Path: OpticalNavigation/Dynamics
% Right hand side for a planetary mission
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Form:
d = RHSHelioMission
[xDot, rPlanet, vPlanet, acc] = RHSHelioMission(x,t,d)
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Inputs
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x (7,1) [r;v;m] (km,km/s,kg)
t (1,1) Time (s)
d (.) Data structure
.mu (2,1) [mu Earth; mu Moon] (km^3/s^2)..
.ref (1,1) Orbit reference
.thrust (3,1) Thrust vector (N)
.jD0 (1,1) Reference Julian data (days)
.uE (1,1) Exhaust velocity (m/s)
.mD (1,1) Dry mass (kg)
.x0 (7,1) Default initial state
.states {:} State names
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Outputs
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xDot (7,1) d[r;v;m]/dt (km,km/s,kg)
rPlanet (3,1) Position of planet (km)
vPlanet (3,1) Velocity of planet (km/s)
acc (3,1) Total non-gravitational acceleration (km/s^2)
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Orbit: OrbitMechanics/APlanet SC: Ephem/PlanetPosJPL Common: Database/Constant Common: Time/JD2000 Math: Linear/Mag
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