PropagateLowThrust:

Path: Orbit/OrbitSim

% Propagate a low thrust trajectory assuming that the thrust is constant
   and tangential to the orbit. 
   The mass flow is modeled as Thrust = mDot*uE.
--------------------------------------------------------------------------
   Form:
   PropagateLowThrust( x0, d )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   x0          (1,:)  Initial state
   d           (1,1)  .stoppingCondition (1,:) 'time', 
                                               'approaching distance',
                                               'receding distance'
                                               'increasing velocity',
                                               'decreasing velocity',
                                                'escape'
                      .stoppingValue     (1,1) value 
                      .thrust            (1,1) Thrust
                      .mu                (1,1) gravitational parameter
                      .uE                (1,1) Exhaust velocity
                      .mass              (1,1) Initial mass
                      .absTol            (1,1) Absolute tolerance
                      .relTol            (1,1) Relative tolerance
                      .t                 (1,:) Time steps

   -------
   Outputs
   -------
   x           (1,1)  The tag if action is 'initialize'

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Children:

Common: GUIs/TimeGUI
Common: Graphics/Plot2D
Common: Time/Date2JD
Orbit: RHSOrbit/FOrbLowThrust
SC: Ephem/Planets

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