Aircraft capable of vertical takeoff and landing, hovering, and efficient forward flight are described. An aircraft includes two side mounted tiltable proprotors and a central rotor disposed above the proprotors. The proprotors are tiltable between at least a horizontal position for forward flight and a vertical position for vertical or hovering flight. The central rotor may be powered for vertical and transitional flight modes and may turn by free autorotation during forward flight. The proprotors may be differentially tilted during vertical or hovering flight to counter torque effects of the central rotor. The central rotor may be foldable and/or easily detachable from the aircraft to facilitate storage and transportation. Left and right proprotors may provide both forward thrust and attitude control. Control inputs to left and right proprotors may be connected directly to an autopilot creating closed loop actuation using motor RPM feedback.

A propeller-type propulsion system for aircraft comprising a propeller, a plurality of electric motors and a gearbox. The gearbox has an output shaft onto which the propeller is mechanically coupled, and has an input shaft onto which the plurality of electric motors is mechanically coupled, the input shaft being off-center with respect to the output shaft. All of the electric motors are mechanically coupled one after the other along the input shaft such that the electric motors are at least partially integrated into a space, on the opposite side of the gearbox from the propeller, that is left free owing to the input shaft and the output shaft being off-center with respect to one another. As a result, the diameter of the propulsion system, in a plane perpendicular to the axis of rotation of the propeller, is reduced. This improves the aerodynamics and the fuel consumption of the aircraft.

A propeller-type propulsion system for aircraft comprising a propeller, a plurality of electric motors and a gearbox. The gearbox has an output shaft onto which the propeller is mechanically coupled, and has an input shaft onto which the plurality of electric motors is mechanically coupled, the input shaft being off-center with respect to the output shaft. All of the electric motors are mechanically coupled one after the other along the input shaft such that the electric motors are at least partially integrated into a space, on the opposite side of the gearbox from the propeller, that is left free owing to the input shaft and the output shaft being off-center with respect to one another. As a result, the diameter of the propulsion system, in a plane perpendicular to the axis of rotation of the propeller, is reduced. This improves the aerodynamics and the fuel consumption of the aircraft.

A turbine engine assembly includes: a fan assembly; a turbine coupled to the fan assembly through a gearbox; a stationary component; and an assembly extending between the gearbox and the stationary component to couple the gearbox to the stationary component, wherein the assembly includes at least one vibration-reducing mechanism configured to isolate a vibratory response of the gearbox from the stationary component.

A turbine engine assembly includes: a fan assembly; a turbine coupled to the fan assembly through a gearbox; a stationary component; and an assembly extending between the gearbox and the stationary component to couple the gearbox to the stationary component, wherein the assembly includes at least one vibration-reducing mechanism configured to isolate a vibratory response of the gearbox from the stationary component.

An exemplary dual motor input includes a common shaft for coupling to a member to be rotationally driven, a first motor rotationally coupled to a first drive shaft, the first drive shaft coupled to the common shaft, and a second motor rotationally coupled to a second drive shaft, the second drive shaft coupled to the common shaft.

An aircraft of a modular type including: at least one rotor suitable for providing in full or in part propulsion and/or lift for the aircraft; at least one power plant of the combustion engine type or of the electric motor type; a main gearbox, for mechanically transmitting drive torque generated by the at least one power plant to the at least one rotor; and an avionics system for assisting in piloting the aircraft. In accordance with the invention, the avionics system is configured for automatically providing the assistance in piloting the aircraft when the aircraft has a first power plant only or when the aircraft has a first power plant and a second power plant.

An aircraft of a modular type including: at least one rotor suitable for providing in full or in part propulsion and/or lift for the aircraft; at least one power plant of the combustion engine type or of the electric motor type; a main gearbox, for mechanically transmitting drive torque generated by the at least one power plant to the at least one rotor; and an avionics system for assisting in piloting the aircraft. In accordance with the invention, the avionics system is configured for automatically providing the assistance in piloting the aircraft when the aircraft has a first power plant only or when the aircraft has a first power plant and a second power plant.

The disclosure is directed to parallel hybrid drive assemblies for lightweight unmanned aerial vehicles (UAVs). Specifically, the disclosure is directed to hybrid drive assemblies and control systems for UAVs, utilizing continuous belt tension modulation to couple and decouple an electric motor and an internal combustion engine. In some embodiments, this is achieved through the use of a tensioner module that is configured to couple and decouple the electric motor and the internal combustion engine by continuously and selectably modulating belt tension on drive elements of each of the electric motor and the internal combustion engine.

The disclosure is directed to parallel hybrid drive assemblies for lightweight unmanned aerial vehicles (UAVs). Specifically, the disclosure is directed to hybrid drive assemblies and control systems for UAVs, utilizing continuous belt tension modulation to couple and decouple an electric motor and an internal combustion engine. In some embodiments, this is achieved through the use of a tensioner module that is configured to couple and decouple the electric motor and the internal combustion engine by continuously and selectably modulating belt tension on drive elements of each of the electric motor and the internal combustion engine.