A rotor blade pitch actuator has a first and second motor configured to control the rotor blade pitch. An actuator control system is configured to drive the first and second motor such that backlash is either eliminated from the system or minimized to an acceptable level.
Anti-Backlash Flight Control Actuator System
27.06.2024
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
Europäisches Patentamt | 2020
|Backlash measurement system for an electromechanical actuator
Europäisches Patentamt | 2023
|NTIS | 1979
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