This paper recalls a non-linear constructive
method, based on controlling cascades of conic-systems as it
applies to the control of quad-rotor aircraft. Such a method
relied on the physical model of the system to construct high performance,
modest sampling period (Ts = .02 s) and low complexity
digital-controllers. The control of fixed-wing aircraft,
however is not nearly a straight forward task in extending
results related to the control of quad-rotor aircraft. Although
fixed-wing aircraft and quad-rotor aircraft ultimately share