A force sensor, flexible sensing element, and method for the force sensor are disclosed. The force sensor uses a flexible sense element with two flexible arms dedicated to measuring strain related to a pitch force and two flexible arms dedicated to measuring strain related to roll force. The use of two channels for each measurement provides a command lane and a monitor lane for strain measurements. Strain gauges are disposed on both the top and the bottom surfaces of each arm, thus providing two completely redundant systems. When a failure is detected in one of the systems, the redundant system can be implemented.

A transducer switch includes a housing, a pushbutton switch near the rear of the housing, an input shaft extending from the front of the housing such that an input force can be applied to the input shaft, a positioning spring adapted and configured to resist movement of the input shaft and bias the input shaft towards alignment with the central axis, and a plurality of strain gauges positioned on a sensing portion of the input shaft. The plurality of strain gauges are adapted and configured to measure tension and compression on at least two sides of the input shaft, the two sides separated by approximately ninety degrees.

Provided are embodiments of control devices capable of simultaneously measuring six degrees of freedom and electronic systems comprising the control devices. In some embodiments, the control devices are useful for controlling and/or directing movement of vehicles and virtual entities through operation of the control device with a computer processor, computer interface and, optionally a display.

An operation lever includes: a pair of rods disposed at point-symmetrical positions with respect to an operation axis; magnets disposed on the respective rods; and a pair of magnetic sensors disposed at line-symmetrical positions with respect to a second straight line perpendicular to a first straight line connecting centers of one of the rods and the other rod, on a plane perpendicular to the operation axis.

Plinth system (1) for a control stick (51) for controlling an aircraft having a plinth flange (3) includes a tubular receiving means (7) and a plinth nut (5) which at least partially encloses the receiving means of the plinth flange (3), wherein the plinth nut (5) comprises an interface (11) for fastening a knurled nut (41).

A haptic interface with at least two degrees of freedom including at least one element for interacting with a user, at least two passive brakes each extending along an axis, each of the brakes being capable of exerting a resistive force about its axis, the forces being controllable, measurement means for measuring a position of the element for interacting with a user, detection means for detecting the force applied on the element for interacting with the user, a control unit capable of sending commands to the brakes depending on information on the position of the element for interacting with the user and on the force applied on the element for interacting with the user, such that said passive brakes generate resistive forces according to at least one given haptic pattern.

A force sensor, flexible sensing element, and method for the force sensor are disclosed. The force sensor uses a flexible sense element with two flexible arms dedicated to measuring strain related to a pitch force and two flexible arms dedicated to measuring strain related to roll force. The use of two channels for each measurement provides a command lane and a monitor lane for strain measurements. Strain gauges are disposed on both the top and the bottom surfaces of each arm, thus providing two completely redundant systems. When a failure is detected in one of the systems, the redundant system can be implemented.

A work vehicle includes a hydraulic actuator, a control valve, a pressure sensing unit, a force imparting component, and a controller. The hydraulic actuator varies a steering angle. The control valve controls flow of fluid supplied to the hydraulic actuator. The operation member is configured to be operated by an operator and to control the control valve when varying the steering angle. The pressure sensing unit senses a pressure produced by the hydraulic actuator. The force imparting component imparts an assisting force or a counterforce to operation of the operation member. The controller controls the force imparting component so as to generate resistance to operation of the operation member based on a pressure value sensed by the pressure sensing unit.

A sensor (102) for detecting input force includes a housing (103) having a cavity (201) and a contact element (105) which is enclosed in the cavity. The contact element and cavity provide a substantially flush profile along their respective surfaces (104, 106). The cavity includes a wall (301, 302, 303) having a sensing device (304) attached thereto and the contact element provides a physical contact between the contact element and the sensing device on application of a mechanical interaction to the surface of the contact element.

A flight control device of an aircraft including a support, an action member attached to the support rotating freely around a primary axis, a rotary device including a stator, rotatably connected to the support around a secondary axis, and a rotor rotating freely relative to the stator around the secondary axis, the rotary device applying a force sensing torque on the rotor relative to the stator around the secondary axis, and a mechanical reducing gear, which connects, with a reduction ratio, rotation of the action member with rotation of the rotor, the mechanical reducing gear including a screw-nut system with rolling elements, including a screw, attached to the rotor, connected in rotation to the rotor around the secondary axis, and a nut fixed in rotation around the secondary axis relative to the stator and helically connected with the screw around and along the secondary axis via the rolling elements.