Combined offset gearbox arrangement for hybrid-electric powerplant

A propulsion system for an aircraft, the propulsion system comprising:

• an engine comprising a first input shaft;
• and
• a drivetrain coupled to the first input shaft, the drivetrain comprising an output shaft, a reduction gear assembly, and an electric motor,
• the reduction gear assembly comprising at least a main gear, a first offset gear, and a bevel ring gear, the main gear being mounted to the output shaft, the bevel ring gear being integrated on a face of the main gear, the first offset gear being coupled to the first input shaft, and the main gear, the bevel ring gear, and the output shaft being rotatable about a first rotational axis, and
• the electric motor comprising a rotor rotatable about a second rotational axis, the second rotational axis being perpendicular to the first rotational axis, and the rotor being coupled to the bevel ring gear.

A propulsion system for an aircraft, the propulsion system comprising:

• an engine comprising an input shaft;
• a drivetrain coupled to the input shaft, the drivetrain comprising an output shaft, a gear assembly, and an electric motor,
• the gear assembly comprising a main gear mounted to the output shaft, and a bevel ring gear integrated on a face of the main gear, wherein the main gear, the bevel ring gear, and the output shaft are rotatable about a first rotational axis, and
• the electric motor comprising a rotor rotatable about a second rotational axis, wherein the second rotational axis is perpendicular to the first rotational axis, and the rotor is coupled to the bevel ring gear;
• and
• a propeller control unit (PCU) mounted on the output shaft.