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.
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Form:
xDot = RHSIsothermal( x, t, d )
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Inputs
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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
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Outputs
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x (2,1) [Temperature;flux]
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SC: BasicOrbit/Period SC: BasicOrbit/RVFromKepler SC: Environs/EarthAlb SC: Environs/EarthRad SC: Environs/SolarFlx SC: Ephem/Eclipse SC: Ephem/SunV1 Thermal: ThermalAnalysis/RHSIsothermal Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/DeBlankLT Common: General/IsVersionAfter Common: General/MatToCell Common: General/StringToTokens Common: General/Watermark Common: Graphics/NPlot Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/Plot3D Common: Graphics/PltStyle Common: Graphics/TimeLabl Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS Common: Time/DTSToDTA Common: Time/Date2JD Common: Time/FindSolsticeOrEquinox Math: Linear/Dot Math: Linear/DupVect Math: Linear/Mag Math: Linear/Unit Math: Trigonometry/CosD Math: Trigonometry/SinD
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