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
Back to the CubeSat Module page