Path: SpacecraftEstimation/OrbitEstimation
% Computes the right-hand-side of the orbit equations about a mass point.
The derivative function d.dFName must be of the form
fun( x, t, d ) where d may be a data structure.
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Form:
xDot = OrbitKFRHS( x, t, d, q )
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Inputs
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x (:,1) The state vector [x;p]
t (1,1) Time
d (1,1) Data structure
.dFName (:,1) Derivative function
.nStates (1,1) Number of elements in the state vector
... Data for derivative function
q Plant noise matrix
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Outputs
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x (:,1) The state vector derivative[xDot;pDot]
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SpacecraftEstimation: OrbitEstimation/ReshapeCovariance Math: Analysis/Jacobian
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