ASTM E1997-07
(Practice)Standard Practice for the Selection of Spacecraft Materials
Standard Practice for the Selection of Spacecraft Materials
SIGNIFICANCE AND USE
This practice is a guideline for proper materials and process selection and application. The specific application of these guidelines must take into account contractual agreements, functional performance requirements for particular programs and missions, and the actual environments and exposures anticipated for each material and the equipment in which the materials are used. Guidelines are not replacements for careful and informed engineering judgment and evaluations and all possible performance and design constraints and requirements cannot be foreseen. This practice is limited to unmanned systems and unmanned or external portions of manned systems, such as the Space Station. Generally, it is applicable to systems in low earth orbit, synchronous orbit, and interplanetary missions. Although many of the suggestions and cautions are applicable to both unmanned and manned spacecraft, manned systems have additional constraints and requirements for crew safety which may not be addressed adequately in unmanned designs. Because of the added constraints and concerns for human-rated systems, these systems are not addressed in this practice.
SCOPE
1.1 The purpose of this practice is to aid engineers, designers, quality and reliability control engineers, materials specialists, and systems designers in the selection and control of materials and processes for spacecraft, external portion of manned systems, or man-tended systems. Spacecraft systems are very different from most other applications. Space environments are very different from terrestrial environments and can dramatically alter the performance and survivability of many materials. Reliability, long life, and inability to repair defective systems (or high cost and difficultly of repairs for manned applications) are characteristic of space applications. This practice also is intended to identify materials processes or applications that may result in degraded or unsatisfactory performance of systems, subsystems, or components. Examples of successful and unsuccessful materials selections and uses are given in the appendices.
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Designation:E1997–07
Standard Practice for the
1
Selection of Spacecraft Materials
This standard is issued under the fixed designation E1997; the number immediately following the designation indicates the year of
original adoption or, in the case of revision, the year of last revision.Anumber in parentheses indicates the year of last reapproval.A
superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
1. Scope MIL-HDBK-17 Properties of Composite Materials
2.4 European Space Agency (ESA) Standard:
1.1 The purpose of this practice is to aid engineers, design-
5
PSS-07/QRM-0 Guidelines for Space Materials Selection
ers, quality and reliability control engineers, materials special-
2.5 Federal Standard:
ists, and systems designers in the selection and control of
QQ-A-250 Aluminum and Aluminum Alloy Plate and
materials and processes for spacecraft, external portion of
4
Sheet, Federal Specification for
manned systems, or man-tended systems. Spacecraft systems
areverydifferentfrommostotherapplications.Spaceenviron-
3. Significance and Use
ments are very different from terrestrial environments and can
3.1 This practice is a guideline for proper materials and
dramatically alter the performance and survivability of many
process selection and application. The specific application of
materials.Reliability,longlife,andinabilitytorepairdefective
these guidelines must take into account contractual agree-
systems (or high cost and difficultly of repairs for manned
ments, functional performance requirements for particular
applications) are characteristic of space applications. This
programs and missions, and the actual environments and
practice also is intended to identify materials processes or
exposures anticipated for each material and the equipment in
applications that may result in degraded or unsatisfactory
which the materials are used. Guidelines are not replacements
performance of systems, subsystems, or components. Ex-
forcarefulandinformedengineeringjudgmentandevaluations
amplesofsuccessfulandunsuccessfulmaterialsselectionsand
and all possible performance and design constraints and
uses are given in the appendices.
requirements cannot be foreseen. This practice is limited to
2. Referenced Documents unmanned systems and unmanned or external portions of
2
manned systems, such as the Space Station. Generally, it is
2.1 ASTM Standards:
applicabletosystemsinlowearthorbit,synchronousorbit,and
E595 Test Method for Total Mass Loss and Collected
interplanetarymissions.Althoughmanyofthesuggestionsand
Volatile Condensable Materials from Outgassing in a
cautions are applicable to both unmanned and manned space-
Vacuum Environment
craft, manned systems have additional constraints and require-
G64 ClassificationofResistancetoStress-CorrosionCrack-
ments for crew safety which may not be addressed adequately
ing of Heat-Treatable Aluminum Alloys
in unmanned designs. Because of the added constraints and
2.2 Marshall Space Flight Center (MSFC) Standard:
concerns for human-rated systems, these systems are not
MSFC-SPEC-522 Design Criteria for Controlling Stress
3 addressed in this practice.
Corrosion Cracking
4
2.3 Military Standards:
4. Design Constraints
MIL-STD-889 Dissimilar Materials
4.1 Orbital Environment—Theactualenvironmentinwhich
MIL-HDBK-5 Metallic Materials and Elements for Aero-
the equipment is expected to operate must be identified and
space Vehicle Structures
defined. The exposures and requirements for material perfor-
mance differ for various missions. Environment definition
includes defining the range of temperature exposure, number
1
This practice is under the jurisdiction of ASTM Committee E21 on Space
and rate of thermal cycles, extent of vacuum exposure, solar
SimulationandApplicationsofSpaceTechnologyandisthedirectresponsibilityof
electromagnetic radiation particulate radiation, (trapped by the
Subcommittee E21.05 on Contamination.
Current edition approved Dec. 1, 2007. Published January 2008. Originally
earth’s magnetosphere, solar wind, solar flares, and gamma
´1
approved in 1999. Last previous edition approved in 2003 as E1997–99(2003) .
rays) micrometeroids, launch loads and vibration, structural
DOI: 10.1520/E1997-07.
2 loads, and so forth. Materials suitable for one orbit or mission
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
environment may be unsuitable for others. The applications
contactASTM Customer Service at service@astm.org. ForAnnual Book ofASTM
Standards volume information, refer to the standard’s Document Summary page on
and requirements will define the suitability of the materials.
the ASTM website.
3
Marshall Space Flight Center, AL 35812.
4
Available from the Superintendent of Documents, U.S. Government Printing
5
Office, Washington, DC 20402. European Space Agency, 8–10, Rue
...
This document is not anASTM standard and is intended only to provide the user of anASTM standard an indication of what changes have been made to the previous version. Because
it may not be technically possible to adequately depict all changes accurately,ASTM recommends that users consult prior editions as appropriate. In all cases only the current version
of the standard as published by ASTM is to be considered the official document.
e1
Designation:E1997–99 (Reapproved 2003) Designation: E 1997 – 07
Standard Practice for the
1
Selection of Spacecraft Materials
This standard is issued under the fixed designation E1997; the number immediately following the designation indicates the year of
original adoption or, in the case of revision, the year of last revision.Anumber in parentheses indicates the year of last reapproval.A
superscript epsilon (e) indicates an editorial change since the last revision or reapproval.
1
e NOTE—Keywords were added editorially in October 2003.
1. Scope
1.1 Thepurposeofthispracticeistoaidengineers,designers,qualityandreliabilitycontrolengineers,materialsspecialists,and
systems designers in the selection and control of materials and processes for spacecraft, external portion of manned systems, or
man-tended systems. Spacecraft systems are very different from most other applications. Space environments are very different
fromterrestrialenvironmentsandcandramaticallyaltertheperformanceandsurvivabilityofmanymaterials.Reliability,longlife,
andinabilitytorepairdefectivesystems(orhighcostanddifficultlyofrepairsformannedapplications)arecharacteristicofspace
applications. This practice also is intended to identify materials processes or applications that may result in degraded or
unsatisfactory performance of systems, subsystems, or components. Examples of successful and unsuccessful materials selections
and uses are given in the appendices.
2. Referenced Documents
2
2.1 ASTM Standards:
E595 Test Method for Total Mass Loss and Collected Volatile Condensable Materials from Outgassing in a Vacuum
Environment
G64 Classification of Resistance to Stress-Corrosion Cracking of Heat-Treatable Aluminum Alloys
2.2 Marshall Space Flight Center (MSFC) Standard:
3
MSFC-SPEC-522 Design Criteria for Controlling Stress Corrosion Cracking
2.3 Military Standards:
4
MIL-STD-889 Dissimilar Materials
4
MIL-HDBK-5Metallic Materials and Elements for Aerospace Vehicle Structures
MIL-STD-889 Dissimilar Materials
MIL-HDBK-5 Metallic Materials and Elements for Aerospace Vehicle Structures
MIL-HDBK-17 Properties of Composite Materials
2.4 European Space Agency (ESA) Standard:
PSS-07/QRM-0Guidelines for Space Materials Selection
5
PSS-07/QRM-0 Guidelines for Space Materials Selection
2.5 Federal Standard:
4
QQ-A-250 Aluminum and Aluminum Alloy Plate and Sheet, Federal Specification for
3. Significance and Use
3.1 This practice is a guideline for proper materials and process selection and application. The specific application of these
guidelines must take into account contractual agreements, functional performance requirements for particular programs and
missions, and the actual environments and exposures anticipated for each material and the equipment in which the materials are
used.Guidelinesarenotreplacementsforcarefulandinformedengineeringjudgmentandevaluationsandallpossibleperformance
and design constraints and requirements cannot be foreseen. This practice is limited to unmanned systems and unmanned or
external portions of manned systems, such as the Space Station. Generally, it is applicable to systems in low earth orbit,
1
This practice is under the jurisdiction of ASTM Committee E21 on Space Simulation and Applications of Space Technology and is the direct responsibility of
Subcommittee E21.05 on Contamination.
Current edition approved Oct. 1, 2003. Published October 2003. Originally approved in 1999. Last previous edition approved in 1999 as E1997–99.
e1
Current edition approved Dec. 1, 2007. Published January 2008. Originally approved in 1999. Last previous edition approved in 2003 as E1997–99(2003) .
2
ForreferencedASTMstandards,visittheASTMwebsite,www.astm.org,orcontactASTMCustomerServiceatservice@astm.org.ForAnnualBookofASTMStandards
volume information, refer to the standard’s Document Summary page on the ASTM website.
3
Marshall Space Flight Center, AL 35812.
4
Available from the Superintendent of Documents, U.S. Government Printing Office, Washington, DC 20402.
5
European Space Agency, 8–10, Rue Mario-Nikis, 75738 Paris Cedex, France.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.
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E1997–07
synchronous orbit, and interplanetary missions.Although many of the suggestions and cautions are applicable to both unmanned
andmannedspacecraft,mannedsystemshaveadditionalconstraintsandrequirementsforcrewsafetywhichmaynotbeaddressed
adequately in unmanned designs. Because of the added constraint
...
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