Path: Missions/AsteroidProspector
% Right-hand side for low thrust GVE simulation.
Accounts for changing mass as fuel is consumed.
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Form:
xDot = LowThrustGVERHS(x,t,xDes,thrust,mDot,index,mu);
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Inputs
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x (7,1) State vector: 6 Keplerian orbital elements
and mass (kg) [a,i,W,w,e,M,m]
t (1,1) Time (not used)
xDes (6,1) Target state vector: 6 Keplerian orbital
elements [a,i,W,w,e,M]
thrust (1,1) Thrust magnitude (kN)
mDot (1,1) Mass flow rate (kg/sec)
index (1,1) Index of which state element to track, 1 - 5
mu (1,1) Gravitational parameter
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Outputs
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xDot (7,1) State derivatives
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See also GVEDynamics, GVEGuidance
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Missions: AsteroidProspector/GVEGuidance Orbit: OrbitCoord/OrbElemDiff Orbit: OrbitMechanics/GVEDynamics SC: BasicOrbit/CP2I SC: BasicOrbit/E2Nu SC: BasicOrbit/El2RV SC: BasicOrbit/M2E SC: BasicOrbit/M2EApp SC: BasicOrbit/M2EEl SC: BasicOrbit/M2EHy SC: BasicOrbit/M2Nu SC: BasicOrbit/M2NuPb Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/DispWithTitle Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Math: Linear/Cross Math: Linear/DupVect Math: Linear/Unit Math: Trigonometry/WrapPhase
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