1、BSI Standards PublicationBS EN 16603-32-01:2014Space engineering FracturecontrolBS EN 16603-32-01:2014 BRITISH STANDARDNational forewordThis British Standard is the UK implementation of EN16603-32-01:2014. It supersedes BS EN 14165:2004 which iswithdrawn.The UK participation in its preparation was e
2、ntrusted to TechnicalCommittee 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 correctapplicatio
3、n. The British Standards Institution 2014. Published by BSI StandardsLimited 2014ISBN 978 0 580 83980 1ICS 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
4、 August 2014.Amendments issued since publicationDate Text affectedBS EN 16603-32-01:2014EUROPEAN STANDARD NORME EUROPENNE EUROPISCHE NORM EN 16603-32-01 August 2014 ICS 49.140 Supersedes EN 14165:2004 English version Space engineering - Fracture control Ingnierie spatiale - Matrise de la rupture Rau
5、mfahrttechnik - berwachung des Rissfortschritts 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 wit
6、hout 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
7、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
8、 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, Slo
9、venia, 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 16603-32-01:2014 E
10、BS EN 16603-32-01:2014EN 16603-32-01:2014 (E) 2 Table of contents Foreword 6 1 Scope . 7 2 Normative references . 8 3 Terms, definitions and abbreviated terms 10 3.1 Terms from other standards 10 3.2 Terms specific to the present standard . 11 3.3 Abbreviated terms. 17 4 Principles 19 5 Fracture con
11、trol programme . 21 5.1 General . 21 5.2 Fracture control plan . 21 5.3 Reviews 22 5.3.1 General . 22 5.3.2 Safety and project reviews 23 6 Identification and evaluation of PFCI 25 6.1 Identification of PFCIs . 25 6.2 Evaluation of PFCIs 26 6.2.1 Damage tolerance . 26 6.2.2 Fracture critical item cl
12、assification . 28 6.3 Compliance procedures 28 6.3.1 General . 28 6.3.2 Safe life items . 28 6.3.3 Fail-safe items . 29 6.3.4 Contained items 30 6.3.5 Low-risk fracture items 31 6.4 Documentation requirements 36 6.4.1 Fracture control plan . 36 6.4.2 Lists 36 6.4.3 Analysis and test documents . 36 B
13、S EN 16603-32-01:2014EN 16603-32-01:2014 (E) 3 6.4.4 Fracture control summary report . 36 7 Fracture mechanics analysis . 38 7.1 General . 38 7.2 Analytical life prediction 39 7.2.1 Identification of all load events 39 7.2.2 Identification of the most critical location and orientation of the crack 3
14、9 7.2.3 Derivation of stresses for the critical location. 40 7.2.4 Derivation of the stress spectrum 40 7.2.5 Derivation of material data 41 7.2.6 Identification of the initial crack size and shape . 41 7.2.7 Identification of an applicable stress intensity factor solution . 42 7.2.8 Performance of
15、crack growth calculations . 43 7.3 Critical crack-size calculation 43 8 Special requirements . 45 8.1 Introduction . 45 8.2 Pressurized hardware . 45 8.2.1 General . 45 8.2.2 Pressure vessels . 45 8.2.3 Pressurized structures 48 8.2.4 Pressure components . 48 8.2.5 Low risk sealed containers 49 8.2.
16、6 Hazardous fluid containers 49 8.3 Welds . 50 8.3.1 Nomenclature 50 8.3.2 Safe life analysis of welds . 50 8.4 Composite, bonded and sandwich structures 51 8.4.1 General . 51 8.4.2 Defect assessment 51 8.4.3 Damage threat assessment 53 8.4.4 Compliance procedures 54 8.5 Non-metallic items other tha
17、n composite, bonded, sandwich and glass items 57 8.6 Rotating machinery . 58 8.7 Glass components 58 8.8 Fasteners . 59 9 Material selection . 61 10 Quality assurance and Inspection 62 BS EN 16603-32-01:2014EN 16603-32-01:2014 (E) 4 10.1 Overview 62 10.2 Nonconformances. 62 10.3 Inspection of PFCI 6
18、2 10.3.1 General . 62 10.3.2 Inspection of raw material . 63 10.3.3 Inspection of safe life finished items 64 10.4 Non-destructive inspection of metallic materials . 65 10.4.1 General . 65 10.4.2 NDI categories versus initial crack size . 65 10.4.3 Inspection procedure requirements for standard NDI
19、69 10.5 NDI for composites, bonded and sandwich parts 72 10.5.1 General . 72 10.5.2 Inspection requirements 73 10.6 Traceability . 74 10.6.1 General . 74 10.6.2 Requirements 75 10.7 Detected defects . 75 10.7.1 General . 75 10.7.2 Acceptability verification 76 10.7.3 Improved probability of detectio
20、n . 77 11 Reduced fracture control programme 78 11.1 Applicability. 78 11.2 Requirements . 78 11.2.1 General . 78 11.2.2 Modifications . 78 Annex A (informative) The ESACRACK software package 80 Annex B (informative) References . 81 Bibliography . 82 Figures Figure 5-1: Identification of PFCI 22 Fig
21、ure 6-1: Fracture control evaluation procedures 27 Figure 6-2: Safe life item evaluation procedure for metallic materials . 33 Figure 6-3: Safe life item evaluation procedure for composite, bonded and sandwich items 34 Figure 6-4: Evaluation procedure for fail-safe items 35 BS EN 16603-32-01:2014EN
22、16603-32-01:2014 (E) 5 Figure 8-1: Procedure for metallic pressure vessel and metallic liner evaluation 47 Figure 10-1: Initial crack geometries for parts without holes . 71 Figure 10-2: Initial crack geometries for parts with holes 72 Figure 10-3: Initial crack geometries for cylindrical parts 72 T
23、ables Table 8-1: Factor on stress for sustained crack growth analysis of glass items 59 Table 10-1: Initial crack size summary, standard NDI . 68 BS EN 16603-32-01:2014EN 16603-32-01:2014 (E) 6 Foreword This document (EN 16603-32-01:2014) has been prepared by Technical Committee CEN/CLC/TC 5 “Space”
24、, the secretariat of which is held by DIN. This standard (EN 16603-32-01:2014) originates from ECSS-E-ST-32-01C 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 conflicti
25、ng 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
26、 supersedes EN 14165:2004. 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 orga
27、nizations 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,
28、 Malta, Netherlands, Norway, Poland, Portugal, Romania, Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey and the United Kingdom. BS EN 16603-32-01:2014EN 16603-32-01:2014 (E) 7 1 Scope This ECSS Engineering Standard specifies the fracture control requirements to be imposed on space segments of
29、 space systems and their related GSE. The fracture control programme is applicable for space systems and related GSE when required by ECSS-Q-ST-40 or by the NASA document NST 1700.7, incl. ISS addendum. The requirements contained in this Standard, when implemented, also satisfy the fracture control
30、requirements applicable to the NASA STS and ISS as specified in the NASA document NSTS 1700.7 (incl. the ISS Addendum). The NASA nomenclature differs in some cases from that used by ECSS. When STS/ISS-specific requirements and nomenclature are included, they are identified as such. This standard may
31、 be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00. BS EN 16603-32-01:2014EN 16603-32-01:2014 (E) 8 2 Normative references The following normative documents contain provisions which, through reference in this text, constitute provisions of
32、 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 indicat
33、ed 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 16603-32 ECSS-E-ST-32 Space engineering Structural EN 16603-32-02 ECSS-E-ST-32-02 Space engineering Struct
34、ural design and verification of pressurized hardware EN 16602-20 ECSS-Q-ST-20 Space product assurance Quality assurance EN 16602-40 ECSS-Q-ST-40 Space product assurance Safety EN 16602-70 ECSS-Q-ST-70 Space product assurance Materials, mechanical parts and processes EN 16602-70-36 ECSS-Q-ST-70-36 Sp
35、ace product assurance Material selection for controlling stress-corrosion cracking EN 16602-70-45 ECSS-Q-ST-70-45 Space product assurance Mechanical testing of metallic materials ASTM E 164 Standard Practice for Ultrasonic Contact Examination of Weldments ASTM E 426 Standard Practice for Electromagn
36、etic (Eddy-Current) Examination of Seamless and Welded Tubular Products, Austenitic Stainless Steel and Similar Alloys ASTM E 1417 Standard Practice for Liquid Penetrant Examination ASTM E 1444 Standard Practice for Magnetic Particle Examination ASTM E 1742 Standard Practice for Radiographic Examina
37、tion DOT/FAA/AR-MMPDS Metallic Materials Properties Development and Standardization (MMPDS) (former MIL-HDBK-5) EN 4179 Aerospace Qualification and Authorization of Personnel for Non-destructive Testing BS EN 16603-32-01:2014EN 16603-32-01:2014 (E) 9 EN reference Reference in text Title EN ISO 6520-
38、1 Welding and allied processes Classification of geometric imperfections in metallic materials Part 1: Fusion welding ISO 17659 Welding Multilingual terms for welded joints with illustrations MIL-HDBK-6870 Inspection program requirements, nondestructive, for aircraft and missile materials and parts
39、NAS-410 Nondestructive testing personnel qualification and certification NSTS 1700.7 Safety Policy and Requirements For Payloads Using the Space Transportation System (STS) NSTS 1700.7 ISS Addendum Safety Policy and Requirements For Payloads Using the International Space Station SAE AMS-STD-2154 Pro
40、cess for inspection, ultrasonic, wrought metals SAE AMS 2644 Inspection Material, Penetrant NSTS/ISS 13830 Payload Safety Review and Data Submittal Requirements For Payloads Using the Space Shuttle the initial size and geometry of the crack; the presence of an aggressive environment; the geometry of
41、 the item; the magnitude and number of loading cycles; the duration of sustained load; the temperature of the material. For metallic materials, the engineering discipline of linear elastic fracture mechanics (LEFM) provides analytical tools for the prediction of crack propagation and critical crack
42、size. Validity of LEFM, depends on stress level, crack configuration and structural geometry. The engineering discipline of elastic-plastic fracture mechanics (EPFM) provides analytical tools for the prediction of crack initiation, stable ductile crack growth and critical crack size. For non-metalli
43、c materials (other than glass and other brittle materials) and fibre-reinforced composites (both with metal and with polymer matrix), linear elastic fracture mechanics technology is agreed by most BS EN 16603-32-01:2014EN 16603-32-01:2014 (E) 20 authorities to be inadequate, with the exception of in
44、terlaminar fracture mechanics applied to debonding and delamination. Fracture control of these materials relies on the techniques of safe life assessment supported by tests, containment, fail safe assessment, and proof testing. Composite, bonded and sandwich items are manufactured and verified to hi
45、gh quality control standards to assure aerospace quality hardware. The hardware developer of composite, bonded and sandwich items uses only manufacturing processes and controls (NDI, coupon tests, sampling techniques, etc.) that are demonstrated to be reliable and consistent with established aerospa
46、ce industry practices for composite/bonded structures. The observed scatter in measured material properties and fracture mechanics analysis uncertainties is considered. NOTE For example, scatter factor and LEF For NSTS and ISS payloads, entities controlling the pressure are two-fault tolerant, see N
47、STS 1700.7 (incl. ISS Addendum). NOTE For example, regulators, relief devices and thermal control systems BS EN 16603-32-01:2014EN 16603-32-01:2014 (E) 21 5 Fracture control programme 5.1 General a. A fracture control programme shall be implemented by the supplier for space systems and their related
48、 GSE in conformance with this Standard, when required by ECSS-Q-ST-40 or the NASA document NSTS 1700.7, incl. ISS Addendum (clause 208.1). b. Fracture control requirements as defined in this standard shall be applied where structural failure can result in a catastrophic or critical hazard. NOTE In N
49、ASA NSTS 1700.7 (Safety Policy and Requirements For Payloads Using the Space Transportation System STS), incl. ISS Addendum, the payload structural design is based on fracture control procedures when the failure of a structural item can result in a catastrophic event. c. Implementation of fracture control for structural GSE may be limited to items which are not covered by other structural safety requirements. NOTE In many cases this limits fracture control verification to elements directly interfacing with flight hardware. d. Items for
