OrbitStateMatrices:

% Generate the orbit state matrices
   The matrices are ax = b
   x is the vector of decision variables or controls
   The order is [x1;x2;x3;...;xN] where each x is a vector

   xI is only used to compute the term mu/R^3. A constant xI is 
   sufficient for most low-altitude landings.

   Type OrbitStateMatrices for a demo.

--------------------------------------------------------------------------
   Form:
   [a,b,xF0,aX,bX] = OrbitStateMatrices( xI, xF, dT, d )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   x       (6,:)   States [x;y;z;vX;vY;vZ]
   xF      (6,:)   Final desired state   [x;y;z;vX;vY;vZ]
   dT      (1,1)   Delta time
   d        (.)    Data structure describing spacecraft model
                   .beta   (1,:) Thrust angle in rv plane
                   .alpha  (1,:) Thrust angle out of plane
                   .thrust (1,:) Thrust (N)
                   .accel  (1,:) 'constant' or 'free'
                   .m0     (1,1) Dry mass
                   .radius (1,1) Planet radius

   -------
   Outputs
   -------
   a     (6,3*n)   Matrix multiplying the decision variables
   b     (6,1)     Right hand side
   xF0   (6,1)     Final state without control
   aX    {n}       Cell array of state transition matrices
   bX    {n}       Cell array of input matrices

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Children:

Common: General/DispWithTitle
Missions: LunarLanding/RHSPlanet3D
Missions: LunarLanding/RHSPlanet3DToAB
SC: BasicOrbit/Period