Patent ID: 6641086
Filing Date: 2003-11-04
Classification: B64C,G05D,Y02T

Abstract:
A system for controlling an aircraft, comprising:an airframe; a first airfoil coupled to a first side of the airframe, at least a portion of the airfoil controllably deflectable to facilitate roll maneuvers of the aircraft, the deflectable portion operable to generate increased lift and a consequent increased drag for at least a portion of the first airfoil during at least one roll maneuver; a second airfoil coupled to a second side of the airframe, at least a portion of the airfoil controllably deflectable to facilitate roll maneuvers of the aircraft, the deflectable portion operable to generate negative lift and a consequent increased drag for at least a portion of the second airfoil during at least one roll maneuver; control software executing on a computer, the control software operable to determine a deflection position of the deflectable portion of the first airfoil and of the deflectable portion of the second airfoil such that: the increased lift of the first airfoil and the decreased lift of the second airfoil generate a roll moment causing the aircraft to roll; an the increased drag of the second airfoil producing a yaw moment that counteracts the yaw moment produced by the increased drag of the first airfoil such that the roll maneuver does not substantially change the yaw moment of the aircraft; and one or more actuators coupled to each deflectable portion, each actuator being operable to deflect an associated deflectable portion to the determined deflection position.