The present invention provides an engine of a vertical take-off and landing aircraft, wherein the engine is configured to be movable with respect to an aircraft component of the aircraft between a hover position for take-off and landing, and a cruise position for forward flight, wherein the engine comprises an aerodynamic component having at least one aerodynamic element movable between a first position and a second position the aerodynamic element defining an aerodynamic surface in contact with an airstream passing through the engine.

The present invention provides an engine of a vertical take-off and landing aircraft, wherein the engine is configured to be movable with respect to an aircraft component of the aircraft between a hover position for take-off and landing, and a cruise position for forward flight, wherein the engine comprises an aerodynamic component having at least one aerodynamic element movable between a first position and a second position the aerodynamic element defining an aerodynamic surface in contact with an airstream passing through the engine.

Presented are a method and apparatus for an aircraft flight surface actuation system including a motor having an output shaft. A gearbox is coupled with the output shaft, whereby a first driving force output via the motor is converted to a second driving force. A torque shaft assembly is driveably coupled with the gearbox. The torque shaft assembly includes a first tube, a second tube located at least partially through the first tube and located coaxial therewith, wherein the first tube comprises an axial preload operable to mitigate lateral deflection, and wherein the first tube comprises a torsional preload operable to mitigate torsional deflection. In addition, the aircraft flight surface actuation system includes an eccentric cam mechanism driveably coupled with the torque shaft assembly, and a flight surface coupled with the eccentric cam mechanism.

Presented are a method and apparatus for an aircraft flight surface actuation system including a motor having an output shaft. A gearbox is coupled with the output shaft, whereby a first driving force output via the motor is converted to a second driving force. A torque shaft assembly is driveably coupled with the gearbox. The torque shaft assembly includes a first tube, a second tube located at least partially through the first tube and located coaxial therewith, wherein the first tube comprises an axial preload operable to mitigate lateral deflection, and wherein the first tube comprises a torsional preload operable to mitigate torsional deflection. In addition, the aircraft flight surface actuation system includes an eccentric cam mechanism driveably coupled with the torque shaft assembly, and a flight surface coupled with the eccentric cam mechanism.

A system and method for preventing back-drive in a braking system for a rotary actuator. The braking system comprises a housing and split cam design. A driving cam located within the housing is associated with an upstream side of the braking system. The driving cam is configured to rotate when a torque is applied to the upstream side. The braking system has a wedging cam and a plurality of cylindrical rollers. The wedging cam located within the housing and is associated with a downstream side of the braking system. The wedging cam is configured to react and prevent back-drive motion when torque is applied to the downstream side. The plurality of cylindrical rollers is positioned between the wedging cam and the housing. The plurality of cylindrical rollers is configured to wedge between a surface of the wedging cam and the housing when the torque is applied to the downstream side.

A system and method for preventing back-drive in a braking system for a rotary actuator. The braking system comprises a housing and split cam design. A driving cam located within the housing is associated with an upstream side of the braking system. The driving cam is configured to rotate when a torque is applied to the upstream side. The braking system has a wedging cam and a plurality of cylindrical rollers. The wedging cam located within the housing and is associated with a downstream side of the braking system. The wedging cam is configured to react and prevent back-drive motion when torque is applied to the downstream side. The plurality of cylindrical rollers is positioned between the wedging cam and the housing. The plurality of cylindrical rollers is configured to wedge between a surface of the wedging cam and the housing when the torque is applied to the downstream side.

A rotary actuator, including a manifold block and a rotor assembly that includes a rotor shaft and a plurality of arcuate pistons attached to the rotor shaft, each arcuate piston curving at a set radial distance from the rotor shaft, and each piston attached to the rotor shaft via a crank arm. A pressure chamber assembly coupled to the manifold block defines a plurality of piston pressure chambers that receive and at least partially enclose each arcuate piston, including a plurality of gland seals disposed adjacent the entrance of each piston pressure chamber to create a seal between the inner surface of the pressure chamber and the outer surface of the arcuate piston. Each gland seal includes an inner seal that engages the piston surface of the arcuate piston, and plural outer seals that engage the inner surface of the piston pressure chamber, forming a hydraulic seal.

A rotary actuator, including a manifold block and a rotor assembly that includes a rotor shaft and a plurality of arcuate pistons attached to the rotor shaft, each arcuate piston curving at a set radial distance from the rotor shaft, and each piston attached to the rotor shaft via a crank arm. A pressure chamber assembly coupled to the manifold block defines a plurality of piston pressure chambers that receive and at least partially enclose each arcuate piston, including a plurality of gland seals disposed adjacent the entrance of each piston pressure chamber to create a seal between the inner surface of the pressure chamber and the outer surface of the arcuate piston. Each gland seal includes an inner seal that engages the piston surface of the arcuate piston, and plural outer seals that engage the inner surface of the piston pressure chamber, forming a hydraulic seal.

A wing for an aircraft includes a main wing, slat, and connection assembly movably connecting the slat to the main wing, wherein the slat is movable between a retracted position and an extended position. The connection assembly includes a guide rail and an elongate slat track extending along a track longitudinal axis between front and rear ends, the front end of the slat track fixedly mounted to the slat. A first roller unit is mounted to the rear end of the slat track engaging the guide rail. A roller bearing includes a second roller unit mounted to the main wing and engaging an engagement surface of the slat track. The slat track includes a slot extending through the slat track along the track longitudinal axis. The second roller unit includes a first roller element and a second roller element mounted on one common shaft for common rotation, and the common shaft proceeds through the slot.

A wing for an aircraft includes a main wing, slat, and connection assembly movably connecting the slat to the main wing, wherein the slat is movable between a retracted position and an extended position. The connection assembly includes a guide rail and an elongate slat track extending along a track longitudinal axis between front and rear ends, the front end of the slat track fixedly mounted to the slat. A first roller unit is mounted to the rear end of the slat track engaging the guide rail. A roller bearing includes a second roller unit mounted to the main wing and engaging an engagement surface of the slat track. The slat track includes a slot extending through the slat track along the track longitudinal axis. The second roller unit includes a first roller element and a second roller element mounted on one common shaft for common rotation, and the common shaft proceeds through the slot.