A method of counteracting a rotor moment of one or more rotors of a concentric dual-rotor helicopter (10) includes sensing angular velocity and angular acceleration of a helicopter during a flight maneuver. The angular velocity and angular acceleration are compared to a set of control parameters and one or more control servos change the cyclic pitch of the one or more rotors (12a,12b) to counteract the rotor moment. A control system for counteracting a rotor moment of one or more rotors (12a,12b) of a concentric dual-rotor helicopter (10) includes one or more sensors configured to sense angular velocity and angular acceleration of a helicopter during a flight maneuver. A computer (42) is operably connected to the one or more sensors (44) and configured to compare sensor data to a set of control parameters. A plurality of control servos change the cyclic pitch of the one or more rotors (12a,12b) to counteract the rotor moment.
Moment limiting control laws for dual rigid rotor helicopters
Momentenbegrenzungssteuerungsgesetze für Hubschrauber mit zwei starren Rotoren
Règles de contrôle de limitation du moment pour hélicoptères à double rotor rigide
2018-08-22
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
Moment limiting control laws for dual rigid rotor helicopters
Europäisches Patentamt | 2018
|"Integrating Active Rotor Control into Helicopters"
British Library Conference Proceedings | 2000
|Control Systems for Single-Rotor Helicopters
NTIS | 1971
|