Abstract: 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.

Abstract: An aircraft inceptor system includes an inceptor member arranged to be operated by a user to cause a corresponding movement of a moveable aircraft surface. The system also includes means for detecting the operation of the inceptor member by the user and for providing a movement signal, associated with the detected operation, to a flight control computer, the flight control computer providing a control signal to an actuator to move the aircraft surface according to the movement signal. The means for detecting the operation of the inceptor member by the user comprises a force sensor configured to sense the force applied by the user to the inceptor member, the movement signal being derived based on the sensed force.

Abstract: Tail rotor control system is described for helicopters. A pedal position sensor operable by a pilot yields greater tail rotor RPM relative to the main rotor RPM, giving the pilot increased control over the vehicle. This proves especially useful in certain situations, such as high altitude, where increasing tail rotor speed from main rotor speed can give a pilot increased maneuverability and stability.

Abstract: A controller includes a first control member movable with one or two degree(s) of freedom (DoF) a second control member coupled to the first control member and movable with three independent DoFs and a third control member coupled to the first and the second control members, the third control member movable with one DoF, which is being one of the three DoFs of the second control member in the set, and providing a third control input, wherein the first, the second, and the third control members are configured to be operated by a user's single hand. Further, a forearm brace for attaching to a forearm of a user and a controller is used to support the user's forearm when the user operates the controller. Additionally, the controller includes vibration haptic motors for provide haptic alerts to the user based on position data and/or orientation data associated with a target object.

Abstract: The system and method for actuator monitoring of an electric aircraft is illustrated. The system includes a plurality of flight components, a computing device attached to each rotor component, and a flight controller. The plurality of flight components are coupled to the electric aircraft. A computing device is communicatively coupled to each rotor component and is configured to detect an input health datum associated with each rotor component of the plurality of flight components and transmit the input health datum to a flight controller. The flight controller is communicatively connected to the computing devices and is configured to receive the health datum from the computing devices, generate an updated health datum as a function of the input health datum, and transmit the updated health datum to each rotor component of the plurality of flight components.

Abstract: An aircraft includes an electronically controlled engine (ECE) and a first and a second throttle control assembly. The first throttle control assembly includes a first throttle fly button configured to command a FLY mode and a first throttle idle button configured to command an IDLE mode. The second throttle control assembly includes a second throttle fly button configured to command the FLY mode and a second throttle idle button configured to command the IDLE mode.

Abstract: An adaptive joystick preferably includes a rotatable cylinder bar, an outer base ring, an inner ring and an industrial joystick base. An adaptive controller receives an output from the adaptive joystick and outputs a control signal to a valve solenoid to control a hydraulic cylinder. Angle, depth and pressure sensors are preferably used to monitor a position of the hydraulic cylinder. The sensor outputs are fed into the adaptive controller. An inward wrist curl of the rotatable cylinder bar combined with a forearm pull rearward of the outer base ring are used to cause a digging motion. An outward wrist curl of the rotatable cylinder bar combined with a forearm push forward of the outer base ring are used to cause a dumping motion. A hand movement to the left is associated with swinging the excavator left. A hand movement to the right is associated to swinging the excavator right.

Abstract: A flight control handle suitable for being operated by a pilot, the flight control handle including a stick-forming grip carrying an end box that is provided with a hollow shell provided with a top face, at least one control projecting towards an external environment of the top face. The flight control handle has a controllable member suitable for being actuated by a person, the end box including at least one electronic wall incorporating an electronic circuit, the electronic circuit including at least one sensor that co-operates with the controllable member.

Abstract: A sensor for monitoring rotors includes a rotating shaft coupled to a set of rotor blades and a non-rotating tube at least partially disposed within the rotating shaft and coupled to the rotating shaft. The non-rotating tube includes a first end and a second end, a sensor mount disposed within the non-rotating tube proximate to the second end of the non-rotating tube. One or more sensors are attached to the sensor mount.

Abstract: A joystick having increased control functionality preferably includes an industrial joystick base and a rotary upper handle. The rotary upper handle preferably includes an outer base ring, a rotatable ring, a position sensor and a base portion. The outer base ring extends upward from the base portion. The base portion extends from the industrial joystick base. The rotatable ring is rotatably retained in an inner perimeter of the outer base ring. The position sensor is retained in a sensor cavity formed in an inner perimeter of the outer base ring. The rotatable ring preferably includes a ring portion, a rotatable cylinder bar and a compression spring. A center contact and a peripheral contact are retained in an end of the rotatable cylinder bar and make contact with the position sensor. The motion of the rotatable ring and the rotatable cylinder bar are sent to a ring controller for processing.

Abstract: An electric pedal control device for an aircraft, the device comprising several pedal transmission assemblies, each of the pedal transmission assemblies comprising an electric motor, an elastic connector, a transmission mechanism, an angular displacement sensor, and a pedal, wherein the angular displacement sensor is configured to acquire rotational position information about the pedal; transmission mechanism revolute pairs of the transmission mechanisms in the pedal transmission assemblies are connected via a mechanical connecting rod mechanism to effect linkage; and a controller of the electric pedal control device is configured to receive the rotational position information, and to control, according to the rotational position information, the electric motors to dampen the elastic connectors.

Abstract: A sensor for monitoring rotors includes a rotating shaft coupled to a set of rotor blades and a non-rotating tube at least partially disposed within the rotating shaft and coupled to the rotating shaft. The non-rotating tube includes a first end and a second end, a sensor mount disposed within the non-rotating tube proximate to the second end of the non-rotating tube. One or more sensors are attached to the sensor mount, wherein the one or more sensors detect one or more parameters associated with the rotating shaft or the set of rotor blades.

Abstract: A controller including a first control member, a second control member that extends from a portion of the first control member, and a third control member that moves in conjunction with, and in opposition to, a degree of freedom of the second control member. The third control member is configured to be operated by one or more of the non-index fingers of the user's hand. A controller processor is operable to produce a rotational movement output signal in response to movement of the first control member, and a translational movement output signal in response to movement of the second control member relative to the first control member. In exemplary embodiments, the first control member may be gripped and moved using a single hand, and the second control member may be moved using the thumb of the single hand.

Abstract: An aircraft hybrid flight control system comprising a manual control element, a mechanical transmission interposed between the manual control element and a control surface, an electromechanical actuator and a coupling unit configured to connect selectively the control surface to the mechanical transmission in a manual control mode and to the electromechanical actuator in a fly-by-wire control mode; the coupling unit is configured to maintain the mechanical transmission in a condition of substantial continuity with said control surface even in fly-by-wire mode, but for a freedom of relative motion of pre-set amplitude.

Abstract: A system and method for controlling a trajectory of a vehicle includes a crew seat with first and second inceptors mounted to a portion of the crew seat; a processor with memory having instructions stored thereon that cause the system to: receive signals indicative of a trajectory for the vehicle; receive signals indicative of a deviation in a trajectory of the vehicle; and transmit signals for controlling a flight path of the vehicle. A second inceptor is configured for selecting one or more menus on a user display and being configured to interact with a fly-by-wire control system for transmitting signals indicative of movement of flight surface of the vehicle. The crew seat is configured to be located on the vehicle, in a control station remotely located from the vehicle, or in a second vehicle remotely located from the vehicle.

Abstract: A magnetic spring input device is disclosed. In various embodiments, an input device as disclosed includes a manual input structure movably coupled to a base assembly; and a non-stationary magnet fixedly coupled to the manual input structure; a stationary magnet coupled to the base assembly in a manner that is fixed with respect to at least a first input axis of the input device, the stationary magnet being coupled to the base assembly with a first magnetic pole having a first magnetic polarity is oriented opposite a corresponding magnetic pole of the non-stationary magnet having the first magnetic polarity, in a position that is adjacent to but offset from the non-stationary magnet when the manual input structure is in a neutral position.

Abstract: In some embodiments, a protective apparatus for rotary control knobs may comprise a cover adapted fit over a rotary control knob; a knob cavity internal to the cover adapted to provide space for the rotary control knob to rotate about; and an access aperture located on the surface of cover member and adapted to provide limited user access to the rotary control knob. The cover member may be configured to encase or surround a control knob. The apparatus may further comprise a plate which may be integrally formed or molded to the cover and which contains a control shaft aperture adapted to receive the control shaft of a rotary control assembly. Once a control shaft is inserted through the control shaft aperture, a fastener may be secured to the control shaft over the plate, thereby securing the apparatus to the control shaft.

Abstract: A hydraulic device includes a body, a piston rod configured to be actuated by a pressurized hydraulic fluid, and a first drainage channel for externally draining an internal leakage of hydraulic fluid in the device. The device includes a second drainage channel for externally draining the internal leakage of hydraulic fluid in the device, the first and second channels being oriented in two different directions and each of the channels communicating at one of the ends thereof inside the body of the device.

Abstract: A control member (10) having a collective pitch lever (20) extending from a first end (21) to a second end (22). Said control member (10) has a handle (30) for controlling a yaw movement control device, said handle (30) being secured to an inner ring (40) that is guided to pivot about a second axis (AXLAC) by an outer ring (50) secured to said second end (22), said inner ring (40) being constrained to move together with said outer ring (50) and the lever (20) in pivoting about said first axis (AXCOL).

Abstract: According to one embodiment, a control assembly includes a post, a grip, and a hand rest. The post has a top, a bottom, and a body joining the top to the bottom. The grip is positioned at least partially above the post and is movable along at least one arc. The hand rest is coupled to the top and comprises an upper surface having a profile corresponding to the at least one arc.

Abstract: A reverse thrust detent system for an aircraft includes a throttle quadrant having an intermediate reverse thrust detent position, a reverse thrust scheduling system interfacing with the throttle quadrant, at least one aircraft engine interfacing with the reverse thrust scheduling system and a programmable input interfacing with the reverse thrust scheduling system and adapted to receive an engine reverse thrust setting. The reverse thrust scheduling system is adapted to operate the at least one aircraft engine according to the engine reverse thrust setting responsive to actuation of the intermediate reverse thrust detent position of the throttle quadrant. A reverse thrust detent method for an aircraft is also disclosed.

Abstract: A control system, in particular an aircraft flight control system, having a linkage with a force-transmission link (3), the link having a body (5) having at least one end housing (8) slidably receiving a coupling rod (9) for coupling the link to an adjacent element of the linkage, the housing being closed by an elastically-deformable test member (10) through which the rod passes and that has an inner periphery fastened to the rod and an outer periphery fastened to a wall defining the end housing, and the end housing receiving at least one sensor (11) for sensing relative movement between the rod and the body.

Abstract: An aircraft control apparatus, control system, and control method are disclosed. A control apparatus includes: a first control rod configured to have a movement in a first movement direction controlling a motion of an aircraft in a first motion direction, wherein after an external force on the first control rod in the first movement direction is removed, the first control rod automatically returns to a preset position in the first movement direction; wherein the preset position which the first control rod automatically returns to corresponds to the aircraft in the first motion direction maintaining a state of flight; wherein the maintaining state of flight depends on control signals received by the aircraft generated resulting from changes in the external force applied to the control rod in the first movement direction and state signals measured by state measurement sensors carried by the aircraft.

Abstract: A device for piloting includes a piloting member connected to at least one member for driving the craft, an electromechanical support box including, for each pivot connection, at least one actuating motor of the piloting member constituted of an electromagnetic actuator including a movable armature integrally formed with the piloting member and equipped with at least one permanent magnet having a magnetic moment parallel to the axis of the pivot connection, and an electromagnetic circuit including a fixed armature, arranged to allow the movable armature to move in the air gap zone, the magnetic moment of the movable armature sweeping each radial surface portion, and at least one coil winding which is dependent in position on the fixed armature and is capable of generating electromagnetic torque on the movable armature.

Abstract: A system and method for a controlling an aircraft with flight control surfaces that are controlled both manually and by a computing device is disclosed. The present invention improves overall flight control operation by reducing the mechanical flight control surface components while providing sufficient back-up control capability in the event of either a mechanical or power-related failure. Through the present invention, natural feedback is provided to the operator from the mechanical flight control surface which operates independent of computer-aided flight control surfaces.

Abstract: A wing flap sensor unit (2) having a position sensor (18) for detection of a rotation position of a shaft for operation of wing flaps and having a housing (4) which surrounds the position sensor (18), having an attachment component (20, 22) for attachment in an aircraft wing and having a connecting point (24) for an electrical connector of the position sensor (18). Hereby, the housing (4) is at least partially manufactured from titanium using a precision-casting method. The titanium precision-casting method makes it possible to achieve a particularly robust and lightweight housing.

Abstract: A flight control system includes a controller which defines a controller displacement and a control surface which defines a control surface authority. A module operable to provide a displacement feel to the controller in response to a remaining portion of the controller displacement being greater than a remaining portion of the control surface authority and the module operable to re-reference a center of the controller displacement to equate the remaining portion of the controller displacement with the remaining portion of the control surface authority in response to the remaining portion of the controller displacement being less than the remaining portion of the control surface authority.

Abstract: An input system (2) for a landing flap control of an aircraft. In order to make the input system (2) compact, light and reliable, it is provided with a selector lever (4) mounted pivotably by a shaft unit (10) for the input of a landing flap position, and a sensor arrangement (22) being arranged at one side of the selector lever (4) and having two mutually redundant optoelectronic sensor units (24) each for detecting a position of the selector lever (4), wherein a one-piece shaft element (40) of the shaft unit (10) is passed from the selector lever (4) through the sensor units (24).

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: A device for piloting includes a piloting member connected to at least one member for driving the craft, an electromechanical support box including, for each pivot connection, at least one actuating motor of the piloting member constituted of an electromagnetic actuator including a movable armature integrally formed with the piloting member and equipped with at least one permanent magnet having a magnetic moment parallel to the axis of the pivot connection, and an electromagnetic circuit including a fixed armature, arranged to allow the movable armature to move in the air gap zone, the magnetic moment of the movable armature sweeping each radial surface portion, and at least one coil winding which is dependent in position on the fixed armature and is capable of generating electromagnetic torque on the movable armature.

Abstract: Control station which comprises: a seat (10) for the operator of the said control station, the seat (10) comprising at least one arm rest (30), and a control and command assembly, said assembly comprising a control stick (1) with controls, mechanical components for transmitting and generating forces and movement to and from the control stick (1), components (17) for measuring the position of the control stick (1), and electronic components which are connected to the control stick (1) and via which the control and command assembly is operated, the control stick (1) of the said control station being incorporated in the seat (10), the control stick (1) being situated moreover on the armrest (30).

Abstract: Embodiments of the invention relate to a flight control system for controlling an aircraft in flight having a backup control system integrated into an active control stick. The actuated control stick may include a processing unit that includes independent and separate hardware and/or software dedicated to the primary control system and the backup control system. For the primary control system, the processing unit may receive a sensed primary control stick signal and communicate with a primary processor, which may be configured to generate a primary control signal. For the backup control system, the processing unit may receive a sensed backup control stick signal and generate a backup control signal. The processing unit may also generate tactile signal for use by the actuated control stick to adjust the feel of a pilot's control stick.

Abstract: An electric power actuator and a method of controlling such an actuator are disclosed. The actuator (1) can include means (17, 26) for limiting the pressure difference in both chambers (9, 10) of a hydraulic jack (8) of the actuator (1) to a limit pressure which is lower than an opening pressure of a pressure relief valve (11) of the actuator (1).

Abstract: An input system (2) for a landing flap control of an aircraft. In order to make the input system (2) compact, light and reliable, it is provided with a selector lever (4) mounted pivotably by a shaft unit (10) for the input of a landing flap position, and a sensor arrangement (22) being arranged at one side of the selector lever (4) and having two mutually redundant optoelectronic sensor units (24) each for detecting a position of the selector lever (4), wherein a one-piece shaft element (40) of the shaft unit (10) is passed from the selector lever (4) through the sensor units (24).

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: A steering system for a mobile platform is provided that reduces and/or eliminates backlash in the steering system. The steering system includes an input mechanism for receiving an input from an operator of the mobile platform to move the input mechanism into a first position or a second position. The input mechanism further includes an input arm. An idler is rotatably coupled to the input, and the idler is configured to engage the input arm in the second position. A pair of biasing members is coupled to the idler and the input arm to bias the input mechanism to a “center” or “neutral” position. The biasing members are operable to resist the movement of the input mechanism into the first or second positions. A steering mechanism coupled to the input mechanism monitors the position of the input mechanism and generates electrical signals to drive a motor that steers a wheel in accordance with the direction of movement of the input mechanism.

Abstract: In accordance with one embodiment of the present disclosure, a method for controlling an aircraft by a hands on throttle-and-stick (HOTAS) includes selectively connecting, by the HOTAS, two interfaces of a controller for the aircraft. The selective connection is made through one of a plurality of possible paths. Each path has an expected respective voltage drop within a predetermined range. The selected one of the possible paths connecting the two interfaces is determined by determining an actual voltage drop associated with the selected path. A control operation for the aircraft is effected by the controller based on the determined selected path. The method reduces the number of required electrical connections.

Abstract: A force sensor rod for an aircraft actuator system. The force sensor rod is constructed from a tube and a force sensing transducer. The force sensing transducer has a body containing a force responsive primary element and electronic circuitry. The force sensing transducer is provided with a protruding end composed of a material relatively harder than the tube material. The threads on the protruding end terminate in a plurality of axially spaced grooves adjacent to the force sensing transducer body and normal to the axis of the force sensing transducer. The tube is threaded onto the protruding end of the force sensing transducer and swaged onto the protruding end by causing the tube material to flow into the grooves.

Abstract: A system and a method for generating a signal to control a steering mechanism and an aircraft using the system are disclosed. A tiller module includes a moveable tiller base configured to moveably respond to a steering signal. The tiller module also includes a tiller coupling configured to couple the tiller with the moveable tiller base and further configured to generate a tiller differential signal indicative of a steering force applied to the tiller relative to a position of the moveable tiller base. A tiller controller is configured to receive the tiller differential signal and a steering mechanism position signal. The tiller controller is further configured to generate the steering signal to direct a steering mechanism to conform with the steering force and to direct the moveable tiller base of each tiller module to a feedback position representative of a current position of the steering mechanism.

Abstract: ABSTRACT A split detent tactile cueing vehicle control system (10) for a vehicle (11) is provided including an active control inceptor system (12). The active system (12) includes a control inceptor (22) having a plurality of positions and a position sensor (42) that generates a control inceptor position signal. The tactile cueing system (10) also includes a plurality of vehicle performance sensors that generate a plurality of vehicle performance signals. A flight controller (20) is electrically coupled to the position sensor (42) and the plurality of vehicle performance sensors, and generates a control inceptor actuation signal by applying a tactile cueing model having a split detent and in response to the position signal and the plurality of vehicle performance signals. A method of performing the same is also provided.

Abstract: A system and method for providing variable motion-resisting loads for a side stick controller on an aircraft where the primary resistive load is provided by a mechanical spring mechanism which is augmented or supplemented by an electric servo motor and electric servo motor linkage system.

Abstract: A device for re-trimming a pilot control of an aircraft to keep a flight parameter at a reference value includes a first detection means for detecting the actual position of the pilot control, a calculation unit for determining the direction and magnitude of displacement of the control in order to re-trim the control based on the actual position and reference position, and a display structure for displaying to the pilot a characteristic sign indicating the direction and magnitude of the displacement needed to re-trim the control.

Abstract: A device for controlling a rudder of an aircraft has at least two servo-systems each including at least one electric control input. At least one of the servo-systems is a mixed servo-system that also has a mechanical control input. When an engine fault occurs, an electric control system causes at least two of the servo-systems to simultaneously operate the rudder. When the electric control system is not operational due to an electric fault, the mixed servo-system operates the rudder based on control signals from the mechanical control input.

Abstract: A cyclic stick system for a helicopter includes sensors for measuring at least one parameter representative of the current flight status of the helicopter. In response to the at least one parameter, the cyclic stick system either (1) continuously and automatically recenters the forces on the cyclic stick, thus canceling out the residual static forces, or (2) allows the pilot fully to feel the countering action of the elastic return device on the cyclic stick.

Abstract: A control device with a control stick, wherein the control stick is moved by an irreversible actuator controlled by a computer, and the computer controls the position of the actuator and thus the movement of the control stick, and slaves the control column position to the force applied, in accordance with force data, from a force sensor, and position data, from a position sensor, through use of a position vs. force law entered in the computer.

Abstract: Automatic trim control for a position stick. Strain gauges are mounted with respect to the position stick so as to generate signals proportional to the force manually exerted upon the control stick. The signals from the strain gauges are used to control trim motors which adjust force exerted by springs on the position stick in opposition to the manual force. The signals from the strain gauges are used to control the trim motors so as to reduce the force of the trim springs opposing the manual force. The trim springs are adjusted to reduce the opposition force to a minimum.

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: An engine control system for a helicopter having at least one engine is provided, including an electronic engine control unit for each engine and further including a manually operated system for backing up each electronic engine control unit in the event of a failure thereof or for permitting optional manual engine operation. The engine control system includes at least one collective pitch stick and at least one twist grip rotatably mounted on the collective pitch stick. Each twist grip includes a normal (NORM) position within the range of the operating arc which is coincident with a detent. The system includes means for electronically actuating the detent to retract when the twist grip is rotated out of the NORM position into a manual operating mode, so that the electronic disablement of the detent permits an operator to smoothly operate the twist grip through the operating arc when the engine control system is in a manual control mode.

Abstract: An active hand controller system is provided wherein a feedback loop detects the position of a control stick to control a motor driving the control stick to thereby provide certain force feel characteristics to the control stick. The feedback loop includes a detector for detecting force exerted for the control stick to generate a signal indicative of the force or torque being applied to the control stick. In a more specific aspect, the invention includes the use of variable reluctance transformers, preferably in a push/pull configuration to detect the forces being exerted on the control stick.

Abstract: An aircraft of the heavier-than-air type driven by reactors includes a fuselage of a lenticular configuration, a central shaft, and two rotary discs rotating in opposite directions and provided with large masses of inertia displaced or diplaceable toward the periphery thereof. The discs rotate about the central shaft driven by the reactors and turbines associated thereto, determining a gyroscopic effect which renders the aircraft stable. The base of the fuselage has a middle longitudinal hollow where the reactors are located. Two vertical rudders are positioned in front of and behind the fuselage and a horizontal depth aileron extends from the rear extension of the fuselage body.