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
2024-06-27
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
European Patent Office | 2020
|Backlash measurement system for an electromechanical actuator
European Patent Office | 2023
|NTIS | 1979
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