An aircraft having a high efficiency forward flight mode. The aircraft includes an airframe having at least one wing. A distributed propulsion system is attached to the airframe and includes a first plurality of propulsion assemblies and a second plurality of propulsion assemblies. A flight control system is operably associated with the distributed propulsion system and is operable to independently control each of the propulsion assemblies. The aircraft is configured for thrust-borne lift in a vertical takeoff and landing flight mode and wing-borne lift in the forward flight mode. In the vertical takeoff and landing flight mode, each of the propulsion assemblies is configured to generate vertical thrust. In the forward flight mode, the propulsion assemblies of the first plurality of propulsion assemblies are configured to generate forward thrust and the propulsion assemblies of the second plurality of propulsion assemblies are configured to shut down.

An aircraft having a high efficiency forward flight mode. The aircraft includes an airframe having at least one wing. A distributed propulsion system is attached to the airframe and includes a first plurality of propulsion assemblies and a second plurality of propulsion assemblies. A flight control system is operably associated with the distributed propulsion system and is operable to independently control each of the propulsion assemblies. The aircraft is configured for thrust-borne lift in a vertical takeoff and landing flight mode and wing-borne lift in the forward flight mode. In the vertical takeoff and landing flight mode, each of the propulsion assemblies is configured to generate vertical thrust. In the forward flight mode, the propulsion assemblies of the first plurality of propulsion assemblies are configured to generate forward thrust and the propulsion assemblies of the second plurality of propulsion assemblies are configured to shut down.

A hydraulic propulsion system is disclosed which includes an input interface configured to receive mechanical power from a power source, a pressure source comprising one or more fixed or variable displacement pumps coupled to the input interface and adaptable to convert mechanical power to hydraulic power and controlling outlet pressure of the pressure source (system pressure), one or more variable displacement motors coupled to the pressure source via a corresponding high-pressure line configured to be mechanically coupled to one or more aerodynamic rotors of an aircraft and comprising a closed loop speed control arrangement in response to a commanded rotor speed, and a controller configured to control the speed of one or more variable displacement motors by providing a control signal for controlling the system pressure.

The invention relates to a device having: —a circuit carrier board (3) and—a conductor element (2), which is designed to transfer an electric current from and/or to the circuit carrier board (3), characterized by: —an electrically conductive, elastically deformable, contoured, plate-like connection element (1), which connects the circuit carrier plate (3) to the conductor element (2) and is designed to create a local, dynamic resilience, as a result of which a force transmission (F) from the conductor element (2) to the circuit carrier plate (3) can be reduced, and—a plate thickness of the connection element (1) of at least 2 cm. The invention also relates to a power converter (4) and an aircraft (6) having such a device.

The invention relates to a device having: —a circuit carrier board (3) and—a conductor element (2), which is designed to transfer an electric current from and/or to the circuit carrier board (3), characterized by: —an electrically conductive, elastically deformable, contoured, plate-like connection element (1), which connects the circuit carrier plate (3) to the conductor element (2) and is designed to create a local, dynamic resilience, as a result of which a force transmission (F) from the conductor element (2) to the circuit carrier plate (3) can be reduced, and—a plate thickness of the connection element (1) of at least 2 cm. The invention also relates to a power converter (4) and an aircraft (6) having such a device.

A door roller includes a carriage member comprising a plurality of bores, and a plurality of roller assemblies connected to the carriage member, each roller assembly of the plurality of roller assemblies including a pivot bearing rotatably disposed within a bore of the plurality of bores and a pair of rollers coupled to the pivot bearing. Each wheel assembly is configured to pivot relative to the carriage member.

An epicyclic gear train of an aircraft powerplant is provided. The epicyclic gear train includes a sun gear having a rotation axis, a ring gear, a plurality of intermediate gears circumscribed by the ring gear and being meshed with the sun gear and with the ring gear, a carrier supporting the intermediate gears, and a torque frame attaching the carrier to a stationary structure of the aircraft powerplant to prevent rotation of the carrier and of the intermediate gears about the rotation axis of the sun gear. The torque frame is attached to the carrier at a connection. The torque frame and the carrier cooperatively define a lubricant passage extending through the connection and supplying lubricant to at least one of the intermediate gears.

An epicyclic gear train of an aircraft powerplant is provided. The epicyclic gear train includes a sun gear having a rotation axis, a ring gear, a plurality of intermediate gears circumscribed by the ring gear and being meshed with the sun gear and with the ring gear, a carrier supporting the intermediate gears, and a torque frame attaching the carrier to a stationary structure of the aircraft powerplant to prevent rotation of the carrier and of the intermediate gears about the rotation axis of the sun gear. The torque frame is attached to the carrier at a connection. The torque frame and the carrier cooperatively define a lubricant passage extending through the connection and supplying lubricant to at least one of the intermediate gears.

An epicyclic gear system includes an input sun gear configured to receive rotational input from a turbine of a turbo charger. A first set of planet gears is distributed around and meshes with the input sun gear. A carrier holds the first set of planet gears and defines a rotational axis about which the carrier rotates. A second set of planet gears is mounted to the carrier. An output sun gear is included, wherein the second set of planet gears are distributed around and mesh with the output sun. The output sun gear is configured to deliver rotational power to an internal combustion engine. The carrier is configured to selectively be driven by a variable speed drive to regulate output to the output sun over a range of input rotational speeds of the input sun gear.

An epicyclic gear system includes an input sun gear configured to receive rotational input from a turbine of a turbo charger. A first set of planet gears is distributed around and meshes with the input sun gear. A carrier holds the first set of planet gears and defines a rotational axis about which the carrier rotates. A second set of planet gears is mounted to the carrier. An output sun gear is included, wherein the second set of planet gears are distributed around and mesh with the output sun. The output sun gear is configured to deliver rotational power to an internal combustion engine. The carrier is configured to selectively be driven by a variable speed drive to regulate output to the output sun over a range of input rotational speeds of the input sun gear.