Path: Orbit/OrbitControl

% Compute two delta-v's to raise the apogee and circularize the orbit.

   [dV1,dV2,tOF,aT] = ApogeeRaisingDeltaV( r, v, rDes, aT );

   r             (3,1)   ECI position (km)
   v             (3,1)   ECI velocity (km/s)
   rDes          (1,1)   Desired apogee (km)
   aT            (1,1)   Transfer orbit semi major axis. Optional. (km)

   dV1           (3,1)   First delta-v to raise the apogee
   dV2           (3,1)   Second delta-v to circularize at apogee
   tOF           (1,1)   Time of flight from current state to final orbit
   aT            (1,1)   Semi major axis of transfer orbit



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
Common: CommonData/SwooshWatermark
Common: General/CellToMat
Common: General/DispWithTitle
Common: General/MatToCell
Common: General/Watermark
Common: Graphics/NewFig
Common: Graphics/Plot2D
Common: Graphics/PltStyle
Math: Linear/Cross
Math: Linear/DupVect
Math: Linear/Mag
Math: Linear/Unit

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