An actuator system for a flight control surface of an aerial vehicle includes a shaft. The shaft includes at least one roller to rotate with the shaft and a plunger. The at least one roller includes a plurality of roller threads. The actuator system includes an inverted nut defining an inner bore including a plurality of nut threads. The inverted nut is coupled about the shaft such that the plurality of nut threads are to engage with the plurality of roller threads to move the inverted nut relative to the shaft. The inverted nut includes a source of a lubricant in fluid communication with the inner bore and the plunger is to be received within the inner bore to supply the lubricant to the at least one roller.

An actuator system for a flight control surface of an aerial vehicle includes a shaft. The shaft includes at least one roller to rotate with the shaft and a plunger. The at least one roller includes a plurality of roller threads. The actuator system includes an inverted nut defining an inner bore including a plurality of nut threads. The inverted nut is coupled about the shaft such that the plurality of nut threads are to engage with the plurality of roller threads to move the inverted nut relative to the shaft. The inverted nut includes a source of a lubricant in fluid communication with the inner bore and the plunger is to be received within the inner bore to supply the lubricant to the at least one roller.

An actuator system for a flight control surface of an aerial vehicle includes a shaft. The shaft includes at least one roller to rotate with the shaft and a plunger. The at least one roller includes a plurality of roller threads. The actuator system includes an inverted nut defining an inner bore including a plurality of nut threads. The inverted nut is coupled about the shaft such that the plurality of nut threads are to engage with the plurality of roller threads to move the inverted nut relative to the shaft. The inverted nut includes a source of a lubricant in fluid communication with the inner bore and the plunger is to be received within the inner bore to supply the lubricant to the at least one roller.

An actuator system for a flight control surface of an aerial vehicle includes a shaft. The shaft includes at least one roller to rotate with the shaft and a plunger. The at least one roller includes a plurality of roller threads. The actuator system includes an inverted nut defining an inner bore including a plurality of nut threads. The inverted nut is coupled about the shaft such that the plurality of nut threads are to engage with the plurality of roller threads to move the inverted nut relative to the shaft. The inverted nut includes a source of a lubricant in fluid communication with the inner bore and the plunger is to be received within the inner bore to supply the lubricant to the at least one roller.

A method, apparatus, and computer program product for managing movement of a flight control surface on an aircraft. A control signal is received to move the flight control surface to a position. Travel in a number of actuators in a plurality of actuators coupled to the flight control surface is limited to an amount that reduces a load on the number of actuators in the plurality of actuators in response to receiving the control signal while the aircraft is on the ground and the speed of the aircraft is less than a threshold.

A flywheel is provided in combination with a hybrid machine, wherein said flywheel comprises, in a radial direction, from inward to outward, an inner turbine, an intermediate compressor, and an outer array of magnets. The turbine cooperates with said hybrid machine to spin faster when said machine decelerates, and slower when said machine accelerates. An inner turbine drives both said intermediate compressor and said hybrid machine. The outer array of magnets is driven by said hybrid machine to accelerate the flywheel to accelerate the flywheel during braking of said hybrid machine. Said hybrid machine communicates with said flywheel to house it and render energy from it, in a hybrid manner such that energy is stored in a pressure or electrical storage mode, or both pressure and electrical storage mode, to effect a regenerative mode that attains low fuel consumption.

A system and method for actuating one or more high-lift flight control surfaces of an aircraft are disclosed. The system comprises actuators operatively coupled between a driveline and one or more high-lift flight control surfaces associated with a wing of the aircraft. The actuators are configured to cause actuation of the one or more first high-lift flight control surfaces in response to being driven by the first driveline. Each actuator is associated with a no-back device configured to prevent an air load on the one or more high-lift flight control surfaces from driving the one or more high-lift flight control surfaces. The system also comprises a backup brake applicable to the driveline. The backup brake can be applied upon the identification of a developing unsafe condition such as an asymmetry condition between the flight control surfaces of each wing of the aircraft or an uncommanded movement the flight control surfaces.

A system and method for actuating one or more high-lift flight control surfaces of an aircraft are disclosed. The system comprises actuators operatively coupled between a driveline and one or more high-lift flight control surfaces associated with a wing of the aircraft. The actuators are configured to cause actuation of the one or more first high-lift flight control surfaces in response to being driven by the first driveline. Each actuator is associated with a no-back device configured to prevent an air load on the one or more high-lift flight control surfaces from driving the one or more high-lift flight control surfaces. The system also comprises a backup brake applicable to the driveline. The backup brake can be applied upon the identification of a developing unsafe condition such as an asymmetry condition between the flight control surfaces of each wing of the aircraft or an uncommanded movement the flight control surfaces.

A flight management system is modified so that it can deal with an unpredicted current event happening to an airplane based on non-standard maneuvers that have been carried out previously by other airplanes in similar circumstances. This allows the flight management system to adaptively or dynamically respond to a variety of flight path changes rather than rely solely on a set of fixed responses to predictable events during a flight. Specifically, the flight management system is configured to provide procedural recommendations to a flight crew in real time based on collaboratively filtered historical data such that the flight crew can make smarter choices while operating airplanes.

Embodiments relate to an aircraft control router for an aircraft. The aircraft control router may include a command processing module, sensor validation module, aircraft state estimation module, and control laws module. The command processing module may be configured to generate aircraft trajectory values based on received aircraft control inputs. The sensor validation module may be configured to validate sensor signals generated by sensors of the aircraft. The aircraft state estimation module may be configured to determine an estimated aircraft state of the aircraft based on the validated sensor signals. The control laws module may be configured to generate actuator commands for actuators of the aircraft to adjust control surfaces of the aircraft, where the generated actuator commands are based on aircraft trajectory values, validated sensor signals, and an estimated aircraft state. The aircraft control router may transmit the generated actuator commands to actuators of the aircraft.