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.
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Form:
PropagateLowThrust( x0, d )
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Inputs
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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
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Outputs
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x (1,1) The tag if action is 'initialize'
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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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