Path: CubeSat/Thermal
% An isothermal CubeSat model dynamical 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 mass is a vector it will
compute temperatures separately for each face. An optional matrix
k provides face thermal conductivities. For multiple faces,
internal power is per face.
If there are no output arguments the demo will plot the equilibrium
temperature.
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Form:
RHSIsothermalCubeSat -- demo
d = RHSIsothermalCubeSat -- default data structure
[tDot, Teq] = RHSIsothermalCubeSat( t0, t, d, p )
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Inputs
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t0 (1,6) or (1,1) Temperature of faces or total temperature
t (1,1) Time (unused)
d (.) Data structure
.mass (1,6) or (1,1) face masss or 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 (1,6) or (1,1) Internal power (W)
.k (6,6) Thermal conductivity (W/deg-K)
p (3,:) Thermal flux in the body frame (W/m2)
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Outputs
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tDot (:,6) or (1,:) Temperature derivative of faces or total
Teq (:,6) or (1,:) Equilibrium temperature of faces or total
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