An adaptive flight control system for controlling the pitch of blades of a propulsive propeller of a hybrid helicopter as a function of the return value of the pitch. The adaptive flight control system comprises control means supplying the pitch control order, a piloting member controlling variation of the pitch, and piloting means applying a control gain in order to transform the control order into a setpoint, and transmitting the setpoint to the piloting member. The piloting means include information return means applying a return gain that is variable to the return value of the variation of the pitch to the piloting means, also modifying the control gain as a function of the return value.
ADAPTIVE FLIGHT CONTROL SYSTEM FOR THE YAW AND THRUST FLIGHT CONTROLS OF A HYBRID HELICOPTER
2017-05-25
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
Adaptive flight control system for the yaw and thrust flight controls of a hybrid helicopter
Europäisches Patentamt | 2019
|Europäisches Patentamt | 2018
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