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.
--------------------------------------------------------------------------
Form:
xDot = RHSIsothermal( x, t, d )
--------------------------------------------------------------------------
------
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]
--------------------------------------------------------------------------
Thermal: ThermalAnalysis/RHSIsothermal
Back to the SpacecraftEstimation Module page