ASTM E491-73(2004)

Standard Practice for Solar Simulation for Thermal Balance Testing of Spacecraft

SCOPE
1.1 Purpose
1.1.1 The primary purpose of this practice is to provide guidance for making adequate thermal balance tests of spacecraft and components where solar simulation has been determined to be the applicable method. Careful adherence to this practice should ensure the adequate simulation of the radiation environment of space for thermal tests of space vehicles.
1.1.2 A corollary purpose is to provide the proper test environment for systems-integration tests of space vehicles. An accurate space-simulation test for thermal balance generally will provide a good environment for operating all electrical and mechanical systems in their various mission modes to determine interferences within the complete system. Although adherence to this practice will provide the correct thermal environment for this type of test, there is no discussion of the extensive electronic equipment and procedures required to support systems-integration testing.
1.2 NonapplicabilityThis practice does not apply to or provide incomplete coverage of the following types of tests:
1.2.1 Launch phase or atmospheric reentry of space vehicles,
1.2.2 Landers on planet surfaces,
1.2.3 Degradation of thermal coatings,
1.2.4 Increased friction in space of mechanical devices, sometimes called "cold welding,"
1.2.5 Sun sensors,
1.2.6 Man in space,
1.2.7 Energy conversion devices, and
1.2.8 Tests of components for leaks, outgassing, radiation damage, or bulk thermal properties.
1.3 Range of Application
1.3.1 The extreme diversification of space-craft, design philosophies, and analytical effort makes the preparation of a brief, concise document impossible. Because of this, various spacecraft parameters are classified and related to the important characteristic of space simulators in a chart in .
1.3.2 The ultimate result of the thermal balance test is to prove the thermal design to the satisfaction of the thermal designers. Flexibility must be provided to them to trade off additional analytical effort for simulator shortcomings. The combination of a comprehensive thermal-analytical model, modern computers, and a competent team of analysts greatly reduces the requirements for accuracy of space simulation.
1.4 UtilityThis practice will be useful during space vehicle test phases from the development through flight acceptance test. It should provide guidance for space simulation testing early in the design phase of thermal control models of subsystems and spacecraft. Flight spacecraft frequently are tested before launch. Occasionally, tests are made in a space chamber after a sister spacecraft is launched as an aid in analyzing anomalies that occur in space.
This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety and health practices and determine the applicability of regulatory limitations prior to use.

General Information

• Status: Historical
• Publication Date: 31-Aug-2004
• ICS: 49.140 - Space systems and operations
• Technical Committee: E21 - Space Simulation and Applications of Space Technology
• Drafting Committee: E21.04 - Space Simulation Test Methods

Relations

• Replaces: ASTM E491-73(1999) - Standard Practice for Solar Simulation for Thermal Balance Testing of Spacecraft
• Effective Date: 01-Sep-2004
• Replaced By: ASTM E491-73(2004)e1 - Standard Practice for Solar Simulation for Thermal Balance Testing of Spacecraft
• Effective Date: 01-Sep-2004
• Referred By: ASTM E927-19 - Standard Classification for Solar Simulators for Electrical Performance Testing of Photovoltaic Devices
• Effective Date: 01-Sep-2004
• Referred By: ASTM E284-22 - Standard Terminology of Appearance
• Effective Date: 01-Sep-2004
• Referred By: ASTM E512-94(2020) - Standard Practice for Combined, Simulated Space Environment Testing of Thermal Control Materials with Electromagnetic and Particulate Radiation
• Effective Date: 01-Sep-2004
• Referred By: ASTM E772-15(2021) - Standard Terminology of Solar Energy Conversion
• Effective Date: 01-Sep-2004
• Referred By: ASTM E948-16(2020) - Standard Test Method for Electrical Performance of Photovoltaic Cells Using Reference Cells Under Simulated Sunlight
• Effective Date: 01-Sep-2004

Standards Content (Sample)

NOTICE: This standard has either been superseded and replaced by a new version or withdrawn.
Contact ASTM International (www.astm.org) for the latest information
Designation: E 491 – 73 (Reapproved 2004)
Standard Practice for
1
Solar Simulation for Thermal Balance Testing of Spacecraft
This standard is issued under the fixed designation E491; 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. Scope designers. Flexibility must be provided to them to trade off
additional analytical effort for simulator shortcomings. The
1.1 Purpose:
combination of a comprehensive thermal-analytical model,
1.1.1 The primary purpose of this practice is to provide
modern computers, and a competent team of analysts greatly
guidance for making adequate thermal balance tests of space-
reduces the requirements for accuracy of space simulation.
craft and components where solar simulation has been deter-
1.4 Utility—This practice will be useful during space ve-
mined to be the applicable method. Careful adherence to this
hicle test phases from the development through flight accep-
practice should ensure the adequate simulation of the radiation
tance test. It should provide guidance for space simulation
environment of space for thermal tests of space vehicles.
testing early in the design phase of thermal control models of
1.1.2 A corollary purpose is to provide the proper test
subsystems and spacecraft. Flight spacecraft frequently are
environmentforsystems-integrationtestsofspacevehicles.An
tested before launch. Occasionally, tests are made in a space
accurate space-simulation test for thermal balance generally
chamber after a sister spacecraft is launched as an aid in
willprovideagoodenvironmentforoperatingallelectricaland
analyzing anomalies that occur in space.
mechanical systems in their various mission modes to deter-
1.5 This standard does not purport to address all of the
mine interferences within the complete system. Although
safety concerns, if any, associated with its use. It is the
adherence to this practice will provide the correct thermal
responsibility of the user of this standard to establish appro-
environment for this type of test, there is no discussion of the
priate safety and health practices and determine the applica-
extensive electronic equipment and procedures required to
bility of regulatory limitations prior to use.
support systems-integration testing.
1.2 Nonapplicability—This practice does not apply to or
2. Referenced Documents
provide incomplete coverage of the following types of tests:
2
2.1 ASTM Standards:
1.2.1 Launch phase or atmospheric reentry of space ve-
E259 Practice for Preparation of Pressed Powder White
hicles,
Reflectance Factor Transfer Standards for Hemispherical
1.2.2 Landers on planet surfaces,
and Bi-Directional Geometries
1.2.3 Degradation of thermal coatings,
E296 Practices for Ionization Gage Application to Space
1.2.4 Increased friction in space of mechanical devices,
Simulators
sometimes called “cold welding,”
E297 Methods for Calibrating Ionization Vacuum Gage
1.2.5 Sun sensors,
3
Tubes
1.2.6 Man in space,
E349 Terminology Relating to Space Simulation
1.2.7 Energy conversion devices, and
2.2 ISO Standard:
1.2.8 Tests of components for leaks, outgassing, radiation
ISO 1000-1973 SI Units and Recommendations for the Use
damage, or bulk thermal properties.
3
of Their Multiples and of Certain Other Units
1.3 Range of Application:
4
2.3 American National Standards:
1.3.1 The extreme diversification of space-craft, design
ANSI Y10.18-1967 Letter Symbols for Illuminating Engi-
philosophies, and analytical effort makes the preparation of a
neering
brief, concise document impossible. Because of this, various
ANSI Z7.1-1967 Standard Nomenclature and Definitions
spacecraftparametersareclassifiedandrelatedtotheimportant
for Illuminating Engineering
characteristic of space simulators in a chart in 7.6.
1.3.2 The ultimate result of the thermal balance test is to
prove the thermal design to the satisfaction of the thermal
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
contact ASTM Customer Service at [e-mail]. For Annual Book of ASTM
1
This practice is under the jurisdiction of ASTM Committee E21 on Space Standards volume information, refer to the standard’s Document Summary page on
Simulation andApplications of SpaceTechnology and is the direct responsibility of the ASTM website.
3
Subcommittee E21.04 on Space Simulation Test Methods. Withdrawn.
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Current edition approved Sept. 1, 2004. Published September 2004. Originally Available fromAmerican National Standards Institute (ANSI), 25 W. 43rd St.,
approved in 1973. Last previous edition approved in 1999 as E491–73 (1999). 4th Floor, New York, NY 10036.
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