OrbitKFRHS:

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
   ------
   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

   -------
   Outputs
   -------
   x  (:,1)     The state vector derivative[xDot;pDot]

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Children:

Math: Analysis/Jacobian
SpacecraftEstimation: OrbitEstimation/ReshapeCovariance

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