초록 ▼

A method and apparatus is provided for countering asymmetrical aerodynamic forces subjected onto an aircraft. Asymmetrical forces are counteracted by this invention automatically by selectively actuating force inducing elements in response detection of one of (a) differential longitudinal forces ind

A method and apparatus is provided for countering asymmetrical aerodynamic forces subjected onto an aircraft. Asymmetrical forces are counteracted by this invention automatically by selectively actuating force inducing elements in response detection of one of (a) differential longitudinal forces induced upon the aircraft by the engines and (b) undesirable rotation of the aircraft about longitudinal axis "c" of the aircraft. The force inducing elements of this invention function independent of primary control elements and other control surfaces of the aircraft.

대표청구항 ▼

[ What is claimed is:] [1.] 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

[ What is claimed is:] [1.] 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.