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
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Form:
xDot = FOrbLEOP( t, x, d )
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Inputs
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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
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Outputs
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xDot (7,1) The state vector derivative d[r;v;m]/dt
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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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