Aeronautics and astronautics – Aircraft control
Patent
1991-05-31
1992-08-04
Peters, Jr., Joseph F.
Aeronautics and astronautics
Aircraft control
244 90R, 244195, B64C 510
Patent
active
051351862
ABSTRACT:
A flutter control system of an aircraft wing comprising an actuator mounted on the aircraft wing to control a control surface, flight control command unit for outputting an actuation command signal for actuating the actuator, wing-displacement measurement unit for measuring an actual displacement of a predetermined point on the wing and outputting an actual displacement signal corresponding to the measured actual displacement, normal-wing-displacement prediction unit for predicting a normal displacement of the wing during normal flight in which no disturbance occurs, on the basis of the actuation command signal and of an information signal representing information about atmospheric density, flight speed and actuation position of the actuator and for outputting a predicted normal displacement signal representing the predicted displacement during the normal flight, disturbance-component estimation unit for receiving the actual displacement signal and the predicted normal displacement signal and for outputting a difference signal between these signals, and command-signal correction unit for correcting the actuation command signal so that a wing displacement by disturbance is cancelled out, on the basis of the difference signal.
REFERENCES:
patent: 2514138 (1950-07-01), O'Connor
patent: 3734432 (1973-05-01), Low
patent: 3781627 (1973-12-01), Binnig et al.
patent: 4479620 (1984-10-01), Rogers et al.
patent: 4562546 (1985-12-01), Wykes et al.
patent: 4615497 (1986-10-01), Seeler et al.
patent: 4796192 (1989-01-01), Lewis
Mojica Virna Lissi
Peters Jr. Joseph F.
Teijin Seiki Co. Ltd.
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