Path: Thermal/ThermalAnalysis
% Model a spacecraft as an isothermal radiator in lunar orbit.
This is useful for preliminary estimates of radiator area.
The spaceccraft illuminated area is aS with radiators of area aR.
You enter the orbital elements and spacecraft properties. The function will
compute the temperature as a function of time.
This function includes solar, albedo and radiation. Both lunar and
earth eclipses are modeled.
Type IsothermalLunar for a demo.
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Form:
IsolthermalLunar;
t = Isothermal( el, d, jD )
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Inputs
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el (1,6) Orbital elements [a i W w e M]
d (1,1) Data structure
.aR (1,1) Radiator area (m^2)
.aS (1,1) Spacecraft illuminated area (m^2)
.alpha (1,1) Spacecraft absorption (0-1)
.epsR (1,1) Radiator emissivity (0-1)
.t0 (1,1) Initial Temperature (deg-K)
.cP (1,1) Average specific heat of the spacecraft (J/kg deg-K)
.m (1,1) Spacecraft mass (kg)
.p (1,:) Internal power consumption (W)
jD (1,n) Julian dates
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Outputs
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t (1,n) Temperature (deg-K)
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SC: BasicOrbit/RVFromKepler SC: Environs/EarthAlb SC: Environs/EarthRad SC: Ephem/Eclipse SC: Ephem/MoonV1 SC: Ephem/SunV1 Common: Database/Constant Common: Graphics/Plot2D Common: Graphics/TimeLabl Common: Time/Date2JD Math: Linear/DupVect Math: Linear/Mag Math: Linear/Unit
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