Path: Orbit/OrbitMechanics

% Generate RV from parameters

 Computes hyperbolic elements from velocity at infinity, radius at perigee
 Inclination, argument or perigee and longitude of the ascending node
 are optional.

 Type VInfRPToRV for a demo.

   [r,v,el] = VinfRPToRV( vInf, rP, f, mu, i, lon, arg )

   vInf  (1,1)   Velocity at infinity (km/s)
   rP    (1,1)   Radius of perigee (km)
   f     (1,1)   True anomaly (rad)
   mu    (1,1)   Gravitational parameter (km^2/s^3) (Default earth)
   i     (1,1)   Inclination (rad)
   lon   (1,1)   Longitude of the ascending node (rad)
   arg   (1,1)   Argument of perigee (rad)

   r     (3,1)   Position (km)
   v     (3,1)   Velocity (km/s)
   el    (1,6)   [a i W w e M]



AC: ACData/ACTConstants
SC: BasicOrbit/CP2I
SC: BasicOrbit/E2M
SC: BasicOrbit/E2Nu
SC: BasicOrbit/El2RV
SC: BasicOrbit/M2E
SC: BasicOrbit/M2EApp
SC: BasicOrbit/M2EEl
SC: BasicOrbit/M2EHy
SC: BasicOrbit/M2Nu
SC: BasicOrbit/M2NuPb
SC: BasicOrbit/Nu2E
SC: BasicOrbit/Nu2M
SC: SCData/sCTConstants
Common: CommonData/Constants
Common: CommonData/SwooshWatermark
Common: CommonData/xSplashSmall
Common: Database/Constant
Common: General/CellToMat
Common: General/DeleteCell
Common: General/DispWithTitle
Common: General/MatToCell
Common: General/Watermark
Common: Graphics/NewFig
Common: Graphics/Plot2D
Common: Graphics/PltStyle
Math: Linear/DupVect

Back to the Orbit Module page