Path: SpacecraftEstimation/OrbitEstimation
% Computes the right-hand-side of the orbit equations for OrbitKalmanFilter.
Low-fidelity mode computes about a mass point, high-fidelity mode uses
nonlinear orbit equations, planetary perturbations and modeled forces.
Includes an onboard clock model.
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Form:
xDot = FOrbKF( x, t, d )
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Inputs
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x (n,1) The state vector [r;v] or [r;v;b;f;...]
t Time
d (1,1) Data structure*
.highFidelity (1,1) High fidelity flag
.planetaryOn (1,1) Planetary accelerations flag
.forcesOn (1,1) Disturbance force modeling
.jD (1,1) Julian date
.nZonal (1,1) Number of zonal harmonics
.nTess (1,1) Number of tesseral harmonics
.gravityModel (1,1) Gravity model struct
.aExt (3,1) External acceleration, ex. thruster firings
* Can be left empty for low-fidelity mode
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Outputs
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xDot (n,1) The derivative of the state vector
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Orbit: OrbitMechanics/AGravityC Orbit: OrbitMechanics/PlanetaryAccelerations SC: BasicOrbit/OrbRate SC: BasicOrbit/RV2A SC: Ephem/ECIToPlanet Math: Linear/Mag
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