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.
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Form:
varargout = FOrbLowThrust( t, x, flag, d )
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Inputs
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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',
'escape'
.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
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Outputs
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varargout (5,1) The state vector derivative
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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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