An aircraft actuation system is disclosed that includes a pair of cylinders, a piston movably disposed in each cylinder, and a roller train that extends between the pistons in the two cylinders. A portion of the roller train is disposed beyond the cylinders to engage a pinion. Movement of the pistons in the two cylinders in opposite directions produces a corresponding movement of the roller train to in turn rotate the pinion. The roller train may be maintained in compression between its two ends by fluid pressure exerted on a common face of each of the pistons in the two cylinders. The cylinders may be disposed in non-colinear relation, including in parallel relation to one another. A guide may be used to maintain rollers of the roller train in a proper orientation for entry into a space between an outer race and the pinion.

A steering apparatus may comprise a steering collar, a first linear actuator, a first drive gear, a crankshaft, and a sun gear, wherein the sun gear is disposed within the collar, wherein the first drive gear is fixed to the crankshaft and coupled to the sun gear such that the collar rotates about the sun gear in response to rotation of the crankshaft, wherein the first linear actuator is coupled between the crankshaft and the collar.

A steering apparatus may comprise a steering collar, a first linear actuator, a first drive gear, a crankshaft, and a sun gear, wherein the sun gear is disposed within the collar, wherein the first drive gear is fixed to the crankshaft and coupled to the sun gear such that the collar rotates about the sun gear in response to rotation of the crankshaft, wherein the first linear actuator is coupled between the crankshaft and the collar.

A steering apparatus may comprise a strut cylinder, a steering collar, a first linear actuator, a first drive gear, a crankshaft, and a ring gear. The ring gear may be coupled to the steering collar. The first drive gear may be fixed to the crankshaft and coupled to the ring gear such that the steering collar rotates in response to rotation of the crank shaft. The first linear actuator may be coupled between the crankshaft and the strut cylinder.

A steering apparatus may comprise a strut cylinder, a steering collar, a first linear actuator, a first drive gear, a crankshaft, and a ring gear. The ring gear may be coupled to the steering collar. The first drive gear may be fixed to the crankshaft and coupled to the ring gear such that the steering collar rotates in response to rotation of the crank shaft. The first linear actuator may be coupled between the crankshaft and the strut cylinder.

The invention relates to a method for controlling the torque of a drive device (1) for rotating wheels (2) of an aircraft comprising actuators for selectively driving rotating wheels of the aircraft to ensure its movement on the ground, comprising the step of regulating a torque generated by the drive device according to a torque setpoint (4) issued by the pilot. According to the invention, the method involves the step of generating, as long as the torque setpoint is not sufficient to guarantee a stable movement speed of the aircraft, a replacement torque setpoint (5) to allow the aircraft to move at a stable speed, and substituting the replacement torque setpoint for the torque setpoint generated by the pilot.

Systems and methods for minimizing an aircraft turn radius are disclosed. For example, a method to minimize an aircraft turn radius may include receiving an activation signal from an activation switch. The activation switch may be configured allow a selected turn. The method may also include receiving a turn command in a direction of the selected turn. The method may also include transmitting a turn signal to an actuator operatively coupled to a nosewheel assembly. The actuator may rotate a shaft in the direction of the selected turn to move at least one nosewheel from a first angle to a second angle with reference to a longitudinal axis of the aircraft. The method may also include transmitting a thrust signal to at least one of a plurality of thrust-producing devices operatively coupled to a first wing and a second wing operatively coupled to the aircraft.

Systems and methods for minimizing an aircraft turn radius are disclosed. For example, a method to minimize an aircraft turn radius may include receiving an activation signal from an activation switch. The activation switch may be configured allow a selected turn. The method may also include receiving a turn command in a direction of the selected turn. The method may also include transmitting a turn signal to an actuator operatively coupled to a nosewheel assembly. The actuator may rotate a shaft in the direction of the selected turn to move at least one nosewheel from a first angle to a second angle with reference to a longitudinal axis of the aircraft. The method may also include transmitting a thrust signal to at least one of a plurality of thrust-producing devices operatively coupled to a first wing and a second wing operatively coupled to the aircraft.

A feedback system senses a steering position of a nose wheel assembly for an aircraft. The nose wheel assembly has a first element rotatably associated with a second element about an axis, and the rotational position of the first element relative to the second element corresponds to the steering position of the nose wheel assembly. The feedback system includes a first magnetic field sensor fixedly positioned relative to the first element and configured to sense a first element orientation. A second magnetic field sensor is fixedly positioned relative to the second element and configured to sense a second element orientation. The feedback system further includes a controller programmed to determine the steering position of the nose wheel according to the sensed first element orientation and the sensed second element orientation.

A feedback system senses a steering position of a nose wheel assembly for an aircraft. The nose wheel assembly has a first element rotatably associated with a second element about an axis, and the rotational position of the first element relative to the second element corresponds to the steering position of the nose wheel assembly. The feedback system includes a first magnetic field sensor fixedly positioned relative to the first element and configured to sense a first element orientation. A second magnetic field sensor is fixedly positioned relative to the second element and configured to sense a second element orientation. The feedback system further includes a controller programmed to determine the steering position of the nose wheel according to the sensed first element orientation and the sensed second element orientation.