Path: Orbit/OrbitMechanics
% Generate an orbit by propagating Keplerian elements.
The orbit may have any eccentricity, including parabolic or hyperbolic.
If t is not entered it generate one orbit. If there are no arguments it
will plot the orbit. Enter rPlanet to draw a planet sphere. If the sun
vector is entered as well the planet sphere will be illuminated.
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Form:
[r, v, t] = RVOrbGen( el, t, uSun, mu, rPlanet, tol )
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Inputs
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elI (1,6) Elements vector [a,i,W,w,e,M] or structure
t (1,:) Time vector (sec)
uSun (3,1) Sun vector*
mu (1,1) Gravitational parameter
rPlanet (1,1) Planet radius*
tol (1,1) Orbit propagation tolerance (1e-8)
* inputs for plotting purposes only
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Outputs
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r (3,:) Position vectors for times t
v (3,:) Velocity vectors for times t
t (1,:) Times at which r and v are calculated
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See also RVFromKepler
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Orbit: OrbitCoord/SLR SC: BasicOrbit/CP2I SC: BasicOrbit/E2M SC: BasicOrbit/E2Nu SC: BasicOrbit/M2E SC: BasicOrbit/M2EApp SC: BasicOrbit/M2EEl SC: BasicOrbit/M2EHy SC: BasicOrbit/Nu2E SC: BasicOrbit/Nu2M Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/DeBlankLT Common: General/MatToCell Common: General/Watermark Common: Graphics/Axis3D Common: Graphics/Mesh2 Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Common: Graphics/TimeLabl Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS Math: Linear/DupVect
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