An actuator for driving a rotatable component includes a first, rotating member comprising a screw and a second member comprising a nut threaded to said screw, wherein rotation of said first member causes axial movement of said first or second member. The component also includes a third member coupled to the second member, wherein axial movement of said first or second member causes axial movement of said third member and a fourth, rotating member coupled to said third member and connectable to said component. The system also includes a bearing system located between said third member and said fourth member, said bearing system configured to cause said fourth member to rotate upon said axial movement of said third member so as to drive said component.

An aircraft control surface deployment system for an aircraft structure, that can be a spoiler deployment system for an aircraft wing, includes a cam body, an actuator, and a coupling mechanism. The actuator moves the cam body such that it raises and lowers the aircraft control surface. The actuator is connected to the cam body via the coupling mechanism. The coupling mechanism has a first portion connected to the cam body and a second portion connected to the actuator, configured such that the coupling mechanism allows some free relative movement and rotation of the first and second portions. Loads transverse to the axis of movement of the actuator, resulting from relative movement of the cam body, are not transferred to the actuator.

An aircraft control surface deployment system for an aircraft structure, that can be a spoiler deployment system for an aircraft wing, includes a cam body, an actuator, and a coupling mechanism. The actuator moves the cam body such that it raises and lowers the aircraft control surface. The actuator is connected to the cam body via the coupling mechanism. The coupling mechanism has a first portion connected to the cam body and a second portion connected to the actuator, configured such that the coupling mechanism allows some free relative movement and rotation of the first and second portions. Loads transverse to the axis of movement of the actuator, resulting from relative movement of the cam body, are not transferred to the actuator.

Wing assemblies comprise a three-position Krueger flap and an actuation assembly that comprises a drive linkage assembly, a primary linkage assembly coupled between the drive linkage assembly and the three-position Krueger flap, and a secondary linkage assembly. The primary linkage assembly comprises a dual linkage that is pivotally and translationally coupled relative to a wing support structure. The secondary linkage assembly comprises a cam, a follower, and a dual-linkage axle that is coupled to the follower and to the dual linkage and that defines a dual-linkage pivot axis of the dual linkage.

Wing assemblies comprise a three-position Krueger flap and an actuation assembly that comprises a drive linkage assembly, a primary linkage assembly coupled between the drive linkage assembly and the three-position Krueger flap, and a secondary linkage assembly. The primary linkage assembly comprises a dual linkage that is pivotally and translationally coupled relative to a wing support structure. The secondary linkage assembly comprises a cam, a follower, and a dual-linkage axle that is coupled to the follower and to the dual linkage and that defines a dual-linkage pivot axis of the dual linkage.

A drive assembly for driving a movable flow body of an aircraft comprises an electric motor having a two sets of independent windings, two motor control electronics units coupled with the windings and a control computer, two actuators couplable with a first or second section of the flow body, a first and a second transmission shaft, wherein the transmission shafts each have a first and a second end, wherein the electric motor is coupled with the first ends of the transmission shafts, wherein the second ends of the transmission shafts are coupled with the respective actuator, and wherein the drive assembly is designed to selectively move and hold the movable flow body into a plurality of extended positions and a retracted position relative to a fixed structural component of the aircraft by selectively moving and holding the first actuator and the second actuator.

An actuation system for a component has a plurality of cylinders. A piston is in operable communication with each of the cylinders and is configured to move at least a portion of the component to a desired position. A plurality of pumps are in fluidic communication with the plurality of cylinders, and are each driven by electric motors. The number of pumps is less than a number of cylinders.

An actuator includes an end fitting, a ball screw connected to the end fitting, a ball nut engaged with the ball screw, a rod disposed at least partially within the ball screw, and a rotating member engaged with the rod. A method of verifying an actuator may include rotating a manual input portion in a first direction under substantially no load until the manual input portion stops, rotating the manual input portion in a second, opposite direction until a first torque is measured, determining a first rotational angle at which the first torque was measured, rotating the manual input portion in the first direction until a second torque is measured, determining a second rotational angle at which the second torque was measured, and verifying a second load path if a backlash is within a predetermined range.

An actuator includes an end fitting, a ball screw connected to the end fitting, a ball nut engaged with the ball screw, a rod disposed at least partially within the ball screw, and a rotating member engaged with the rod. A method of verifying an actuator may include rotating a manual input portion in a first direction under substantially no load until the manual input portion stops, rotating the manual input portion in a second, opposite direction until a first torque is measured, determining a first rotational angle at which the first torque was measured, rotating the manual input portion in the first direction until a second torque is measured, determining a second rotational angle at which the second torque was measured, and verifying a second load path if a backlash is within a predetermined range.

In order to provide a track drive device for an aircraft that has zero backlash, a large gear reduction, the ability to self-lock, and a better load transfer and reduced wear, the track drive device drives a track member through a drive device that has at least one drive unit that is arranged adjacent to the track member. Each drive unit comprises a plurality of engaging members that are driven by a cam shaft or a cam gear such that the engaging members are sequentially shifted in a wave-like pattern which results in the track member being moved in a linear manner relative to the drive device along a longitudinal direction.