Patent ID: 11858632
Assignee: PARALLEL FLIGHT TECHNOLOGIES, INC.
Field: Transport (Mechanical engineering)
Classification: CPC B  F | IPC B

Claim 4:
5. The system of claim 1, further comprising:
an output shaft coupling the internal-combustion engine to the rotor;
a clutch interposed between the output shaft and the motor output and configured to selectively transfer torque between the output shaft and the motor output;
a clutch actuator coupled to the clutch;
a first angular position sensor coupled to the output shaft;
a second angular position sensor coupled to an output side of the clutch;
a battery powering the primary electric motor; and
wherein the local controller is further configured to, during normal flight operation:
trigger the clutch actuator to disengage the clutch;
deactivate the internal-combustion engine when a state of charge of the battery exceeds a target battery state of charge or when noise generated by the aerial vehicle exceeds a noise limit or upon failure of the internal-combustion engine;
calculate an angular clutch actuator trigger position; and
trigger the clutch actuator to engage the clutch when a clutch output reaches the angular clutch actuator trigger position.