PropagateState:

Path: Missions/LunarLanding

% Propagate the 2D state for the landing problem.
--------------------------------------------------------------------------
   Form:
   xP = PropagateState( x, beta, dT, d )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   x       (4,:)   Initial state [x;y;vX;vY]
   beta    (1,:)   Thrust angle (rad)
   dT      (1,:)   Delta time for each step
   d        (.)    Data structure describing spacecraft model
                   .a (1,1) Thrust acceleration (m/s^2)
                   .g (1,1) Gravitation acceleration (m/s^2)
                   .n (1,1) Number of steps

   -------
   Outputs
   -------
   xP    (4,:)   State

--------------------------------------------------------------------------

Children:

SCPro: DynamicalModels/RHSPlanetTakeoff
Math: Integration/RK4

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