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US 6,586,901 B1Granted
Methods and apparatus suitable for facilitating control of an aircraft rudder
AssigneeHoneywell International Inc.
InventorsDonald James Singer, Dean Richard Wilkens
Life of this patent
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Abstract
A method and an apparatus for controlling aircraft rudder movement are disclosed. The system including a yaw damping control portion integrated with a directional compensation rudder control portion, such that the system may simultaneously provide yaw damping control and directional compensation.
Claims21
A control system for producing a signal to manipulate a rudder of an aircraft comprising:
- a yaw damping command source;
- a motor coupled to said yaw damping command source, said motor configured to manipulate a position of the rudder;
- a yaw damping feed forward path configured to transmit a yaw damping signal from said yaw damping command source to said motor;
- a bias command source coupled to said motor;
- and
- a bias command feed forward path configured to transmit a bias command signal from said bias command source to said motor.
3 more elements
An airplane rudder control system comprising:
- a yaw damping feed forward control path including a yaw damping control source and a motor command source;
- a bias command feed forward control path, including a bias command source coupled to said yaw damping feed forward control path;
- and
- a bias command feedback loop coupled to the bias command source.
1 more element
A method of controlling an aircraft rudder control motor, said method comprising the steps of:
- providing a yaw damping command signal;
- providing a bias command signal;
- summing said bias command signal with a current amp signal;
- filtering the sum of said bias command signal and said current amp signal;
- and
- summing the filtered bias command signal with the yaw damping command signal.
3 more elements
Dependencies are inferred from the claim text.