Path: CubeSat/Thermal
% An isothermal CubeSat model dynamical right-hand-side.
The entire spacecraft is assumed to be at the same temperature. p should
have all the input flux vectors such as sun, albedo and earth radiation.
This input should 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. In this case the function
does not compute an 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,:) or (1,1) Temperature of faces or total temperature
t (1,1) Time (unused)
d (.) Data structure
.mass (1,:) or (1,1) face masses or total mass (kg)
.uSurface (3,:) Surface unit vectors
.alpha (1,:) Absorptivity
.epsilon (1,:) Emissivity
.area (1,:) Area (m^2)
.cP (1,1) Specific heat capacity (J/kg-K)
.powerTotal (1,:) or (1,1) Internal power (W)
.k (n,n) Thermal conductivity (W/deg-K)
p (3,:) Thermal fluxes in the body frame (W/m2)
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Outputs
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tDot (1,:) or (1,1) Temperature derivative of faces or total
Teq (1,1) Equilibrium temperature (for total mass)
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CubeSat: Modeling/CubeSatFaces Common: Graphics/Plot2D
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