1、BSI Standards PublicationBS EN 16603-32-10:2014Space engineering Structuralfactors of safety for spaceflighthardwareBS EN 16603-32-10:2014 BRITISH STANDARDNational forewordThis British Standard is the UK implementation of EN16603-32-10:2014.The UK participation in its preparation was entrusted to Te
2、chnicalCommittee ACE/68, Space systems and operations.A list of organizations represented on this committee can beobtained on request to its secretary.This publication does not purport to include all the necessaryprovisions of a contract. Users are responsible for its correctapplication. The British
3、 Standards Institution 2014. Published by BSI StandardsLimited 2014ISBN 978 0 580 83982 5ICS 49.140Compliance with a British Standard cannot confer immunity fromlegal obligations.This British Standard was published under the authority of theStandards Policy and Strategy Committee on 31 August 2014.A
4、mendments issued since publicationDate Text affectedBS EN 16603-32-10:2014EUROPEAN STANDARD NORME EUROPENNE EUROPISCHE NORM EN 16603-32-10 August 2014 ICS 49.140 English version Space engineering - Structural factors of safety for spaceflight hardware Ingnierie spatiale - Facteurs de scurit pour les
5、 structure spatiales Raumfahrttechnik - Strukturelle Sicherheitsfaktoren fr 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 S
6、tandard 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 v
7、ersions (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 s
8、tandards 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, Nor
9、way, 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 CEN
10、ELEC Members. Ref. No. EN 16603-32-10:2014 EBS EN 16603-32-10:2014EN 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 te
11、rms. 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
12、 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 BS EN 16603-32
13、-10:2014EN 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 saf
14、ety 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 BS EN 16603-32-10:2014EN 16603-32-10:2014 (E) 4 Foreword This document (EN 16603-32-10:2014) has been prepared by Technical Committee CEN/CLC/TC 5 “Spa
15、ce”, 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 conflic
16、ting 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 docume
17、nt 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 a
18、re 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, P
19、ortugal, Romania, Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey and the United Kingdom. BS EN 16603-32-10:2014EN 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 des
20、ign 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
21、 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 indu
22、stry 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, dimens
23、ioning 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, planetar
24、y 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
25、 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 BS EN 16603-32-10:2014EN 16603-32-10:2014 (E) 6 of safety for pressurised hardware can be foun
26、d 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
27、 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 co
28、uld 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
29、-S-ST-00. BS EN 16603-32-10:2014EN 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 public
30、ations, 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 refere
31、nce 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 EC
32、SS-E-ST-32-02 Space engineering Structural design and verification of pressurized hardware BS EN 16603-32-10:2014EN 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-
33、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 includ
34、es 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 programm
35、atic 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 th
36、e 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 BS EN 16603-32-10:2014EN 16603-32-10:2014 (E) 9 3.2.9 yield design factor of safety (FOSY) multiplying factor
37、 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 de
38、sign 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 applicabl
39、e QL qualification test load S/C spacecraft BS EN 16603-32-10:2014EN 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 s
40、paceflight 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 launc
41、h 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 value
42、s 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 Des
43、ign Limit Loads (DLL). BS EN 16603-32-10:2014EN 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 leve
44、l 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-corre
45、lated dynamic behaviour. NOTE 2 While going through the design refinement loops, KM can be progressively reduced to 1,0 after demonstration of satisfactory correlation between mathematical models and test measurements. NOTE 3 For launch vehicles, at system level, KM is also called “system margin”. b
46、. KM value shall be justified. NOTE Justification can be performed based on relevant historical practice (e.g. typical values of 1,2 are used for satellites at the beginning of new development and 1,0 for internal pressure loads for pressurized hardware), analytical or experimental means. 4.1.4.3 Pr
47、oject factor a. A specific “project factor” KP shall be applied to account for the maturity of the program (e.g. stability of the mass budget, well identified design) and the confidence in the specification given to the project (this factor integrates a programmatic margin e.g. for growth potential
48、for further developments). NOTE The value of this factor is generally defined at system level and can be reduced during the development. b. KP value shall be justified. NOTE Justification can be performed based on relevant historical practice or on foreseen evolutions. 4.1.4.4 Qualification test fac
49、tor a. The qualification factor KQ shall be applied for satellites. NOTE For satellites, the qualification loads are part of the specified loads and are accounted for in the dimensioning process. This is different for BS EN 16603-32-10:2014EN 16603-32-10:2014 (E) 12 launch vehicles for which QL are consequences of the dimensioning process. 4.1.5 Additional factors for design 4.1.5.1 Overview All the analysis complexity or inaccuracies and uncertainties not mentioned in clause 4.1.4 are taken into account with the following additional factors. 4.1.5.2 Local de
