1、Designation: E 491 73 (Reapproved 2004)e1Standard Practice forSolar Simulation for Thermal Balance Testing of Spacecraft1This standard is issued under the fixed designation E 491; the number immediately following the designation indicates the year oforiginal adoption or, in the case of revision, the
2、 year of last revision. A number in parentheses indicates the year of last reapproval. Asuperscript epsilon (e) indicates an editorial change since the last revision or reapproval.e1NOTEAn editorial change was made in paragraph 6.6.5.2 in February 2005.1. Scope1.1 Purpose:1.1.1 The primary purpose o
3、f this practice is to provideguidance for making adequate thermal balance tests of space-craft and components where solar simulation has been deter-mined to be the applicable method. Careful adherence to thispractice should ensure the adequate simulation of the radiationenvironment of space for ther
4、mal tests of space vehicles.1.1.2 A corollary purpose is to provide the proper testenvironment for systems-integration tests of space vehicles.Anaccurate space-simulation test for thermal balance generallywill provide a good environment for operating all electrical andmechanical systems in their var
5、ious mission modes to deter-mine interferences within the complete system. Althoughadherence to this practice will provide the correct thermalenvironment for this type of test, there is no discussion of theextensive electronic equipment and procedures required tosupport systems-integration testing.1
6、.2 NonapplicabilityThis practice does not apply to orprovide incomplete coverage of the following types of tests:1.2.1 Launch phase or atmospheric reentry of space ve-hicles,1.2.2 Landers on planet surfaces,1.2.3 Degradation of thermal coatings,1.2.4 Increased friction in space of mechanical devices
7、,sometimes called “cold welding,”1.2.5 Sun sensors,1.2.6 Man in space,1.2.7 Energy conversion devices, and1.2.8 Tests of components for leaks, outgassing, radiationdamage, or bulk thermal properties.1.3 Range of Application:1.3.1 The extreme diversification of space-craft, designphilosophies, and an
8、alytical effort makes the preparation of abrief, concise document impossible. Because of this, variousspacecraft parameters are classified and related to the importantcharacteristic of space simulators in a chart in 7.6.1.3.2 The ultimate result of the thermal balance test is toprove the thermal des
9、ign to the satisfaction of the thermaldesigners. Flexibility must be provided to them to trade offadditional analytical effort for simulator shortcomings. Thecombination of a comprehensive thermal-analytical model,modern computers, and a competent team of analysts greatlyreduces the requirements for
10、 accuracy of space simulation.1.4 UtilityThis practice will be useful during space ve-hicle test phases from the development through flight accep-tance test. It should provide guidance for space simulationtesting early in the design phase of thermal control models ofsubsystems and spacecraft. Flight
11、 spacecraft frequently aretested before launch. Occasionally, tests are made in a spacechamber after a sister spacecraft is launched as an aid inanalyzing anomalies that occur in space.1.5 This standard does not purport to address all of thesafety concerns, if any, associated with its use. It is the
12、responsibility of the user of this standard to establish appro-priate safety and health practices and determine the applica-bility of regulatory limitations prior to use.2. Referenced Documents2.1 ASTM Standards:2E 259 Practice for Preparation of Pressed Powder WhiteReflectance Factor Transfer Stand
13、ards for Hemisphericaland Bi-Directional GeometriesE 296 Practices for Ionization Gage Application to SpaceSimulatorsE 297 Methods for Calibrating Ionization Vacuum GageTubes3E 349 Terminology Relating to Space Simulation2.2 ISO Standard:ISO 1000-1973 SI Units and Recommendations for the Useof Their
14、 Multiples and of Certain Other Units32.3 American National Standards:41This practice is under the jurisdiction of ASTM Committee E21 on SpaceSimulation and Applications of Space Technology and is the direct responsibility ofSubcommittee E21.04 on Space Simulation Test Methods.Current edition approv
15、ed Sept. 1, 2004. Published September 2004. Originallyapproved in 1973. Last previous edition approved in 1999 as E 491 73 (1999).2For referenced ASTM standards, visit the ASTM website, www.astm.org, orcontact ASTM Customer Service at serviceastm.org. For Annual Book of ASTMStandards volume informat
16、ion, refer to the standards Document Summary page onthe ASTM website.3Withdrawn.4Available from American National Standards Institute (ANSI), 25 W. 43rd St.,4th Floor, New York, NY 10036.1Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United State
17、s.ANSI Y10.18-1967 Letter Symbols for Illuminating Engi-neeringANSI Z7.1-1967 Standard Nomenclature and Definitionsfor Illuminating EngineeringANSI Y10.19-1969 Letter Symbols for Units Used in Sci-ence and Technology3. Terminology3.1 Definitions, Symbols, Units, and ConstantsThis sec-tion contains t
18、he recommended definitions, symbols, units, andconstants for use in solar simulation for thermal balance testingof spacecraft. The International System of Units (SI) andInternational and American National Standards have beenadhered to as much as possible.Terminology E 349 is also usedand is so indic
19、ated in the text. Table 1 provides commonly usedsymbols.3.2 Definitions:3.2.1 absorptance (ae, av,a )ratio of the absorbed radiantor luminous flux to the incident flux (E 349)(Table 1).3.2.2 absorptivity of an absorbing materialinternal ab-sorptance of a layer of the material such that the path of t
20、heradiation is of unit length (E 349).3.2.3 air mass one (AM1)the equivalent atmosphericattenuation of the electromagnetic spectrum to modify the solarirradiance as measured at one astronomical unit from the sumoutside the sensible atmosphere to that received at sea level,when the sun is in the zeni
21、th position.3.2.4 air mass zero (AM0)the absence of atmosphericattenuation of the solar irradiance at one astronomical unitfrom the sun.3.2.5 albedothe ratio of the amount of electromagneticradiation reflected by a body to the amount incident upon it.3.2.6 apparent sourcethe minimum area of the fina
22、lelements of the solar optical system from which issues 95 % ormore of the energy that strikes an arbitrary point on the testspecimen.3.2.7 astronomical unit (AU)a unit of length defined asthe mean distance from the earth to the sun (that is,149 597 890 6 500 km).3.2.8 blackbody (USA), Planckian rad
23、iatora thermal ra-diator which completely absorbs all incident radiation, what-ever the wavelength, the direction of incidence, or the polar-ization. This radiator has, for any wavelength, the maximumspectral concentration of radiant exitance at a given tempera-ture (E 349).3.2.9 collimateto render
24、parallel, (for example, rays oflight).3.2.10 collimation anglein solar simulation, the angularnonparallelism of the solar beam, that is, the decollimationangle. In general, a collimated solar simulator uses an opticalcomponent to image at infinity an apparent source (pseudo sun)of finite size.The an
25、gle subtended by the apparent source to thefinal optical component referred to as the collimator, is definedas the solar subtense angle and establishes the nominal angle ofdecollimation. A primary property of the “collimated” systemis the near constancy of the angular subtense angle as viewedfrom an
26、y point in the test volume. The solar subtense angle istherefore a measure of the nonparallelism of the beam. Toavoid confusion between various scientific fields, the use ofsolar subtense angle instead of collimation angle or decollima-tion angle is encouraged (see solar subtense angle).3.2.11 colli
27、matoran optical device which renders rays oflight parallel.3.2.12 decollimation anglenot recommended (see colli-mation angle).3.2.13 diffuse reflectora body that reflects radiant energyin such a manner that the reflected energy may be treated as ifit were being emitted (radiated) in accordance with
28、Lambertslaw. The radiant intensity reflected in any direction from a unitarea of such a reflector varies as the cosine of the anglebetween the normal to the surface and the direction of thereflected radiant energy (E 349).3.2.14 dispersion function (X/l)a measure of the separa-tion of wavelengths fr
29、om each other at the exit slit of themonochromator, where X is the distance in the slit plane and lis wavelength. The dispersion function is, in general, differentfor each monochromator design and is usually available fromthe manufacturer.3.2.15 divergence anglesee solar beam divergence angle(3.2.60
30、).3.2.16 electromagnetic spectrumthe ordered array ofknown electromagnetic radiations, extending from the shortestTABLE 1 Commonly Used SymbolsSymbol Quantity Definition Equation or Value Unit Unit SymbolQ radiant energy, work,quantity of heatjoule JF radiant flux F =dQ/dt watt (joule/second) W, Js1
31、E irradiance (receiver) fluxdensityE =dF/dA watt per square metre Wm2M radiant exitance (source) M =dF/dA watt per square metre Wm2I radiant intensity (source) I =dF/dv watt per steradian Wsr1v = solid angle through which flux from source is radiatedL radiance L =dI/(dA cosu ) watt per steradian =sq
32、uare metreWsr1m2u = angle between line of sight and normal to surface dAt transmittance t = F, transmitted/F, incident nonet(l) spectral transmittance t(l)=F(l), transmitted/F(l), incident noner reflectance (total) r = F, reflected/F, incident noneeH emittance (totalhemispherical)eH = M, specimen/M,
33、 blackbodya absorptance a = F, absorbed/F, incident noneassolar absorptance as= solar irradiance absorbed/solar irradiance incident noneE 491 73 (2004)e12wavelengths, gamma rays, through X rays, ultraviolet radia-tion, visible radiation, infrared and including microwave andall other wavelengths of r
34、adio energy (E 349).3.2.17 emissivity of a thermal radiator e, e =Me,th/Me(e = 1)ratio of the thermal radiant exitance of the radiator tothat of a full radiator at the same temperature, formerly“pouvoir emissif ” (E 349).3.2.18 emittance (e)the ratio of the radiant exitance of aspecimen to that emit
35、ted by a blackbody radiator at the sametemperature identically viewed. The term generally refers to aspecific sample or measurement of a specific sample. Totalhemispherical emittance is the energy emitted over the hemi-sphere above emitting element for all wavelengths. Normalemittance refers to the
36、emittance normal to the surface to theemitting body.3.2.19 exitance at a point on a surface (radiant exitance)(M)quotient of the radiant flux leaving an element of thesurface containing the point, by the area of that element,measured in Wm2(E 349)(Table 1).3.2.20 field anglenot recommended (see sola
37、r beam sub-tense angle).3.2.21 flight modelan operational flight-capable space-craft that is usually subjected to acceptance tests.3.2.22 flux (radiant, particulate, and so forth)for electro-magnetic radiation, the quantity of radiant energy flowing perunit time; for particles and photons, the numbe
38、r of particles orphotons flowing per unit time (E 349).3.2.23 gray bodya body for which the spectral emittanceand absorptance is constant and independent of wavelength.The term is also used to describe bodies whose spectralemittance and absorptance are constant within a given wave-length band of int
39、erest (E 349).3.2.24 incident anglethe angle at which a ray of energyimpinges upon a surface, usually measured between the direc-tion of propagation of the energy and a perpendicular to thesurface at the point of impingement or incidence.3.2.25 infrared radiationsee electromagnetic spectrum(E 349).3
40、.2.26 insolationdirect solar irradiance received at a sur-face, contracted from incoming solar radiation.3.2.27 integrating (Ulbrecht) spherepart of an integratingphotometer. It is a sphere which is coated internally with awhite diffusing paint as nonselective as possible, and which isprovided with
41、associated equipment for making a photometricmeasurement at a point of the inner surface of the sphere. Ascreen placed inside the sphere prevents the point underobservation from receiving any radiation directly from thesource (E 349).3.2.28 intensitysee radiant intensity.3.2.29 irradiance at a point
42、 on a surface Ee,E;Ee=dFe/dAquotient of the radiant flux incident on an element of thesurface containing the point, by the area of that elementmeasured in Wm2(E 349)(Table 1).3.2.30 irradiance, mean total (E)the average total irradi-ance over the test volume, as defined by the followingequation:E5 *
43、vE r,u,z!dV/*vdV (1)where:E(r,u,z) = total irradiance as a function of position (Table1).3.2.31 irradiance, spectral Elor E(l)the irradiance at aspecific wavelength over a narrow bandwidth, or as a functionof wavelength.3.2.32 irradiance, temporalthe temporal variation of in-dividual irradiances fro
44、m the mean irradiance. The temporalvariations should be measured over time intervals equal to thethermal time constants of the components. The temporalstability of total irradiance can be defined as:Et56100DEt min!1DEt max!/2E# (2)3.2.33 irradiance, totalthe integration over all wave-lengths of the
45、spectral irradiance.3.2.34 irradiance, uniformity ofuniformity of total irradi-ance can be defined as:Eu56100Emin!1 Emax!/2E# (3)where:Eu= uniformity of the irradiance within the test vol-ume, expressed as a percent of the mean irradi-ance,E(min)= smallest value obtained for irradiance within thetes
46、t volume, andE(max)= largest value obtained for irradiance within thetest volume.Uniformity of irradiance values must always be specifiedtogether with the largest linear dimension of the detector used.3.2.35 Lamberts lawthe radiant intensity (flux per unitsolid angle) emitted in any direction from a
47、 unit-radiatingsurface varies as the cosine of the angle between the normal tothe surface and the direction of the radiation (also calledLamberts cosine law). Lamberts law is not obeyed exactly bymost real surfaces, but an ideal blackbody emits according tothis law. This law is also satisfied (by de
48、finition) by thedistribution of radiation from a perfectly diffuse radiator and bythe radiation reflected by a perfectly diffuse reflector. Inaccordance with Lamberts law, an incandescent sphericalblackbody when viewed from a distance appears to be auniformly illuminated disk. This law does not take
49、 into accountany effects that may alter the radiation after it leaves thesource.3.2.36 maximum test plane divergence anglethe anglebetween the extreme ray from the apparent source and the testplane. This applies principally to direct projection beamswhere it is equivalent to one half the projection cone angle (seeFig. 1).3.2.37 natural bandwidththe width at half height of aradiation source emission peak. It is independent of instrumentspectral bandwidth, being an intrinsic property of the radiationsource.3
