Patent ID: 6095459
Filing Date: 2000-08-01
Classification: B64C,G05D

Abstract:
A method for automatically, free of pilot input, countering undesirable changing attitude of a multi-engine aircraft caused by asymmetrical aerodynamic forces subjected on the aircraft during flight, said aircraft having left and right wings, a primary control element on each wing, a fuselage, and a longitudinal fuselage axis ""c"", comprising:sensing undesirable rotation of the aircraft about axis ""c"" and delivering a respective controlling signal in response thereto;receiving the controlling signal; andautomatically, free of pilot input, causing a force to be exerted on a preselected wing, in response to receiving the controlling signal, in a manner and direction sufficient to counteract the asymmetrical forces on the aircraft and undesirable yaw and roll of the aircraft, said aircraft having a force inducing element on each wing with said force inducing elements being selectively, independently operational relative to primary control elements of the aircraft, said force inducing elements are each a portion of a respective primary control element of a respective wing and each having an increase chamber toward the respective wing tip and being independently actuatable.