014
EN 16603-32-10:2014 (E) 9 3.2.9
yield design factor of safety (FOSY) multiplying factor applied to the design limit load in order to calculate the design yield load 3.3 Abbreviated terms For the purpose of this standard, the abbreviated terms from ECSS-S-ST-00-01 and the following apply.
Abbreviation Meaning AL acceptance test load DLL design limit load DUL design ultimate load DYL design yield load FOS factor of safety FOSU ultimate design factor of safety FOSY yield design factor of safety FRP fibre reinforced plastics GSE ground support equipment KA acceptance test factor KQ qualification test factor LCDA launch vehicle coupled dynamic analysis LL limit load N/A not applicable QL qualification test load S/C spacecraft SIST EN 16603-32-10:2014
EN 16603-32-10:2014 (E) 10 4 Requirements 4.1 Applicability of structural factors of safety
4.1.1 Overview The purpose of the factors of safety defined in this Standard is to guarantee an adequate level of mechanical reliability for spaceflight hardware. 4.1.2 Applicability a. The factors specified in clauses 4.1.4, 4.1.5 and 4.3 shall be applied for: 1. Structural elements of satellites including payloads, equipment and experiments. NOTE
These factors are not applied for the GSE sizing and qualification. 2. The expendable launch vehicles structural elements. 3. Man-rated spacecraft structures including payloads, equipments and experiments. b. The factors in clauses 4.1.4, 4.1.5 and 4.3 shall be applied for both the design and test phases as defined in Figure 4-1. 4.1.3 General a. Design factor and additional factors values shall be agreed with the customer. 4.1.4 Design factor for loads 4.1.4.1 General a. For determination of the Design Limit Load (DLL) the Design Factor shall be used, this is defined as the product of the factors defined hereafter. NOTE
Robustness of the sizing process is considered through the Design Limit Loads (DLL). SIST EN 16603-32-10:2014
EN 16603-32-10:2014 (E) 11 4.1.4.2 Model factor a. A “model Factor" KM shall be applied to account for uncertainties in mathematical models when predicting dynamic response, loads and evaluating load paths. NOTE 1 The model factor is applied at every level of the analysis tree system (Figure 4-2) where predictive models are used. It encompasses the lack of confidence in the information provided by the model, e.g. hyperstaticity (uncertainty in the load path because of non accuracy of the mathematical model), junction stiffness uncertainty, non-correlated dynamic behaviour.
NOTE 2 While going through the design refinement loops, KM can be progressively reduced to 1,0 after demonstration of satisfactory correlatio
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