IsothermalCubeSat:
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An isothermal CubeSat model.
The entire spacecraft is assumed to be at the same temperature.
With no output arguments it will plot the equilibrium temperature
for all input p. r is the ECI orbit.
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Form:
IsothermalCubeSat
t = IsothermalCubeSat( d, r, q, jD, t0 )
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Inputs
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d (1,1) 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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Children:
Common: Coord/QForm
Common: Coord/QLVLH
Common: Graphics/Plot2D
Common: Time/Date2JD
Common: Time/JD2T
SC: BasicOrbit/Period
SC: BasicOrbit/RVFromKepler
SC: Ephem/Eclipse
SC: Ephem/SunV1
