IsothermalLunar:

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 )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   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

   -------
   Outputs
   -------
   t        (1,n) Temperature (deg-K)

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Children:

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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