Path: Orbit/OrbitSim
% Propagate a low thrust trajectory with constant thrust
Assumes 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: RHSOrbit/FOrbLowThrust SC: Ephem/Planets Common: GUIs/TimeGUI Common: Graphics/Plot2D Common: Time/Date2JD
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