Path: SpacecraftEstimation/OrbitEstimation
% Computes the right-hand-side of the for a point mass gravity model.
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Form:
xDot = FOrbitKFPointMass( x, t, d )
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Inputs
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x (6,1) The state vector [r;v]
t (1,1) Time (sec)
d (1,1) Data structure*
.mu (1,1) Gravitational potential
.aExt (3,1) External acceleration, ex. thruster firings
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Outputs
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xDot (6,1) The derivative of the state vector
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Math: Linear/Mag
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