Patent ID: 6554229
Filing Date: 2003-04-29
Classification: B64C,Y02T

Abstract:
An aerodynamic control system for roll control of an aircraft around a longitudinal axis of the aircraft, the aerodynamic control system comprising:a first wing having a rear portion, the first wing having a top surface and a bottom surface; an aileron assembly having an upper panel and a lower panel, the upper panel being pivotally attached to the top surface of the first wing at the rear portion and the lower panel being pivotally attached to the bottom surface of the first wing at the rear portion, wherein the upper panel and the lower panel are operatively related such that both the upper panel and the lower panel are deflected in an upward direction as a unit from both an upper panel neutral position and a lower panel neutral position, the upper panel having an upper surface where the upper surface of the upper panel forms a continuation of the first wing top surface when the upper panel is in the upper panel neutral position, wherein the upper panel is limited to deflect only upwardly relative to the upper panel neutral position, the lower panel having a lower surface where the lower surface of the lower panel forms a continuation of the first wing bottom surface when the lower panel is in the lower panel neutral position; and a second wing, the second wing being opposite the first wing, the second wing having the aileron assembly such that only the upward deflection of the upper panel of the aileron assembly on the second wing is sufficient to effect roll control of the aircraft without adverse yaw of a nose of the aircraft.