IsothermalCubeSatSim:

Path: CubeSat/Thermal

% An isothermal CubeSat simulation using Euler integration.
 The entire spacecraft is assumed to be at the same temperature.
 The spacecraft temperature is computed over the given orbit.  
--------------------------------------------------------------------------
   Form:
   IsothermalCubeSatSim -- demo
   t = IsothermalCubeSatSim( d, r, q, jD, t0 )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   d       (.)      Data structure
                    .mass       (1,1) Total mass
                    .uSurface   (3,6) Surface unit vectors
                    .alpha      {1,6} Absorptivity
                    .epsilon    {1,6} Emissivity
                    .area       (1,6) Area
                    .cP         (1,1) Specific heat
                    .powerTotal (1,1) Internal power (W)
   r      (3,:)     Orbit
   q      (4,:)     Quaternion
   jD     (1,:)     Julian date
   t0     (1,1)     Initial Temperature( deg-K )

   -------
   Outputs
   -------
   t      (1,:)     Temperature

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 See also SunV1, Eclipse, RHSIsothermalCubeSat.
--------------------------------------------------------------------------

Children:

AeroUtils: Coord/QLVLH
Common: Graphics/Plot2D
Common: Quaternion/QForm
Common: Time/Date2JD
CubeSat: Thermal/RHSIsothermalCubeSat
SC: BasicOrbit/RVFromKepler
SC: Ephem/Eclipse
SC: Ephem/SunV1

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