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mechanisms and methods for providing rudder control assistance during symmetrical and asymmetrical thrust conditions
mechanisms and methods for providing rudder control assistance during symmetrical and asymmetrical thrust conditions
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机译：对称和非对称推力条件下提供舵控制辅助的机构和方法
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摘要
mechanisms and methods for providing rudder control assistance during symmetrical and asymmetrical thrust conditions. Rudder assistance mechanisms and methods that are operatively connected to an aircraft's rudder control system (rc) are described. the rudder assist mechanisms preferably have over-center spring compensation functions so as to provide substantially no spring force (ie when the coupling is over the spring compensation center), or substantially all of the spring force. spring force (ie when coupling is to the left or right of the spring compensation center) is exerted on the rudder control system (rc). The helm assist mechanism (10) may include a control spring assembly (50), and a coupling assembly that operatively connects the control spring assembly (50) to the helm control assembly. the coupling assembly is operably movable between a zero position, wherein substantially no spring force of the control spring assembly (50) is transferred to the rudder control system (rc) by the coupling assembly, and compensated right and left positions spring, wherein the right and left spring forces of the control spring assembly (50) are transferred to the rudder control system (rc) respectively. zero position can then establish a rudder deflection dead zone within a selected range of right and left deflection angles of the rudder control surface (rcs). thus, right and left spring forces can be transferred to the rudder control system (rc) when the rudder control surface (rcs) is tilted at an angle that exceeds the selected range of deflection angles. Some embodiments include an actuator unit (42) which is operatively capable of moving the connected spring assembly and coupling assembly between a symmetrical thrust mode condition (tsm and an asymmetric thrust mode condition ( tam) to cause different spring forces to be exerted on the rudder control system (rc) under such different thrust conditions.
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