Targeting4BP:

Path: Orbit/LowEnergyManeuver

% Transfer a LET from the restricted 3BP to the Sun/Planet/Moon 4BP

   Since version 9.
--------------------------------------------------------------------------
   Form:
   [elementsNew,dV1EphNew,dtNew,exitflag] = Targeting4BP(elements,dV1Eph,dtTarg,et,p,muMoon);
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   elements         (1,6)    Ecliptic orbital elements of the initial
                             state
   dV1Eph            (1)     Magnitude of the initial burn
   dtTarg            (1)     Transfer time
   et                (1)     Seconds after the Epoch at which the transfer
                             is initiated
   p                 (1)     Distance from the moon to L2
   muMoon            (1)     Gravitational parameter of the moon

   -------
   Outputs
   -------
   elementsNew      (1,6)    Converged ecliptic orbital elements
   dV1EphNew         (1)     Converged maneuver magnitude
   dtNew             (1)     Converged transfer time
   exitflag          (1)     1 if successful
  
--------------------------------------------------------------------------

Children:

Common: Database/Constant
Math: Linear/Mag
Math: Linear/Unit
Orbit: LowEnergyManeuver/CheckForOptimizationToolbox
Orbit: OrbitSim/Propagate4BP
SC: BasicOrbit/El2RV
SC: Ephem/PlanetPositionEMBarycenter

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