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Path: CubeSat/Visualization
% Draw the Earth, CubeSat model, orbit, sensor cone(s), and GPS
constellation. The spacecraft can be left out (empty) to just view the
cones.
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Form:
out = DrawSpacecraftInOrbit( jD0, orbit, gSC, qEB, planet, cone, gps )
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Inputs
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jD0 (1,1) Julian date epoch.
orbit (1,6) Orbital elements [a,i,W,w,e,M]
gSC (.) Data structure array or mat-file that stores it.
Each element of array is a component in the body.
.name String name of component
.v Vertices
.f Faces
.scale Scale
.color Color of each component
.alpha Transparency (0-1) of each component
qEB (4,1) ECI to Body quaternion. Uses [1;0;0;0] if not
entered.
planet (:) Name of planet file to use (e.g. 'Earth')
cone (.) Cone geometry. Includes:
.fov Field of view
.pitch Pitch angle from nadir
.azimuth Azimuth angle from north
gps (1,1) Flag to include GPS constellation or not.
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Outputs
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out (.) Data structure with satellite Earth fixed
position, cone
See also: PlaybackOrbitSim.m
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AerospaceUtils: Coord/ECEFToLLA AerospaceUtils: Coord/ECIToEF AerospaceUtils: Coord/LLAToECEF Common: ComponentModels/Cone Common: Graphics/CameraControls Common: Graphics/Map Common: Quaternion/AU2Q Common: Quaternion/QForm Common: Quaternion/QMult Common: Quaternion/QRand Common: Quaternion/QTForm Common: Time/Date2JD Common: Time/JD2T CubeSat: MissionPlanning/RapidSwath CubeSat: Utilities/CubeSatModel Math: Linear/Cross Math: Linear/Dot Math: Linear/DupVect Math: Linear/Mag Math: Linear/Unit Orbit: OrbitMechanics/PropagateTLECommonTime SC: BasicOrbit/Period SC: BasicOrbit/RVFromKepler SC: Ephem/SunV1 SC: Ephem/TerminatorLine
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