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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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Math: Linear/Mag Orbit: Interplanetary/SolarSysState Orbit: OrbitMechanics/APlanet
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