An aircraft (10) has a fuselage (28), a first rotor assembly (36) having a first rotor hub (38) and first rotor blades (40a, 40b, 40c) pivotably coupled to the first rotor hub (38) and a second rotor assembly (56) having a second rotor hub (58) and second rotor blades (60a, 60b, 60c) pivotably coupled to the second rotor hub (58). The first (40a, 40b, 40c) and second (60a, 60b, 60c) rotor blades have deployed configurations extending generally radially from the fuselage (28) and stowed configurations extending generally parallel with the fuselage (28). A sequencing cam (90), positioned between the first (38) and second (58) rotor hubs, is coupled to the second rotor blades (60a, 60b, 60c). The sequencing cam (90) has a retracted orientation when the second rotor blades (60a, 60b, 60c) are in the stowed configuration and an extended orientation when the second rotor blades (60a, 60b, 60c) are in the deployed configuration in which the sequencing cam (90) props support arms (42a, 42b, 42c) of the first rotor blades (40a, 40b, 40c) preventing transition of the first rotor blades (40a, 40b, 40c) from the deployed configuration to the stowed configuration.
ROTOR SEQUENCING FOR DUAL ROTOR AIRCRAFT
ROTORSEQUENZIERUNG FUER DOPPELROTORFLUGZEUG
SÉQUENÇAGE DE ROTOR POUR AÉRONEF À ROTOR DOUBLE
2018-09-26
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |