Path: Orbit/RHSOrbit
% Right hand side for a heliocentric system with a thruster.
Uses the ephemerides from Planets and SolarSysState to compute
the planet locations in the heliocentric frame.
Since version 2014.1
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Forms:
[xDot, g] = RHSHelioWithPlanets( x, t, d )
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Inputs
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x (7,1) State in the heliocentric frame [r;v;m]
t (1,1) Time since jD0, sec
d (1,1) Data structure
.mDry (1,1) Dry mass (kg)
.thrust (3,1) Heliocentric thrust vector (N)
.uE (1,1) Exhaust velocity (m/s)
.p (1,1) Planet data structure
.jD0 (1,1) Julian date at the start of the
simulation
.muPlanet
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Outputs
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xH (7,1) State in the heliocentric frame
g (1,1) Output data structure
.accelSun (3,1) Acceleration due to the sun
.accelThrust (3,1) Acceleration due to the engine
.accelPlanet (3,:) Acceleration due to planets
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See also APlanet
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Orbit: Interplanetary/SolarSysState Orbit: OrbitMechanics/APlanet 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 Math: Linear/Mag
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