Control systems (20) for a rotorcraft (1) are provided, the rotorcraft (1) including main rotor (5) and auxiliary propulsor assemblies (6). the main rotor assembly (1) including first (50) and second (51) rotors disposed to oppositely rotate relative to an airframe (2) about a same rotational axis (RA), and sensors (30) disposed to generate hub moment, tip clearance and lift offset data of the main rotor assembly (5).
CONTROL SYSTEMS FOR COAXIAL ROTORCRAFT
STEUERUNGSSYSTEME FÜR KOAXIALEN DREHFLÜGLER
SYSTÈMES DE COMMANDE POUR GIRAVION COAXIAL
03.04.2019
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
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