A system for integrated pitch and thrust control of an aircraft. The system includes a calculation device which receives the first to sixth electrical signals, together with the tenth electrical signal and delivers first and second linear combinations of the first and second electrical signals, with the coefficients given to the first and second electrical signals, respectively, in the first and second linear combinations depending on the third to sixth and tenth electrical signals; another calculation device which receives the third to tenth electrical ...
A pitch and thrust control system for an aircraft (1), comprising: (a) first airfoils for pitch control (5, 12) actuated from a first actuator member (14) associated with a first transducer (18) delivering a first electrical signal representative of a first longitudinal parameter setting (QaQQQQaQaQddp
이 특허를 인용한 특허 피인용횟수: 10
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