Path: CubeSat/Thermal
% An isothermal CubeSat simulation using Euler integration.
The entire spacecraft is assumed to be at the same temperature.
The spacecraft temperature is computed over the given orbit.
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Form:
IsothermalCubeSatSim -- demo
t = IsothermalCubeSatSim( d, r, q, jD, t0 )
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Inputs
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d (.) 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)
r (3,:) Orbit
q (4,:) Quaternion
jD (1,:) Julian date
t0 (1,1) Initial Temperature( deg-K )
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Outputs
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t (1,:) Temperature
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See also SunV1, Eclipse, RHSIsothermalCubeSat.
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AeroUtils: Coord/QLVLH Common: Graphics/Plot2D Common: Quaternion/QForm Common: Time/Date2JD CubeSat: Thermal/RHSIsothermalCubeSat SC: BasicOrbit/RVFromKepler SC: Ephem/Eclipse SC: Ephem/SunV1
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