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SUPPORT SITE |
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SUPPORT SITE |
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Path: SC/Ephem
% Compute the solar intensity experienced by a spacecraft.
This accounts for eclipses by the Earth and Moon.
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Usage:
[sI,eE,eM,rSEs,rMEs] = ...
SolarVisibility( rECI, jD, animate, centralBody, ...fov, map3d )
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Inputs
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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.
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Outputs
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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]
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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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