Path: SC/Ephem

% Compute the solar intensity experienced by a spacecraft.
   This accounts for eclipses by the Earth and Moon.
   [sI,eE,eM,rSEs,rMEs] = ...
         SolarVisibility( rECI, jD, animate, centralBody, ...fov, map3d )

   rECI       (3,n)    Position vectors in ECI frame
   jD         (1,n)    Julian date for each position
   animate     (1)     Animation setting. 
                          0  No animation.
                          1  Field-of-view animation of Earth & moon with
                                sun at (0,0)
                          2  Orbit animation with line-of-sight vectors to
                                sun, Earth and moon.
                          3  Both animations in one window.

   centralBody (:)     Name of central body. Can be Earth, Sun, or Moon.

   fov         (1)     Sets the angular field of view for the animation
                          window. Units are degrees. 360 is full sky. 180
                          is frontal view.

   map3d       (1)     Flag. Indicates whether to display a 3D map of the
                          central body in the orbit animation or not.

   sI         (1,n)  	Solar intensity at each time. [W/m^2]
   eE         (1,n)    Binary. Eclipse from Earth (1) or not (0).
   eM         (1,n)    Binary. Eclipse from Moon  (1) or not (0).
   rSEs       (3,n)    Position of sun with respect to Earth in ECI. [km]
   rMEs       (3,n)    Position of moon with respect to Earth in ECI. [km]



Common: Database/Constant
Common: Graphics/AddView
Common: Graphics/AddZoom
Common: Graphics/Circle
Common: Graphics/Map
Common: Graphics/NewFig
Common: Time/JD2Date
Math: Linear/Mag
Math: Trigonometry/WrapPhase
SC: BasicOrbit/RVFromKepler
SC: Ephem/Eclipse
SC: Ephem/MoonV1
SC: Ephem/SunV1

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