Path: Orbit/RHSOrbit

% Orbit model for Launch and Early Orbit Operations.
   This model is compatible with ode113. It includes an event for
   apogee. If events are on it will stop at apogee unless a burn is
   underway. Its companion function is FOrbLEOPStopping
   xDot = FOrbLEOP( t, x, d )

   t                      Time
   x             (7,1)    The state vector [r;v;m]
   d             (1,1)    Data structure
                          .thrust    (1,1) Engine thrust (N)
                          .mu        (1,1) Gravitational parameter
                          .uE        (1,1) Exhaust velocity (m/s)
                          .cDA       (1,1) Drag area product
                          .burnStart (1,1) Start time of burn
                          .burnEnd   (1,1) End time of burn

   xDot          (7,1)     The state vector derivative d[r;v;m]/dt



AerospaceUtils: AtmosphericCalculations/AtmDens1
AerospaceUtils: AtmosphericCalculations/AtmDensTitan
AerospaceUtils: AtmosphericCalculations/NeptuneDensity
SC: Environs/MolWt2R
Common: CommonData/SwooshWatermark
Common: General/CellToMat
Common: General/DeBlankLT
Common: General/MatToCell
Common: General/Watermark
Common: Graphics/NewFig
Common: Graphics/Plot2D
Common: Graphics/PlotDoubleYAxis
Common: Graphics/PltStyle
Common: Graphics/TitleS
Common: Graphics/XLabelS
Common: Graphics/YLabelS
Math: Linear/Mag

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