RHSIsothermalPState:

Path: SpacecraftEstimation/DemoFuns

% Model a spacecraft as an isothermal radiator with an input state.
   This model works only in Earth orbit. It has a second state for a 
   flux modeled as a Markov process.
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   Form:
   xDot = RHSIsothermal( x, t, d )
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   ------
   Inputs
   ------
   x        (2,1) [Temperature;flux]
   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
                  .a4    (1,1) 1/tau
                  .p     (1,1) Internal power
                  .jD0   (1,1) Julian date at t = 0
                  .rECI  (3,1) ECI Position vector
   jD       (1,n) Julian dates

   -------
   Outputs
   -------
   x        (2,1) [Temperature;flux]

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Children:

Thermal: ThermalAnalysis/RHSIsothermal

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