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 from the solar flux and internal power. Either enter a vector of dates in jD or provide a timestep in the data structure. -------------------------------------------------------------------------- Form: IsothermalCubeSatSim -- demo t = IsothermalCubeSatSim( d, r, q, jD, t0 ) -------------------------------------------------------------------------- ------ Inputs ------ d (.) Data structure .mass (1,1) Total mass (kg) .uSurface (3,n) Surface unit vectors .alpha (1,n) Absorptivity .epsilon (1,n) Emissivity .area (1,n) Area (m^2) .cP (1,1) Specific heat capacity (J/kg-K) .powerTotal (1,1) Internal power (W) .dT (1,1) Timestep (optional, s) r (3,:) Orbit q (4,:) Quaternion jD (1,:) Julian date t0 (1,1) Initial Temperature( deg-K ) ------- Outputs ------- t (1,:) Temperature -------------------------------------------------------------------------- See also SunV1, Eclipse, RHSIsothermalCubeSat. --------------------------------------------------------------------------
AerospaceUtils: Coord/QLVLH CubeSat: Thermal/RHSIsothermalCubeSat Orbit: OrbitSim/RVFromKepler SC: Ephem/Eclipse SC: Ephem/SunV1 Common: Graphics/AddFillToPlots Common: Graphics/Plot2D Common: Quaternion/QForm Common: Time/Date2JD
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