Systems and methods relate to a vertical takeoff and landing (VTOL) platform that can include a stator and a rotor magnetically levitated by the stator. The rotor and stator can be annular, such that the rotor rotates about a rotational axis. The stator can include magnets that provide guidance, levitation, and drive forces to drive the rotor, as well as to control operation of rotor blades of the rotor that can be independently rotated to specific pitch angles to control at least one of lift, pitch, roll, or yaw of the VTOL platform. Various controllers can be used to enable independent and redundant control of components of the VTOL platform.

A helicopter may include a hybrid engine system including an internal combustion engine (e.g., a turbine engine) and an electric engine. The internal combustion engine and the electric engine being coupled to the rotor system and configured to separately or collectively operate the rotor system in response to a triggering event. In one aspect, a method for operating a rotor system of a helicopter may include receiving an indicator of a triggering event and actuating a non-active engine, one of the internal combustion engine or the electric engine, in response to receiving the triggering event.

A helicopter may include a hybrid engine system including an internal combustion engine (e.g., a turbine engine) and an electric engine. The internal combustion engine and the electric engine being coupled to the rotor system and configured to separately or collectively operate the rotor system in response to a triggering event. In one aspect, a method for operating a rotor system of a helicopter may include receiving an indicator of a triggering event and actuating a non-active engine, one of the internal combustion engine or the electric engine, in response to receiving the triggering event.

A clutch arrangement for between an engine and a propeller of a drivetrain of a roadable aircraft. The arrangement includes an engine shaft, a propeller shaft, a stationary clutch arrangement housing, and an engagement member which is rotationally locked to and axially slidable relative to propeller shaft. The engagement member includes a first engagement structure for engaging a corresponding engagement structure associated with the engine shaft for setting the clutch arrangement in a propeller propulsion mode, in which rotational propulsion torque is transmitted from the engine shaft to the propeller shaft via the engagement member. The engagement member further includes a second engagement structure for engaging a corresponding engagement structure associated with the clutch arrangement housing for setting the clutch arrangement in a propeller locked mode, in which the propeller shaft is rotationally locked to the clutch arrangement housing by means of the engagement member.

A clutch arrangement for between an engine and a propeller of a drivetrain of a roadable aircraft. The arrangement includes an engine shaft, a propeller shaft, a stationary clutch arrangement housing, and an engagement member which is rotationally locked to and axially slidable relative to propeller shaft. The engagement member includes a first engagement structure for engaging a corresponding engagement structure associated with the engine shaft for setting the clutch arrangement in a propeller propulsion mode, in which rotational propulsion torque is transmitted from the engine shaft to the propeller shaft via the engagement member. The engagement member further includes a second engagement structure for engaging a corresponding engagement structure associated with the clutch arrangement housing for setting the clutch arrangement in a propeller locked mode, in which the propeller shaft is rotationally locked to the clutch arrangement housing by means of the engagement member.

One embodiment is an electric drive system including a plurality of redundant motors, wherein power generated by the plurality of motors is used to drive a rotor system comprising a rotor shaft having a plurality of rotor blades connected thereto via a swashplate; a gear box associated with the plurality of redundant motors; a cyclic actuation system for controlling an individual pitch of the rotor blades connected to the swashplate; and at least one structural element for retaining the redundant motors, the gear box, and the cyclic actuation system together as a single integrated unit.

One embodiment is an electric drive system including a plurality of redundant motors, wherein power generated by the plurality of motors is used to drive a rotor system comprising a rotor shaft having a plurality of rotor blades connected thereto via a swashplate; a gear box associated with the plurality of redundant motors; a cyclic actuation system for controlling an individual pitch of the rotor blades connected to the swashplate; and at least one structural element for retaining the redundant motors, the gear box, and the cyclic actuation system together as a single integrated unit.

A system and method of converting engines on a turboprop aircraft, including removing an existing engine and associated propeller from an aircraft fuselage, installing an engine mount adapter assembly to the fuselage, and installing a replacement engine to the engine mount adapter assembly, whereby at least some portions of the replacement engine are attached to the engine mount adapter assembly for structural support.

A system and method of converting engines on a turboprop aircraft, including removing an existing engine and associated propeller from an aircraft fuselage, installing an engine mount adapter assembly to the fuselage, and installing a replacement engine to the engine mount adapter assembly, whereby at least some portions of the replacement engine are attached to the engine mount adapter assembly for structural support.

Vertical takeoff and landing (VTOL) aircraft are provided with fixed-position port and starboard wings extending laterally from an elongate fuselage having an empennage at an aft end of the fuselage and a propeller to provide horizontal thrust to the aircraft in a direction of the longitudinal axis thereof. A series of port and starboard rotor units are provided, each of which includes axially opposed rotor blades, and a motor to rotate the rotor blades and provide vertical thrust to the aircraft. A logic control unit (LCU) controllably sets an angular position of the opposed rotor blades along a position axis relative to the longitudinal axis of the aircraft in response to determining an optimal position of the rotor blades during cruise flight operation to thereby minimize airflow disruption over the fixed-position wings.