Path: OpticalNavigation/Dynamics
% Right hand side for a heliocentric mission
This is a three body model with the sun, a planet (or asteroid).
Either the sun or the planet/asteroid can be the gravitational center.
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Form:
d = RHSUKFHelioMission
[xDot, rPlanet, vPlanet] = RHSUKFHelioMission(x,t,d)
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Inputs
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x (7,1) [r;v;m] (km,km/s)
t (1,1) Time (s)
d (.) Data structure
.mu (2,1) [mu Sun; mu Planet] (km^3/s^2)..
.ref (1,1) Orbit center reference
.acc (3,1) Acceleration vector (km/s^2)
.jD0 (1,1) Reference Julian data (days)
.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 secondary body (km)
vPlanet (3,1) Velocity of secondary body (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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