A multirotor aircraft (101) comprises at least three proprotors (114-117). Each proprotor has a plurality of rotor blades (118-121) pivotably attached to a mast assembly. When a rotor blade pitch angle is changed for a proprotor, all rotor blades on the proprotor change to a same pitch angle. The proprotors are configured to spin freely when a power source is disengaged or fails. In various embodiments, one or more engines provides power to each proprotor, or at least one engine provides power to two or more proprotors. A rotor blade control system (300) is configured to control a collective rotor blade pitch angle on each proprotor independently of the rotor blade pitch on the other proprotors. The rotor blade control system is configured to set a negative collective rotor blade pitch angle on an unpowered proprotor, such as in response to manual inputs by a pilot or in response to current engine conditions.
MULTIROTOR AIRCRAFT WITH COLLECTIVE FOR AUTOROTATION
MEHRROTORFLUGZEUG MIT KOLLEKTIV FÜR AUTOROTATION
AÉRONEF À MULTIROTOR COMPORTANT UN COLLECTIF POUR AUTOROTATION
2020-06-03
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |