RHSPlanet3DToAB:

% This function computes the matrices a and b for dx/dt = a*x + b*u .

 This is for the function RHSPlanet3D. If aL is entered it will use
 an analytical solution for a spherical planet. The mass state equation
 is not output. b multiplies the acceleration vector.

 Type RHSPlanet3DToAB for a demo.

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   Form:
   [a,b,aC] = RHSPlanet3DToAB( x, d, dT )
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   ------
   Inputs
   ------
   x   (6,1)	[r;v] (km/km/s)
   d   (.)   Data structure for RHSPlanet3D
   dT  (1,1) Time step

   -------
   Outputs
   -------
   a   (6,6) State transition matrix
   b   (6,3) Input matrix
   aC  (6,6) Continuous

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Children:

Common: Control/C2DZOH
Common: General/DispWithTitle
Math: Linear/Mag
Math: Linear/Skew
Missions: LunarLanding/RHSPlanet3D