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Path: Thermal/ThermalAnalysis
% Model a spacecraft as an isothermal radiator.
This model works only in Earth orbit.
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Form:
xDot = RHSIsothermal( x, t, d )
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Inputs
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x (1,1) Temperature
t (1,1) TIme
d (1,1) Data structure
.a1 (1,1) epsilon*a_r/cp*m
.a2 (1,1) alpha*a_s/cp*m
.a3 (1,1) 1/cp*m
.p (1,1) Internal power
.jD0 (1,1) Julian date at t = 0
.rECI (3,1) ECI Position vector
jD (1,n) Julian dates
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Outputs
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x (1,1) Temperatures (deg-K)
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References: Agrawal, B. ,"Design of Geosynchronous Spacecraft,"
Prentice-Hall, 1986, pp. 281-283
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Math: Linear/Mag Math: Linear/Unit SC: Environs/EarthAlb SC: Environs/EarthRad SC: Environs/SolarFlx SC: Ephem/Eclipse SC: Ephem/SunV1
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