公开(公告)号：CA2841447C

公开(公告)日：2019-01-15

申请号：CA2841447

申请日：2011-07-26

Applicant: LEARJET INC

Inventor： BUTLER HARRIS ,  VELETAS MIHALIS ,  HAWKINS JAMES D

IPC: B64C13/24

Abstract: A bias gain system (10) for aircraft rudder comprises a pair of connector ends (21) receiving an actuation force from a bias actuator (12). A rudder bar interface is positioned between the connector ends. The interface rotates about the rudder bar (11) as a function of the actuation forces from the bias actuators. A mechanism comprising links and joints between the connector ends and the rudder bar is actuatable between a contracted configuration, in which first moment arms are defined between the connector ends and the rudder bar interface, and an expanded gain configuration, in which second moment arms have a greater dimension than the first moment arms. An actuator is connected to the mechanism to actuate the mechanism independently from the actuation forces from the bias actuators, to move the mechanism between configurations. An aircraft and a method for controlling a torque on a rudder bar of an aircraft are also provided.