Patent ID: 9561846
Date: 2017-02-07
CPC Classifications: B64C

Claim:
1. A bias gain system for aircraft rudder, comprising: a pair of bias actuators; a pair of connector ends, each of said connector ends receiving an actuation force from a respective one of the bias actuators; a rudder bar; a rudder bar interface positioned between the connector ends and connected to the rudder bar for rotation therewith about an axis of the rudder bar 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 for transmission of the actuation forces to the rudder bar, the mechanism being actuated 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 are defined between the connector ends and the rudder bar interface, the second moment arms having a greater dimension than the first moment arms; and at least one actuator connected to the mechanism to actuate the mechanism independently from the actuation forces from the bias actuators so as to move the mechanism between the contracted configuration and the expanded gain configuration.