RHSIsothermalCubeSat:

Path: CubeSat/Thermal

% An isothermal CubeSat model right-hand-side.
 The entire spacecraft is assumed to be at the same temperature.
 p should be the net input vector and include sun, albedo and earth 
 radiation. You should also factor in eclipses.  The total power is the 
 internal power that is absorbed by the spacecraft. The specific heat is
 the average over the whole spacecraft.

 If there are no output arguments the demo will plot the equilibrium
 temperature.

 Since version 8.
--------------------------------------------------------------------------
   Form:
   RHSIsothermalCubeSat -- demo
   d = RHSIsothermalCubeSat -- default data structure
   [tDot, Teq] = RHSIsothermalCubeSat( T0, t, d, p )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   T0     (1,1)     Temperature
   t      (1,1)     Time (unused)
   d      (1,1)     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)
   p      (3,:)     Thermal flux in the body frame (W/m2)

   -------
   Outputs
   -------
   tDot     (1,:) Temperature derivative
   Teq      (1,:) Equilibrium temperature

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Children:

Common: Graphics/Plot2D
CubeSat: Utilities/CubeSatFaces

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