Abstract: A work machine comprises an armrest and a user control operable by the user to control tool or machine functions when the user's arm rests on the armrest. An armrest sensor is configured to sense the presence of the user's arm and to disable the control when the user's arm is removed from the armrest. The control may be mounted on the armrest and the armrest movable between enabling and disabling positions by the weight of the user's arm. A seat sensor may be configured to disable the control when the user leaves the seated position.

Abstract: A crane controller for controlling travel movements of a crane, in particular a portal crane. The crane controller includes control electronics and at least one input device, connected to the control electronics, having a grip part, a main axis of the grip part is swivellable together with the grip part in at least two swivel directions oriented, in particular orthogonally, in relation to one another, and the control electronics are able to generate electrical signals, for actuating at least one actuator of the crane, on the basis of an adjustment of the grip part relative to an original position of the grip part. The grip part has its main axis additionally displaceable in at least two, preferably three, different displacement directions relative to the original position and/or is rotatable about the main axis, and the control electronics generate electrical signals for actuating the at least one actuator of the crane.

Abstract: The working machine includes an operator seat, an armrest arranged adjacent to the operator seat, an operation lever arranged in front of the armrest, and a jug dial arranged adjacent to the operation lever. The jog dial is arranged on a position allowing an operator seated on the operator seat to operate the operation lever and the jog dial with an arm placed on the armrest.

Abstract: The invention relates to a force application device for an aircraft control stick comprising: —a casing (24), —an electromagnet (22) mounted on the casing (24), —an actuator (30) mounted on the shaft (13), the actuator (30) being mobile in translation in relation to the shaft (13) along the axis (A), the actuator (30) comprising a magnetic material, and —a coupling device comprising an input gear (40) that is mounted so as to be stationary in relation to the casing (24) and an output gear (50) connected to the actuator (30) by means of an attachment part (60), the attachment part (60) being configured so as to allow a limited angular displacement between the output gear (50) and the shaft (13) around the axis (A) and to allow the actuator (30) of the output gear (50) to translate along the axis (A).

Abstract: A controller having a joystick which can be moved in three dimensions is disclosed. The joystick is connected by a Y (yaw) link which is, in turn, connected to a P (pitch) link, which is, in turn connected to an R (roll) link. The R link is rotatable about a fixed-position mounting base. Alternately, the joystick is connected by an R (roll) link which is, in turn, connected to a P (pitch) link, which is, in turn connected to an Y (yaw) link. The Y link is rotatable about a fixed-position mounting base. In either of these manners, one can rotate a joystick around any of three axes. When used to control a vehicle, rotation around the yaw and roll axes can steer (with one being more fine-tuned steering), and rotation around the pitch axis can control acceleration and deceleration.

Abstract: A controller having a joystick which can be moved in three dimensions is disclosed. The joystick is connected by a Y (yaw) link which is, in turn, connected to a P (pitch) link, which is, in turn connected to an R (roll) link. The R link is rotatable about a fixed-position mounting base. In this manner, one can rotate a joystick around any of three axes. When used to control a vehicle, rotation around the yaw and roll axes can steer (with yaw being more fine-tuned steering), and rotation around the pitch axis can control acceleration and deceleration. A starting or center position for each link can be defined, and the further a link is rotated and/or force increases on tires being steered from this central position, the more resistance is applied, in embodiments of the disclosed technology.

Abstract: A piloting system having a control stick configured to control the aircraft with respect to its three piloting axes, namely the pitch axis, the roll axis and the yaw axis, and an auxiliary control device configured to automatically control the aircraft during one of the following phases: a landing phase and a takeoff phase. The auxiliary control device automatically controls the aircraft with respect to at least one of the piloting axes, and the other piloting axes, which are not controlled automatically by the auxiliary control device, then being controlled manually by a pilot with the aid of the control stick.

Abstract: The invention relates to a joystick (1) for controlling an aircraft, including a frame (2), a lever (3), a mechanical linking assembly (4) for connecting the lever to the frame enabling a rotation of the lever (3) relative to the frame (2) about a first rotation axis (X), in which the mechanical linking assembly (4) includes a first pivot joint (9), the first pivot joint (9) including a first portion, a second portion movably mounted relative to the first portion, and at least two flexible blades, each flexible blade having an end that is attached to the first portion and another end that is attached to the second portion, and being resiliently deformable in order to enable a rotation of the second portion relative to the first portion along the first rotation axis (X) and to generate a return torque which hinders the rotation of the second portion relative to the first portion.

Abstract: A system and method for illuminating one or more sidestick controllers within a cockpit of an aircraft is described. In some embodiments, the system includes a sidestick controller having lighting components that display lighting behaviors representing the movement and/or control of an aircraft. In some embodiments, the system illuminates various different lighting components on a sidestick controller based on information received from aircraft control systems, cockpit lighting systems, and other systems associated with an aircraft.

Abstract: A multi-axis serially redundant, single channel, multi-path fly-by-wire control system comprising: serially redundant flight control computers in a single channel where only one “primary” flight control computer is active and controlling at any given time; a matrix of parallel flight control surface controllers including stabilizer motor control units (SMCU) and actuator electronics control modules (AECM) define multiple control paths within the single channel, each implemented with dissimilar hardware and which each control the movement of a distributed set of flight control surfaces on the aircraft in response to flight control surface commands of the primary flight control computer; and a set of (pilot and co-pilot) controls and aircraft surface/reference/navigation sensors and systems which provide input to a primary flight control computer and are used to generate the flight control surface commands to control the aircraft in flight in accordance with the control law algorithms implemented in the flight

Abstract: Input/steering mechanisms and aircraft control systems are provided. In an embodiment, by way of example only, an input/steering mechanism is provided for use with an aircraft control system. The input/steering mechanism includes a yoke that includes a hub, an alphanumeric keyboard, and a first grip surface. The alphanumeric keyboard is disposed on a face of the hub and is adapted to receive a manual input from a user and to transmit an output signal to the aircraft control system in response to the manual input. The first grip surface is formed on an outer periphery of the hub and is contoured to correspond with one or more fingers of the user, the first grip surface is formed such that a thumb of the user is positioned to rest in proximity to at least a portion of the alphanumeric keyboard when the one or more fingers grip the first grip surface.

Abstract: An aircraft flight control (10) includes a control stick (11) with a handle (14) and a root (13) that are interconnected by an intermediate segment (12) of the control stick (11). The flight control (10) includes a pitch shaft (20) and a roll shaft (30) that are mutually perpendicular, the control stick (11) passing through an oblong orifice (21) formed in the pitch shaft (20), the root (13) being mechanically connected to the roll shaft (30) by a mechanical connection (40), while the intermediate segment (12) is connected to the pitch shaft (20) via a connection pin (70) that passes through the intermediate segment (12) and that is arranged axially in the oblong orifice (21).

Abstract: An aircraft flight control system advantageously is provided with a control rod which is spline-connected to a bearing assembly so as to permit simultaneous independent longitudinal and rotational movements of the control rod while isolating such movements from one another (e.g., so as to allow operative interconnection to an aircraft's aileron and elevator control surfaces). Thus, the control rod is moveable in longitudinal and rotational directions relative to a longitudinal axis of the control rod in response to pitch and roll command inputs, respectively. The control rod is splined operatively to the bearing assembly so as to allow for independent simultaneous longitudinal and rotational movements of the control rod relative to the longitudinal axis thereof to thereby allow the command inputs to be transferred to the aircraft's respective flight control surfaces.

Abstract: A method and apparatus for a control system for an aircraft. The control system comprises a grip, a set of feedback components connected to the grip, and a set of sensors. The set of feedback components transmit a restoring force opposite to a movement of the grip. The set of sensors are capable of detecting pitch input, roll input, and yaw input in response to the movement of the grip.

Abstract: A vertical take off and land (VTOL) jet aircraft may have a jet engine mounted in a forward portion of the aircraft. A thrust deflection assembly may be provided rearward of the jet engine, and include a cascade and control box for deflecting thrust during vertical flight of the aircraft. By manipulating the cascade and control box, the roll, yaw and pitch of the aircraft during vertical flight may be controlled. In addition, ailerons, a rudder and elevators may be provided for controlling roll, yaw and pitch during forward flight. A pilot control input apparatus is also provided, which receives pilot input regarding desired roll, yaw and pitch of the aircraft. The pilot control input is operatively associated with a control mixer, which controls the control box, ailerons, rudder and elevators in accordance with the desired roll, yaw and pitch of the aircraft. As a result, the pilot uses the same control input apparatus for vertical and forward flight.

Abstract: An integrated side stick controller combines air speed, turning and altitude changing rate control into one pilot input control device. Movements of the integrated side stick controller will perform manipulations on aircraft surfaces devices in order to maneuver the aircraft. For instance, fore and aft movement of the side stick will increase/decrease the air speed, left/right movements of the side stick will control the turning of the aircraft, and up/down movements of the slider on the side stick will change the ascend/descend rate of the aircraft.

Abstract: A vertical take off and land (VTOL) jet aircraft may have a jet engine mounted in a forward portion of the aircraft. A thrust deflection assembly may be provided rearward of the jet engine, and include a cascade and control box for deflecting thrust during vertical flight of the aircraft. By manipulating the cascade and control box, the roll, yaw and pitch of the aircraft during vertical flight may be controlled. In addition, ailerons, a rudder and elevators may be provided for controlling roll, yaw and pitch during forward flight. A pilot control input apparatus is also provided, which receives pilot input regarding desired roll, yaw and pitch of the aircraft. The pilot control input is operatively associated with a control mixer, which controls the control box, ailerons, rudder and elevators in accordance with the desired roll, yaw and pitch of the aircraft. As a result, the pilot uses the same control input apparatus for vertical and forward flight.

Abstract: A dual-seat control system for an aircraft provides an upright mounted at one end to pivot by actuation of a user near the other end. Cross beams extend from the upper end of the upright to positions in front of each user. The cross beams each carry a handle at an outboard end by which an operator can move the upright as a control stick in either a pitch-control direction, or a roll-control direction. The cross beams are free to move in one degree of freedom with respect to the upright, and are fixed in the other degree of freedom. Typically, the handle is attached in a manner to move in rigid body motion with respect to the upright in a pitch-control direction, while being free to move in a plane defined by the cross beam and upright at will, according to the desires of an operator. In certain embodiments, the handle may be required to be parallel to the upright in all positions, from a lower stowed position to an upper deployed position.

Abstract: A computer interface device includes a gimbal mounted handle having a plurality of input members for effectively communicating navigation and command signals to a computer. This invention provides a user with six degrees of freedom for navigation within a virtual reality world while simultaneously enabling a user to enter a series of commands in order to effectively communicate a user's intentions to a computer to effect a change within a virtual reality world.

Abstract: Asymmetrical mechanical linkages for sidestick roll controllers located at the pilot and copilot stations of aircraft and other vehicles with fly-by-wire control systems. The asymmetrical character of the linkage reduces the level of exertion required to rotatably displace the sidestick in the outboard direction and, as an important consequence, significantly reduces pilot fatigue.

Abstract: Device for the control of the elements of a machine having a stick (6,7) designed to be activated by one hand of an operator and mounted tilting around at least one axis (X--X) transverse to the stick. The stick is associated with at least one position sensor (17) which deliver an electric signal representing the tilting of the stick around said axis on both sides of a neutral position, the electric signal controlling at least one of the elements of the machine by a calculation device (30). The device also includes at least one torque motor (12,13) associated to said axis (X--X) so that the tilting of the stick (6,70 drives a relative rotation between the rotor and the stator of the torque motor and in that the torque motor is fed by the calculation device (30).

Abstract: Device for controlling elements of a machine, comprising a stick intended to be actuated by a single hand of an operator and mounted for tilting about at least one axis transversal to said stick, said stick being associated with at least one position sensor and delivering an electric signal representative of tilting of said stick about said axis, on each side of a neutral position, said electric signal controlling at least one actuator which controls at least one of said elements of the machine. This device is characterized in that said stick is mounted for rotation on itself about its longitudinal axis and in that it comprises at least one other position sensor delivering another electric signal representative of rotation of said stick about itself, on each side of a neutral position, said other electric signal controlling at least one other actuator which controls at least one other element of said machine.

Abstract: A two-axis hand controller including a human interface to simulate feel parameters for use in a vehicle having a pitch axis and a roll axis. A hollow grip having a base end is connected to a swash plate through a rigid connecting member. A universal joint having a center shaft member rigidly affixed to a first support surface and having roll and pitch pivot axis members is attached within the center of the hollow grip so as to provide dual palm pivot points. The swash plate includes an opening positioned so as to accept the shaft member through the opening and into the hollow grip. The swash plate is also flexibly engaged to the first support surface so as to allow for control of the human interface feel parameters. Apparatus for transducing is attached between the swash plate and the base so as to provide electrical signals responsive to movements in the pitch and roll axes without cross-coupling from one axis to the other.

Abstract: A five or six degree of freedom device which includes a two or three degree of freedom wrist action hand controller and in which additional degrees of freedom are provided by motion of an operator's forearm connected to a mounting member that carries or supports the wrist action hand controller.

Abstract: A three or four degree of freedom device which includes a two or three degree of freedom wrist action hand controller and in which the additional degree of freedom control is provided by motion of an operator's forearm connected to a mounting member that carries or supports the wrist action hand controller.

Abstract: A single-stick control system for helicopters, by which at least four different flight control functions of piloting the craft--cyclic, collective with simultaneous engine throttling, independent throttling for one or more engines and including immediate transition to emergency autorotation--may be performed by the manipulation of the single stick by one and the same hand of the pilot.

Abstract: A controller for producing electrical control signals has a relatively stationary supporting section providing an upwardly facing hand supporting surface and an upward projection, and has a stick-like control section mounted on a first gimbal joint on top of the projection, to swing about pitch and roll axes. A second gimbal joint is spaced along the roll axis from the first one and rotates about said roll axis and about a gimbal axis parallel to the pitch axis. A gimbal ring of the first joint is rigidly connected to a gimbal member of the second joint for unison rotation about the roll axis. A second gimbal member of the second joint is caused to rotate about said gimbal axis in unison with swinging of the control section about the pitch axis by a linkage connection between them. A signal generator for each of the pitch and roll axes and a stick force generating means for each of those axes are connected with respective gimbal members of the second joint.

Abstract: An ultralight aircraft has a single stick three-axis aerodynamic control, twin engined power control, wing- and tail-mounted ailerons, an inverted V-tail and wide span wings with upturned tips.