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   Computes aircraft weight. Any parameter can be varied except type. You must
   enter the fields of d in the order shown in the input list.
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   Form:
   g = ACWeightEstimation( d, tol )
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   Inputs
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   d              (1,1)  Data structure with parameters
                         .type                 (1,:) 'military', 'transport'
                         .nPassengers          (1,n) Number of passengers
                         .weightPayload        (1,n) Weight of payload and crew
                         .dFuselage            (1,n) Fuselage diameter
                         .lFuselage            (1,n) Fuselage lengths
                         .thrustToWeight       (1,n) Thrust to weight ratio
                         .wingLoading          (1,n) Wing loading
                         .structuralLF         (1,n) Structural load factor
                         .thicknessRatio       (1,n) Thickness Ratio
                         .sweepAngle           (1,n) Sweep ratio
                         .tipRootChordRatio    (1,n) tip Chord/Root Chord.
                         .aspectRatio          (1,n) Aspect ratio
                         .thrustToEngineWeight (1,n) Thrust to Engine Weight
                         .fractionFuel         (1,n) Fuel to gross weight ratio
   tol           (1,1) Tolerance on computation
          

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   Outputs
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   g             (1,1)  Structure
                        .gWT           (1,n)  Gross weight
                        .wingWT        (1,n)  Wing weight
                        .fuselageWT    (1,n)  Fuselage weight
                        .engineWT      (1,n)  Engine weight
                        .miscWT        (1,n)  Everything else
   

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