FLambert:

Path: Orbit/OrbitControl

% Right hand side for locally optimizing the Lambert time of flight problem.
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   Form:
   dV = FLambert( t, d )
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   -------
   Inputs
   -------
   t          (1,2)     Start and transfer time
   d                    Maneuver data
    .r1, .v1  (6,1)     Initial state
    .r2, .v2  (3,1)     Target state
    .type     (:)       Type {'direct' 'retrograde'}
    .dTMax    (1,1)     Maximum allowed transfer time (sec)
    .rhs      (:)       RHS function, 'FOrb' or 'FOrbHF'
    .mu       (1,1)     Gravitational parameter
    .tol      (1,1)     Tolerance
   g                    Gravity model struct, for FOrbKF
    .mu                 Gravitational parameter
    .s, .c, .j, .a      Model parameters

   -------
   Outputs
   -------
   dV         (1,1)     Magnitude of delta-V

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Children:

Math: Integration/RK45
Math: Linear/Mag
Orbit: GravityModels/LoadGravityModel
Orbit: OrbitMechanics/LambertTOF

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