|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||24/4213 ; 24/407.5R ; 24/409.0R ; 24/409.0A|
|발명자 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 17 인용 특허 : 4|
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 air...
[ 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 p...