A flight controller of a flight vehicle includes an electric motor control unit for controlling each of a plurality of electric motors, and in a case where the plurality of electric motors are driven by electric power stored in a battery or in a case where the battery is charged with electric power generated by a generator, the electric motor control unit controls the plurality of electric motors in accordance with the state of the battery.

A flight controller of a flight vehicle includes an electric motor control unit for controlling each of a plurality of electric motors, and in a case where the plurality of electric motors are driven by electric power stored in a battery or in a case where the battery is charged with electric power generated by a generator, the electric motor control unit controls the plurality of electric motors in accordance with the state of the battery.

In one embodiment of the present disclosure, there is provided an aircraft gearbox including a gear and a gear shrouding for providing lubrication to the gear. The gear shrouding is disposed around the gear, has an inner surface facing the gear and an opposing outer surface facing away from the gear, and includes a channel formed along at least a portion of the gear shrouding between the inner surface and the outer surface of the gear shrouding, an input orifice extending to the channel, wherein the input orifice is at a first position on the channel, and an output orifice extending to the channel, wherein the output orifice is at a second position on the channel different from the first position. In another embodiment, the gear shrouding further includes a second output orifice at a third position on the channel different from the first and second positions.

In one embodiment of the present disclosure, there is provided an aircraft gearbox including a gear and a gear shrouding for providing lubrication to the gear. The gear shrouding is disposed around the gear, has an inner surface facing the gear and an opposing outer surface facing away from the gear, and includes a channel formed along at least a portion of the gear shrouding between the inner surface and the outer surface of the gear shrouding, an input orifice extending to the channel, wherein the input orifice is at a first position on the channel, and an output orifice extending to the channel, wherein the output orifice is at a second position on the channel different from the first position. In another embodiment, the gear shrouding further includes a second output orifice at a third position on the channel different from the first and second positions.

In one embodiment of the present disclosure, there is provided a drive tube and swashplate trunnion assembly. The drive tube and swashplate trunnion assembly includes a drive tube having a plurality of grooves formed on an outer surface of the drive tube; a swashplate trunnion having a plurality of grooves formed on an inner surface of the swashplate trunnion, wherein individual grooves of the plurality of grooves on the swashplate trunnion mate with individual grooves of the plurality of grooves on the drive tube to form a plurality of channels; and a plurality of cylindrical bearings, wherein each of said cylindrical bearings is disposed within an individual channel of the plurality of channels.

In one embodiment of the present disclosure, there is provided a drive tube and swashplate trunnion assembly. The drive tube and swashplate trunnion assembly includes a drive tube having a plurality of grooves formed on an outer surface of the drive tube; a swashplate trunnion having a plurality of grooves formed on an inner surface of the swashplate trunnion, wherein individual grooves of the plurality of grooves on the swashplate trunnion mate with individual grooves of the plurality of grooves on the drive tube to form a plurality of channels; and a plurality of cylindrical bearings, wherein each of said cylindrical bearings is disposed within an individual channel of the plurality of channels.

An aircraft has an airframe with first and second wings having first and second pylons extending therebetween. A distributed propulsion system attached to the airframe includes at least first, second, third and fourth propulsion assemblies that are independently controlled by a flight control system. A pod assembly is coupled to the airframe. In a VTOL flight mode, the first and second propulsion assemblies are forward of the pod assembly and the third and fourth propulsion assemblies are aft of the pod assembly. In a forward flight mode, the first and second propulsion assemblies are below the pod assembly and the third and fourth propulsion assemblies are above the pod assembly. In both the VTOL and forward flight modes, the first and fourth propulsion assemblies generate thrust having a first direction while the second and third propulsion assemblies generate thrust having a second direction that is different from the first direction.

An aircraft has an airframe with first and second wings having first and second pylons extending therebetween. A distributed propulsion system attached to the airframe includes at least first, second, third and fourth propulsion assemblies that are independently controlled by a flight control system. A pod assembly is coupled to the airframe. In a VTOL flight mode, the first and second propulsion assemblies are forward of the pod assembly and the third and fourth propulsion assemblies are aft of the pod assembly. In a forward flight mode, the first and second propulsion assemblies are below the pod assembly and the third and fourth propulsion assemblies are above the pod assembly. In both the VTOL and forward flight modes, the first and fourth propulsion assemblies generate thrust having a first direction while the second and third propulsion assemblies generate thrust having a second direction that is different from the first direction.

In some examples, an aircraft gearbox comprises a housing, a barrier, a rotatable drive system component, a set of gears, and a lubrication system. The barrier separates a first compartment and a second compartment within the housing. Each of the rotatable drive system component and the set of gears operable to rotate based on torque received from an engine. The rotatable drive system component is located in the first compartment. The set of gears is located in the second compartment. The lubrication system comprises a first lubrication subsystem and a second lubrication subsystem, which are, at least in part, independent from one another. The first lubrication subsystem is operable to lubricate the rotatable drive system component in the first compartment. The second lubrication subsystem is operable to lubricate the set of gears in the second compartment. The barrier inhibits lubricant from passing between the first compartment and the second compartment.

In some examples, an aircraft gearbox comprises a housing, a barrier, a rotatable drive system component, a set of gears, and a lubrication system. The barrier separates a first compartment and a second compartment within the housing. Each of the rotatable drive system component and the set of gears operable to rotate based on torque received from an engine. The rotatable drive system component is located in the first compartment. The set of gears is located in the second compartment. The lubrication system comprises a first lubrication subsystem and a second lubrication subsystem, which are, at least in part, independent from one another. The first lubrication subsystem is operable to lubricate the rotatable drive system component in the first compartment. The second lubrication subsystem is operable to lubricate the set of gears in the second compartment. The barrier inhibits lubricant from passing between the first compartment and the second compartment.