Aeronautics and astronautics – Aircraft control – Automatic
Patent
1988-11-23
1992-12-15
Peters, Jr., Joseph F.
Aeronautics and astronautics
Aircraft control
Automatic
244175, 244195, 244221, 244230, 244179, G05D 100
Patent
active
051709694
ABSTRACT:
An aircraft rudder command system for allowing a pilot to directly input a sideslip command for yaw-axis control through use of the rudder pedals is disclosed. The aircraft rudder command system includes a pedal input device for receiving a pedal input signal indicative of pilot rudder pedal input, a signal-receiving device for receiving feedback signals indicative of the current state of aircraft operation, a command generator system responsive to the pedal input signal and at least one of the feedback signals for generating a sideslip angle command, command limiting means for generating a limited sideslip angle command, and a feedback control system for transmitting a sideslip control rudder command to a rudder actuation system. The rudder actuation system causes the rudder to move in such a manner so as to produce an actual aircraft sideslip angle which follows the limited sideslip angle command. The aircraft rudder command system may also include a sideslip estimator. The sideslip estimator includes a component for receiving an airmass sideslip signal, a sideslip rate estimator for generating a sideslip rate estimate signal, and a complementary filter for synthesizing a sideslip angle estimate signal from the airmass sideslip signal and the sideslip rate estimate signal. The rudder actuation system, in turn, causes the rudder to move in such a manner so as to cause the sideslip angle estimate signal to follow the limited sideslip angle command.
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Bidwell Anne E.
Peters Jr. Joseph F.
The Boeing Company
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