Path: Orbit/RHSOrbit

% Right hand side of the planar orbit equations assuming constant thrust
   and thrust aligned with the velocity vector. This produces a nearly optimal
   spiral into or out from an orbit.
   varargout = FOrbLowThrust( t, x, flag, d )

   t             (1,1)  Time
   x             (5,1)  The state vector [r;phi;rDot;phiDot;mass]
   flag          (1,:)  Flags for ode113
   d             (1,1)  .stoppingCondition (1,:) 'time',
                                                 'approaching distance',
                                                 'receding distance',
                                                 'increasing velocity', 
                                                 'decreasing velocity',
                        .stoppingValue     (1,1) value 
                        .mu                (1,1) gravitational parameters
                        .thrust            (1,1) Thrust
                        .uE                (1,1) Exhaust velocity
                        .mass              (1,1) Dry mass
                        .absTol            (1,1) Absolute tolerance
                        .relTol            (1,1) Relative tolerance
                        .t                 (1,:) Time steps

   varargout     (5,1)  The state vector derivative



Orbit: OrbitMechanics/VEscape
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: General/CellToMat
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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