Aircraft electric motors are described. The electric motors include an annular rotor sleeve having an inner wall, a connecting wall, and an outer wall, wherein the inner wall, the connecting wall, and the outer wall define a U-shaped channel configured to receive a U-shaped magnet structure and a sleeve inner cavity defined radially inward from the inner wall, a hub connector extending radially inward from the inner wall into the sleeve inner cavity, a hub arranged in the sleeve inner cavity and fixedly connected to the hub connector, wherein the hub is configured to rotate with rotation of the rotor sleeve, and a U-shaped magnet structure arranged within the U-shaped channel of the rotor sleeve. At least one of the rotor sleeve, the hub connector, and the hub are formed from a composite material.

A gas turbine engine includes an inlet duct that is formed with a generally elliptical shape. The inlet duct includes a vertical centerline and a fan section that has an axis of rotation. The axis of rotation is spaced from the vertical centerline and is disposed within an inlet duct orifice.

A gas turbine engine includes an inlet duct that is formed with a generally elliptical shape. The inlet duct includes a vertical centerline and a fan section that has an axis of rotation. The axis of rotation is spaced from the vertical centerline and is disposed within an inlet duct orifice.

A bracket comprising a first planar portion having at least one bolt hole, a second planar portion angularly spaced apart from the first planar portion. The bracket may include an intermediate portion integral with the first planar portion and the second planar portion. The second planar portion includes projections and bolt holes, the projections are operable to interlock with cut-outs of flanges.

A bracket comprising a first planar portion having at least one bolt hole, a second planar portion angularly spaced apart from the first planar portion. The bracket may include an intermediate portion integral with the first planar portion and the second planar portion. The second planar portion includes projections and bolt holes, the projections are operable to interlock with cut-outs of flanges.

A quadrotor UAV including ruggedized, integral-battery, load-bearing body, two arms on the load-bearing body, each arm having two rotors, a control module mounted on the load-bearing body, a payload module mounted on the control module, and skids configured as landing gear. The two arms are replaceable with arms having wheels for ground vehicle use, with arms having floats and props for water-surface use, and with arms having pitch-controlled props for underwater use. The control module is configured to operate as an unmanned aerial vehicle, an unmanned ground vehicle, an unmanned (water) surface vehicle, and an unmanned underwater vehicle, depending on the type of arms that are attached.

A quadrotor UAV including ruggedized, integral-battery, load-bearing body, two arms on the load-bearing body, each arm having two rotors, a control module mounted on the load-bearing body, a payload module mounted on the control module, and skids configured as landing gear. The two arms are replaceable with arms having wheels for ground vehicle use, with arms having floats and props for water-surface use, and with arms having pitch-controlled props for underwater use. The control module is configured to operate as an unmanned aerial vehicle, an unmanned ground vehicle, an unmanned (water) surface vehicle, and an unmanned underwater vehicle, depending on the type of arms that are attached.

A health monitoring system including an array of microphones, a data collection system, and analytic software used to detect health status, pending malfunctions, or faults of several disparate, engine subsystems. The system can be used to monitor health of the main engines, the engine nacelles, and auxiliary power units (APU) on the aircraft.

A rear engine attachment system for an aircraft engine. The attachment system has an engine pylon with a lower spar having a lower surface, and a rear engine attachment having a beam fixed against the lower surface and to which a pair of rods is fixed. Each rod is fixed to the beam by at least one first connection point and to the engine by at least one second connection point. The beam includes front and rear fittings, and an intermediate fitting with a shoe and an intermediate clevis. The shoe presses against the lower surface. The front fitting presses against the intermediate fitting at the front and the rear fitting presses against the intermediate fitting at the rear. The fixing to the lower spar is ensured by bolts, each passing through the front base or the rear base, the shoe and the lower spar.

The present disclosure relates to the manufacture of battery packs/assemblies and more specifically, the manufacture of battery packs/assemblies for use in aircraft. A lightweight battery assembly with cell compression and/or pressure management system is disclosed herein. The cell compression and/or pressure management system can employ a sealed container housing a volatile vapor. The sealed container can be positioned within the battery enclosure and configured to impart a force to compress the cell-stack.