IsothermalCubeSatSim:

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.
--------------------------------------------------------------------------

Children:

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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