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   Aircraft trimming algorithm. Uses the function FTrim. This algorithm
   determines the Euler angles, body rates, engine state and control 
   settings. Initial settings are obtained from d and g. Uses fminsearch.
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   Form:
   [x, d, cost] = ACTrim( x, d, w, g, options )
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   Inputs
   ------
   x             (:)    Aircraft state
   d             (:)    Aircraft data structure
   w             (:,1)  Weights:
                         [vTDot, alphaDot, betaDot, wDot, vT, rDot, eDot, engDot]
   g             (:)    Constraint structure
                          .vT    (1,1) Velocity             (required)
                          .rDot  (1,1) Climb rate           (optional)
                          .eDot  (3,1) Euler angle rate     (optional)
   options              Options for fmins

   -------
   Outputs
   -------
   x             (:)    Trimmed aircraft state
   d             (:)    Trimmed aircraft data structure
   cost                 .start
                        .end

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