LambertTOF:

Path: Orbit/OrbitMechanics

% Solves the Lambert time of flight problem using Battin's method.

   Type LambertTOF for a demo

--------------------------------------------------------------------------
   Form:
   [vT, a, p, tol] = LambertTOF( r1, r2, dT, orbitType, mu, tol, maxIter )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   r1            (3,1)   Initial position vector
   r2            (3,1)   Final position vector
   dT            (1,1)   Time between position 2 and 1 (s)
   orbitType     (1,:)   'direct' (1) or 'retrograde' (-1)*
   mu            (1,1)   Gravitational parameter*
   tol           (1,1)   Desired tolerance [1e-10]*
   maxIter       (1,1)   Maximum number of iterations [20]*
                           * optional

   -------
   Outputs
   -------
   vT            (3,2)    Transfer velocity at beginning and end of 
                          the transfer ellipse
   a             (1,1)    Semi-major axis of the trajectory
   p             (1,1)    The parameter for the orbit
   tol           (1,1)    Achieved tolerance

--------------------------------------------------------------------------
   Reference:	Battin, R. H. "An Introduction to the Mathematics and Methods
               of Astrodynamics", AIAA Education Series.
               Vallado, D. A. Fundamentals of Astrodynamics and Applications.
--------------------------------------------------------------------------

Children:

Common: General/DispWithTitle
Math: Linear/Cross
Math: Linear/Unit

Back to the Orbit Module page