SIST EN 16603-32-08:2016
(Main)Space engineering - Materials
Space engineering - Materials
ECSS-E-ST-32-08 defines the mechanical engineering requirements for materials. This Standard also encompasses the mechanical effects of the natural and induced environments to which materials used for space applications can be subjected.
This Standard defines requirements for the establishment of the mechanical and physical properties of the materials to be used for space applications, and the verification of these requirements.
Verification includes destructive and non-destructive test methods. Quality assurance requirements for materials (e.g. procurement and control) are covered by ECSS-Q-ST-70.
This standard may be tailored for the specific characteristics and constrains of a space project in conformance with ECSS-S-ST-00.
Raumfahrttechnik - Werkstoffe
Ingénierie spatiale - Matériaux
Vesoljska tehnika - Materiali
ECSS-E-ST-32-08 določa strojniške zahteve za materiale. Ta standard zajema tudi mehanske učinke naravnih in umetno ustvarjenih okolij, ki so jim lahko izpostavljeni materiali, uporabljeni za vesoljske namene. Ta standard določa zahteve za vzpostavitev mehanskih in fizikalnih lastnosti materialov za uporabo za vesoljske namene in preverjanje teh zahtev. Preverjanje vključuje porušitvene in neporušitvene preskusne metode. Zahteve za zagotavljanje kakovosti materialov (npr. naročanje in nadzor) so zajete v standardu ECSS-Q-ST-70. Ta standard se lahko prilagodi posameznim lastnostim in omejitvam vesoljskega projekta v skladu s standardom ECSS-S-ST-00.
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2003-01.Slovenski inštitut za standardizacijo. Razmnoževanje celote ali delov tega standarda ni dovoljeno.Vesoljska tehnika - MaterialiRaumfahrttechnik - WerkstoffeIngénierie spatiale - MatériauxSpace engineering - Materials49.140Vesoljski sistemi in operacijeSpace systems and operationsICS:Ta slovenski standard je istoveten z:EN 16603-32-08:2016SIST EN 16603-32-08:2016en,fr,de01-november-2016SIST EN 16603-32-08:2016SLOVENSKI
STANDARDSIST EN 14607-8:20051DGRPHãþD
SIST EN 16603-32-08:2016
EUROPEAN STANDARD NORME EUROPÉENNE EUROPÄISCHE NORM
EN 16603-32-08
August 2016 ICS 49.140 Supersedes EN 14607-8:2004
English version
Space engineering - Materials
Ingénierie spatiale - Matériaux
Raumfahrttechnik - Werkstoffe This European Standard was approved by CEN on 22 May 2016.
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 © 2016 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 16603-32-08:2016 E SIST EN 16603-32-08:2016
EN 16603-32-08:2016 (E) 2 Table of contents European Foreword . 4 1 Scope . 5 2 Normative references . 6 3 Terms, definitions and abbreviated terms . 7 3.1 Terms and definitions from other standards . 7 3.2 Terms specific to the present standard . 7 3.3 Abbreviated terms. 8 3.4 Nomenclature . 8 4 Requirements . 10 4.1 General . 10 4.2 Functionality . 10 4.2.1 Strength . 10 4.2.2 Elastic modulus . 10 4.2.3 Fatigue . 11 4.2.4 Fracture toughness . 11 4.2.5 Creep . 11 4.2.6 Micro-yielding . 11 4.2.7 Coefficient of thermal expansion and coefficient of moisture expansion . 12 4.2.8 Corrosion fatigue . 12 4.2.9 Hydrogen embrittlement . 13 4.2.10 Mechanical contact surface effects . 13 4.2.11 Hydrogen, Oxygen and Nitrogen uptake . 13 4.3 Interfaces . 13 4.3.1 General . 13 4.3.2 Anodizing . 13 4.3.3 Chemical conversion . 14 4.3.4 Metallic coatings (overlay and diffusion) . 14 4.3.5 Hard coatings . 14 4.3.6 Thermal barriers . 14 SIST EN 16603-32-08:2016
EN 16603-32-08:2016 (E) 3 4.3.7 Moisture barriers . 14 4.3.8 Coatings on CFRP . 15 4.3.9 Organic coatings as paint . 15 4.4 Joining (mechanical fastening). 15 4.4.1 General . 15 4.4.2 Bolted joints . 15 4.4.3 Riveted joints . 16 4.4.4 Inserts . 16 4.5 Design . 16 4.5.1 Metallic design allowables . 16 4.5.2 Composite design allowables . 16 4.6 Verification . 18 4.6.1 Metallic materials . 18 4.6.2 Composite materials - laminates . 18 4.6.3 Test methods on metals . 19 4.6.4 Test methods on composites . 19 4.6.5 Non-destructive inspection . 21 4.7 Data exchange . 21 Bibliography . 22 SIST EN 16603-32-08:2016
EN 16603-32-08:2016 (E) 4 European Foreword This document (EN 16603-32-08:2016) has been prepared by Technical Committee CEN/CLC/TC 5 “Space”, the secretariat of which is held by DIN. This standard (EN 16603-32-08:2016) originates from ECSS-E-ST-32-08C 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 2017, and conflicting national standards shall be withdrawn at the latest by February 2017. 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 supersedes EN 14607-8:2004. The main changes with respect to EN 14607-8:2004 are listed below: - new EN number and modified title, - Reorganization of the content of the document to separate descriptive text and requirements, including clarification, modification of requirements and implementation of change requests, - Alignment of the three Standards EN 16603-32-08 (based on ECSS-E-ST-32-08C Rev.1), EN 16602-70 (based on ECSS-Q-ST-70C Rev.1) and EN 16602-70-71 (based on ECSS-Q-ST-70-71C), - Deletion of deletion of clauses 4.2, 4.4, 4.9, 4.10, 4.12, 4.13 and Table 1. This document has been prepared under a mandate given to CEN by the European Commission and the European Free Trade Association. 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 16603-32-08:2016
EN 16603-32-08:2016 (E) 5 1 Scope ECSS-E-ST-32-08 specifies the mechanical engineering requirements for materials. This Standard also encompasses the mechanical effects of the natural and induced environments to which materials used for space applications can be subjected.
This standard specifies requirements for the establishment of the mechanical and physical properties of the materials to be used for space applications, and the verification of these requirements.
Verification includes destructive and non-destructive test methods. Quality assurance requirements for materials (e.g. procurement and control) are covered by ECSS-Q-ST-70. This standard may be tailored for the specific characteristics and constrains of a space project in conformance with ECSS-S-ST-00. SIST EN 16603-32-08:2016
EN 16603-32-08:2016 (E) 6 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 16603-32 ECSS-E-ST-32 Space engineering -
Structural EN 16602-70 ECSS-Q-ST-70 Space product assurance - Materials, mechanical parts and processes EN 16602-70-37 ECSS-Q-ST-70-37 Space product assurance - Determination of the susceptibility of metals to stress-corrosion cracking EN 16602-70-71 ECSS-Q-ST-70-71 Space product assurance - Material, processes and their data selection
EN 4179:2005 Aerospace series - Qualification and approval of personnel for non-destructive testing SIST EN 16603-32-08:2016
EN 16603-32-08:2016 (E) 7 3 Terms, definitions and abbreviated terms 3.1 Terms and definitions from other standards a. For the purpose of this standard, the terms and definitions from ECSS-S-ST-00-01 and ECSS-E-ST-32 apply, in particular for the followings:
1. A-basis design allowable (A-value) 2. B-basis design allowable (B-value) 3. corrosion 3.2 Terms specific to the present standard 3.2.1 composite sandwich construction panels composed of a lightweight core material, such as honeycomb, foamed plastic, and so forth, to which two relatively thin, dense, high-strength or high stiffness faces or skins are adhered 3.2.2 material design allowable material property that has been determined from test data on a probability basis and has been chosen to assure a high degree of confidence in the integrity of the completed structure 3.2.3 micro-yield applied force to produce a residual strain of 1 × 10-6 mm/m along the tensile or compression loading direction 3.2.4 polymer high molecular weight organic compound, natural or synthetic, with a structure that can be represented by a repeated small unit, the mer NOTE
E.g. polyethylene, rubber, and cellulose. SIST EN 16603-32-08:2016
EN 16603-32-08:2016 (E) 8 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 ASTM
American Society for Testing Materials CFRP
carbon fibre reinforced plastic CMC
ceramic matrix composites CME
coefficient of moisture expansion CTE
coefficient of thermal expansion DRD
document requirements definition EB
electron beam EN
European Standard Kic
plane strain critical stress intensity factor Kiscc
plane strain critical stress intensity factor for a specific environment LEO
low Earth orbit MIG
metal inert gas MMC
metal matrix composite NDE
non-destructive evaluation NDI
non-destructive inspection NDT
non-destructive test PTFE
polytetrafluoroethylene SCC
stress-corrosion cracking STS
space transportation system TIG
tungsten inert gas UD
uni-directional UV
ultra violet 3.4 Nomenclature The following nomenclature applies throughout this document: a. The word “shall” is used in this standard to express requirements. All the requirements are expressed with the word “shall”. b. The word “should” is used in this standard to express recommendations. All the recommendations are expressed with the word “should”. NOTE It is expected that, during tailoring, recommendations in this document are either converted into requirements or tailored out. c. The words “may” and “need not” are used in this standard to express positive and negative permissions, respectively. All the positive SIST EN 16603-32-08:2016
EN 16603-32-08:2016 (E) 9 permissions are expressed with the word “may”. All the negative permissions are expressed with the words “need not”. d. The word “can” is used in this standard to express capabilities or possibilities, and therefore, if not accompanied by one of the previous words, it implies descriptive text. NOTE In ECSS “may” and “can” have completely different meanings: “may” is normative (permission), and “can” is descriptive. e. The present and past tenses are used in this standard to express statements of fact, and therefore they imply descriptive text. SIST EN 16603-32-08:2016
EN 16603-32-08:2016 (E) 10 4 Requirements 4.1 General a. The supplier shall perform the review of materials for structures to be used in space at Materials, Mechanical Parts and Processes Control Board (MPCB) in conformance with requirements from clause 4.2.3 of ECSS-Q-ST-70.
NOTE
This clause covers only structural subjects affecting materials for use in space projects. 4.2 Functionality 4.2.1 Strength a. The material strength shall be established for the worst combination of mechanical and thermal effects expected during its lifetime. NOTE
The strength of a material is highly dependent on the direction as well as on the sign of the applied load, e.g. axial tensile, transverse compressive, and others. Structural subjects are covered in ECSS-E-ST-32. 4.2.2 Elastic modulus a. For composites, the specified elastic modulus shall be verified by test on representative samples, in tension and in compression directions. NOTE 1 For metallic and alloy, it can be based on values certified by the manufacturer. NOTE 2 The elastic modulus defined as the ratio between the uniaxial stress and the strain (e.g. Young’s modulus, compressive modulus, shear modulus) is for metals and alloys weakly dependant on heat-treatment and orientation. However, for fibre reinforced materials, the elastic modulus depends on the fibre orientation. SIST EN 16603-32-08:2016
EN 16603-32-08:2016 (E) 11 4.2.3 Fatigue a. For all components subject to alternating stresses, it shall be demonstrated that the degradation of material properties over the complete mission remains within the specified limits. NOTE
Fatigue fracture can form in components which are subjected to alternating stresses. These stresses can exist far below the allowed static strength of the material. For fracture control, see ECSS-E-ST-32-01. 4.2.4 Fracture toughness a. For homogeneous materials the Kic or Kiscc shall be measured according to procedures approved by the customer at MPCB. b. Metallic materials intended for use in corrosive surface environments shall be tested for fracture. NOTE
The fracture toughness is a measure of the damage tolerance of a material containing initial flaws or cracks. The fracture toughness in metallic materials is described by the plain strain value of the critical stress intensity factor. The fracture toughness depends on the environment. For fracture control, see ECSS-E-ST-32-01. 4.2.5 Creep a. A risk analysis shall be performed to assess the risk of creeping. b. If analysis specified in 4.2.5a confirms that creep can occur, the creep testing campaign to be performed shall be agreed with the customer at MPCB. NOTE
Creep is a time-dependant deformation of a material under an applied load. It usually occurs at elevated temperature, although some materials creep at room temperature. If permitted to continue indefinitely, creep terminates in rupture. Extrapolations from simple to complex stress-temperature time conditions are difficult. 4.2.6 Micro-yielding a. A risk analysis shall be performed to assess the risk of micro-yielding. N
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2003-01.Slovenski inštitut za standardizacijo. Razmnoževanje celote ali delov tega standarda ni dovoljeno.Vesoljska tehnika - MaterialiRaumfahrttechnik - WerkstoffeIngénierie spatiale - MatériauxSpace engineering - Materials49.140Vesoljski sistemi in operacijeSpace systems and operationsICS:Ta slovenski standard je istoveten z:FprEN 16603-32-08kSIST FprEN 16603-32-08:2016en,fr,de01-marec-2016kSIST FprEN 16603-32-08:2016SLOVENSKI
STANDARD
kSIST FprEN 16603-32-08:2016
EUROPEAN STANDARD NORME EUROPÉENNE EUROPÄISCHE NORM
FINAL DRAFT
FprEN 16603-32-08
January
t r s x ICS
v {ä s v r Will supersede EN
s v x r yæ zã t r r v
English version
Space engineering æ Materials
Ingëierie spatiale æ Matëiaux
Raumfahrttechnik æ Werkstoffe This draft European Standard is submitted to CEN members for unique acceptance procedureä It has been drawn up by the
If this draft becomes a European Standardá CEN and CENELEC membRegulations which stipulate the conditions for giving this European Standard the status of a national standard without any alterationä
This draft European Standard was established by CEN and CENELECversion in any other language made by translation under the responsibility of a CEN and CENELEC member into its own language and notified to the CENæCENELEC Management Centre has the same status as the official versionsä
CEN and CENELEC members are the national standards bodies and national electrotechnical committees of Austriaá Belgiumá Bulgariaá Croatiaá Cyprusá Czech Republicá Denmarká Estoniaá Finlandá Former Yugoslav Republic of Macedoniaá Franceá Germanyá Greeceá Hungaryá Icelandá Irelandá Italyá Latviaá Lithuaniaá Luxembourgá Maltaá Netherlandsá Norwayá Polandá Portugalá Romaniaá Slovakiaá Sloveniaá Spainá Swedená Switzerlandá Turkey and United Kingdomä
Recipients of this draft are invited to submitá with their commentsá notification of any relevant patent rights of which they are aware and to provide supporting documentationä
Warning ã This document is not a European Standardä It is distributed for review and commentsä It is subject to change without notice and shall not be referred to as a European Standardä CEN-CENELEC Management Centre: Avenue Marnix 17, B-1000 Brussels y any means reserved worldwide for CEN national Members and for CENELEC Membersä Refä Noä FprEN
s x x r uæ u tæ r zã t r s x EkSIST FprEN 16603-32-08:2016
FprEN 16603-32-08:2016 (E) 2 Table of contents European Foreword . 4 1 Scope . 5 2 Normative references . 6 3 Terms, definitions and abbreviated terms . 7 3.1 Terms and definitions from other standards . 7 3.2 Terms specific to the present standard . 7 3.3 Abbreviated terms. 8 3.4 Nomenclature . 8 4 Requirements . 10 4.1 General . 10 4.2 Functionality . 10 4.2.1 Strength . 10 4.2.2 Elastic modulus . 10 4.2.3 Fatigue . 11 4.2.4 Fracture toughness . 11 4.2.5 Creep . 11 4.2.6 Micro-yielding . 11 4.2.7 Coefficient of thermal expansion and coefficient of moisture expansion . 12 4.2.8 Corrosion fatigue . 12 4.2.9 Hydrogen embrittlement . 13 4.2.10 Mechanical contact surface effects . 13 4.2.11 Hydrogen, Oxygen and Nitrogen uptake . 13 4.3 Interfaces . 13 4.3.1 General . 13 4.3.2 Anodizing . 13 4.3.3 Chemical conversion . 14 4.3.4 Metallic coatings (overlay and diffusion) . 14 4.3.5 Hard coatings . 14 4.3.6 Thermal barriers . 14 kSIST FprEN 16603-32-08:2016
FprEN 16603-32-08:2016 (E) 3 4.3.7 Moisture barriers . 14 4.3.8 Coatings on CFRP . 15 4.3.9 Organic coatings as paint . 15 4.4 Joining (mechanical fastening). 15 4.4.1 General . 15 4.4.2 Bolted joints . 15 4.4.3 Riveted joints . 16 4.4.4 Inserts . 16 4.5 Design . 16 4.5.1 Metallic design allowables . 16 4.5.2 Composite design allowables . 16 4.6 Verification . 18 4.6.1 Metallic materials . 18 4.6.2 Composite materials - laminates . 18 4.6.3 Test methods on metals . 19 4.6.4 Test methods on composites . 19 4.6.5 Non-destructive inspection . 21 4.7 Data exchange . 21 Bibliography . 22 kSIST FprEN 16603-32-08:2016
FprEN 16603-32-08:2016 (E) 4 European Foreword This document (FprEN 16603-32-08:2016) has been prepared by Technical Committee CEN/CLC/TC 5 “Space”, the secretariat of which is held by DIN (Germany). This document (FprEN 16603-32-08:2016) originates from ECSS-E-ST-32-08C Rev.1. This document is currently submitted to the Unique Acceptance Procedure. This document will supersede EN 14607-8:2004. This document has been developed to cover specifically space systems and will the-refore have precedence over any EN covering the same scope but with a wider do-main of applicability (e.g. : aerospace).
kSIST FprEN 16603-32-08:2016
FprEN 16603-32-08:2016 (E) 5 1 Scope ECSS-E-ST-32-08 specifies the mechanical engineering requirements for materials. This Standard also encompasses the mechanical effects of the natural and induced environments to which materials used for space applications can be subjected.
This Standard specifies requirements for the establishment of the mechanical and physical properties of the materials to be used for space applications, and the verification of these requirements.
Verification includes destructive and non-destructive test methods. Quality assurance requirements for materials (e.g. procurement and control) are covered by ECSS-Q-ST-70. This standard may be tailored for the specific characteristics and constrains of a space project in conformance with ECSS-S-ST-00. kSIST FprEN 16603-32-08:2016
FprEN 16603-32-08:2016 (E) 6 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 16603-32 ECSS-E-ST-32 Space engineering -
Structural EN 16602-70 ECSS-Q-ST-70 Space product assurance - Materials, mechanical parts and processes EN 16602-70-37 ECSS-Q-ST-70-37 Space product assurance - Determination of the susceptibility of metals to stress-corrosion cracking EN 16602-70-71 ECSS-Q-ST-70-71 Space product assurance - Material, processes and their data selection
EN 4179:2005 Aerospace series - Qualification and approval of personnel for non-destructive testing kSIST FprEN 16603-32-08:2016
FprEN 16603-32-08:2016 (E) 7 3 Terms, definitions and abbreviated terms 3.1 Terms and definitions from other standards a. For the purpose of this Standard, the terms and definitions from ECSS-S-ST-00-01 and ECSS-E-ST-32 apply, in particular for the followings:
1. A-basis design allowable (A-value) 2. B-basis design allowable (B-value) 3. corrosion 3.2 Terms specific to the present standard 3.2.1 composite sandwich construction panels composed of a lightweight core material, such as honeycomb, foamed plastic, and so forth, to which two relatively thin, dense, high-strength or high stiffness faces or skins are adhered 3.2.2 material design allowable material property that has been determined from test data on a probability basis and has been chosen to assure a high degree of confidence in the integrity of the completed structure 3.2.3 micro-yield applied force to produce a residual strain of 1 × 10-6 mm/m along the tensile or compression loading direction 3.2.4 polymer high molecular weight organic compound, natural or synthetic, with a structure that can be represented by a repeated small unit, the mer NOTE
E.g. polyethylene, rubber, and cellulose. kSIST FprEN 16603-32-08:2016
FprEN 16603-32-08:2016 (E) 8 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 ASTM
American Society for Testing Materials CFRP
carbon fibre reinforced plastic CMC
ceramic matrix composites CME
coefficient of moisture expansion CTE
coefficient of thermal expansion DRD
document requirements definition EB
electron beam EN
European Standard Kic
plane strain critical stress intensity factor Kiscc
plane strain critical stress intensity factor for a specific environment LEO
low Earth orbit MIG
metal inert gas MMC
metal matrix composite NDE
non-destructive evaluation NDI
non-destructive inspection NDT
non-destructive test PTFE
polytetrafluoroethylene SCC
stress-corrosion cracking STS
space transportation system TIG
tungsten inert gas UD
uni-directional UV
ultra violet 3.4 Nomenclature The following nomenclature applies throughout this document: a. The word “shall” is used in this Standard to express requirements. All the requirements are expressed with the word “shall”. b. The word “should” is used in this Standard to express recommendations. All the recommendations are expressed with the word “should”. NOTE It is expected that, during tailoring, recommendations in this document are either converted into requirements or tailored out. c. The words “may” and “need not” are used in this Standard to express positive and negative permissions, respectively. All the positive kSIST FprEN 16603-32-08:2016
FprEN 16603-32-08:2016 (E) 9 permissions are expressed with the word “may”. All the negative permissions are expressed with the words “need not”. d. The word “can” is used in this Standard to express capabilities or possibilities, and therefore, if not accompanied by one of the previous words, it implies descriptive text. NOTE In ECSS “may” and “can” have completely different meanings: “may” is normative (permission), and “can” is descriptive. e. The present and past tenses are used in this Standard to express statements of fact, and therefore they imply descriptive text. kSIST FprEN 16603-32-08:2016
FprEN 16603-32-08:2016 (E) 10 4 Requirements 4.1 General a. The supplier shall perform the review of materials for structures to be used in space at Materials, Mechanical Parts and Processes Control Board (MPCB) in conformance with requirements from clause 4.2.3 of ECSS-Q-ST-70.
NOTE
This clause covers only structural subjects affecting materials for use in space projects. 4.2 Functionality 4.2.1 Strength a. The material strength shall be established for the worst combination of mechanical and thermal effects expected during its lifetime. NOTE
The strength of a material is highly dependent on the direction as well as on the sign of the applied load, e.g. axial tensile, transverse compressive, and others. Structural subjects are covered in ECSS-E-ST-32. 4.2.2 Elastic modulus a. For composites, the specified elastic modulus shall be verified by test on representative samples, in tension and in compression directions. NOTE 1 For metallic and alloy, it can be based on values certified by the manufacturer. NOTE 2 The elastic modulus defined as the ratio between the uniaxial stress and the strain (e.g. Young’s modulus, compressive modulus, shear modulus) is for metals and alloys weakly dependant on heat-treatment and orientation. However, for fibre reinforced materials, the elastic modulus depends on the fibre orientation. kSIST FprEN 16603-32-08:2016
FprEN 16603-32-08:2016 (E) 11 4.2.3 Fatigue a. For all components subject to alternating stresses, it shall be demonstrated that the degradation of material properties over the complete mission remains within the specified limits. NOTE
Fatigue fracture can form in components which are subjected to alternating stresses. These stresses can exist far below the allowed static strength of the material. For fracture control, see ECSS-E-ST-32-01. 4.2.4 Fracture toughness a. For homogeneous materials the Kic or Kiscc shall be measured according to procedures approved by the customer at MPCB. b. Metallic materials intended for use in corrosive surface environments shall be tested for fracture. NOTE
The fracture toughness is a measure of the damage tolerance of a material containing initial flaws or cracks. The fracture toughness in metallic materials is described by the plain strain value of the critical stress intensity factor. The fracture toughness depends on the environment. For fracture control, see ECSS-E-ST-32-01. 4.2.5 Creep a. A risk analysis shall be performed to assess the risk of creeping. b. If analysis specified in 4.2.5a confirms that creep can occur, the creep testing campaign to be performed shall be agreed with the customer at MPCB. NOTE
Creep is a time-dependant deformation of a material under an applied load. It usually occurs at elevated temperature, although some materials creep at room temperature. If permitted to continue indefinitely, creep terminates in rupture. Extrapolations from simple to complex stress-temperature time conditions are difficult. 4.2.6 Micro-yielding a. A risk analysis shall be performed to assess the risk of micro-yielding. NOTE
Micro-yielding can have an impact in the dimensional stability. b. When the analysis specified in 4.2.6a predicts that micro-yielding can occur in an element, the dimensional stability of the element shall be verified by testing.
kSIST FprEN 16603-32-08:2016
FprEN 16603-32-08:2016 (E) 12 NOTE 1 Some materials can exhibit residual strain after mechanical loading. NOTE 2 In general the most severe mechanical loading occurs during launch. 4.2.7 Coefficient of thermal expansion and coefficient of moisture expansion a. Thermal mismatch between structural members shall not generate stresses in the specified operational temperature range for the item higher that the specified allowable limi
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