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.
   PropagateLowThrust( x0, d )

   x0          (1,:)  Initial state
   d           (1,1)  .stoppingCondition (1,:) 'time', 
                                               'approaching distance',
                                               'receding distance'
                                               'increasing velocity',
                                               'decreasing velocity',
                      .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

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



Orbit: OrbitMechanics/VEscape
Orbit: RHSOrbit/FOrbLowThrust
SC: BasicOrbit/E2Nu
SC: BasicOrbit/M2E
SC: BasicOrbit/M2EApp
SC: BasicOrbit/M2EEl
SC: BasicOrbit/M2EHy
SC: BasicOrbit/M2Nu
SC: BasicOrbit/M2NuPb
SC: Ephem/Planets
SC: Ephem/SolarSys
Common: CommonData/SwooshWatermark
Common: GUIs/TimeGUI
Common: General/CellToMat
Common: General/CloseIfHandle
Common: General/DeBlankLT
Common: General/MatToCell
Common: General/Watermark
Common: Graphics/NewFig
Common: Graphics/Plot2D
Common: Graphics/PltStyle
Common: Graphics/TextS
Common: Graphics/XLabelS
Common: Graphics/YLabelS
Common: Time/DTSToDTA
Common: Time/Date2JD
Common: Time/JD2T
Math: Linear/DupVect

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