Path: Orbit/OrbitManeuver

% Computes the delta-V to lower apogee.
 Generates the time to the maneuver which is done at perigee.
 It is assumed that the maneuver is an impulse.

 Type OrbMnvrLowerApogee for a circularization demo.

   [deltaV, tToM] = OrbMnvrLowerApogee( el0, rAF, mu )

   elI         (1,6)  Initial elements [a i W w e M]
   rAF         (1,1)  Final apogee
   mu          (1,1)  Gravitational parameter (Earth is the default)

   deltaV      (1,1)  Delta-V 
   tOM         (1,1)  Time of maneuver



Orbit: OrbitCoord/RPRA2AE
Orbit: OrbitCoord/SLR
Orbit: OrbitMechanics/RVOrbGen
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: BasicOrbit/Period
SC: BasicOrbit/RVFromKepler
SC: BasicOrbit/VOrbit
Common: CommonData/SwooshWatermark
Common: General/CellToMat
Common: General/DeBlankLT
Common: General/DispWithTitle
Common: General/MatToCell
Common: General/Watermark
Common: Graphics/Axis3D
Common: Graphics/Mesh2
Common: Graphics/NewFig
Common: Graphics/Plot2D
Common: Graphics/Plot3D
Common: Graphics/PltStyle
Common: Graphics/TimeLabl
Common: Graphics/XLabelS
Common: Graphics/YLabelS
Common: Graphics/ZLabelS
Math: Linear/DupVect

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