Systems and methods for tilt propellers with tilt actuator gearbox and integrated inverter

A tilt apparatus of an aircraft, comprising:

• a first frame;
• a second frame moveably coupled to the first frame;
• a propulsion system mounted to the second frame and configured to move with the second frame, the propulsion system comprising:
• a propeller;
• a motor configured to rotate the propeller, and
• a propulsion inverter configured to supply current to the motor;
• a tilt actuation system mounted to the second frame and configured to tilt with the second frame with respect to the first frame, the tilt actuation system comprising:
• a tilt actuator linearly aligned with a body of the second frame;
• and
• a tilt actuator inverter configured to supply current to the tilt actuator,
• wherein the tilt actuator is configured to tilt the second frame with respect to the first frame.

An aircraft, comprising:

• a boom;
• a first frame coupled to the boom;
• a second frame moveably coupled to the first frame;
• a propulsion system mounted to the second frame and configured to move with the second frame, the propulsion system comprising:
• a propeller;
• a motor configured to rotate the propeller, and
• a propulsion inverter configured to supply current to the motor;
• a tilt actuation system mounted to the second frame and configured to tilt with the second frame with respect to the first frame, the tilt actuation system comprising:
• a tilt actuator linearly aligned with a body of the second frame;
• and
• a tilt actuator inverter configured to supply current to the tilt actuator,
• wherein the tilt actuator is configured to tilt the second frame with respect to the first frame.