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.
   [r, v, t] = RVOrbGen( el, t, uSun, mu, rPlanet, tol )

   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

   r          (3,:) Position vectors for times t
   v          (3,:) Velocity vectors for times t
   t          (1,:) Times at which r and v are calculated

   See also RVFromKepler


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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